Aircraft IL-114MP IL-114P Maritime Patrol Aircraft Mig-AT Yak-130 Combat Trainers Su-32 Tu-22M3E Attack Aircraft Andbombers ..11 AIRCRAFT

AEROSPACE SYSTEMS

export catalogue Rosoboronexport

Aerospace Systems Export Catalogue

This Catalogue has been prepared by the Rosoboronexport Air Force Department and Media & PR Service with valuable support of Russian aerospace enterprises.

Additional information on the equipment described within can be requested at the Rosoboronexport central office and its representations abroad.

Rosoboronexport State Corporation 21, Gogolevsky Blvd, Moscow, 119992, Russia, Phone: +7-095 964 6140 Fax: +7-095 964 8311 www.rusarm.ru Su-33 Su-35 Su-30MK2 MiG-29 An-3T Su-80GP An-38 An-74 IL-76P IL-78MK IL-76MD/IL-76MF Military Transport andSpecial-PurposeAircraft IL-114MP IL-114P Maritime Patrol Aircraft MiG-AT Yak-130 Combat Trainers Su-32 Tu-22M3E Attack Aircraft andBombers ..11 AIRCRAFT . . .10 FOREWORD ..9 GLOSSARY ..3 CONTENTS Su-27SKM MiG-29M/M2 MiG-29KUB MiG-29K MiG-29SMT MiG-29SE Su-30MK MiG-31E MiG-21-93 Fighters Su-39 Yak-42D IL-22-M11RT M-55 GEOFIZIKA Be-200 Be-103 Tu-214 IL-96-300 ut-ups rnpr icat..3 Multi-Purpose Transport Aircraft ut-ups rnpr icat..3 Multi-Purpose Transport Aircraft ..33 Multi-Purpose Transport Aircraft Shipborne Fighter . Shipborne Fighter . Multirole Fighter Fighter-Bomber . Fighter-Bomber icatwt oy aa . . Aircraft withKopyoRadar ieFgtn icat. Fire-Fighting Aircraft Combat Trainer . Business Aircraft . Business Aircraft Light Tactical . . Fighter ut-ups mhba ..37 Multi-Purpose Amphibian ..37 Multi-Purpose Amphibian Patrol Aircraft . Patrol Aircraft obtTanr . Combat Trainer I diitaieArrf . VIP AdministrativeAircraft Convertible Flight Refuelling Tanker . .31 Convertible FlightRefuellingTanker necpo ihe . . Interceptor Fighter ut-ups rnpr icat. ..35 Multi-Purpose Transport Aircraft hpon utrl ihe ..20 Shipborne Multirole Fighter utrl ihe . Multirole Fighter Multi-Purpose Patrol Aircraft ..29 Multi-Purpose Patrol Aircraft uiesArrf . . Aircraft Business ih atclFgtr. Light Tactical Fighter ogRneMsieCryn obr..12 Long-Range Missile-CarryingBomber Fighter Modernisation Programme ..15 Fighter ModernisationProgramme utrl ihe . Multirole Fighter utrl ihe . Multirole Fighter ih utrl ihe ..19 Light Multirole Fighter Shipborne Combat Trainer ..20 Shipborne CombatTrainer ibreCmadPs n ai-ea icat..39 Airborne CommandPost andRadio-RelayAircraft utrl ihe ..21 Multirole Fighter ihAttd icat..38 High-Altitude Aircraft ROSOBORONEXPORT eimRneMltr rnpr icat..30 Medium-Range MilitaryTransport Aircraft CONTENTS ..29 ..25 . .13 ..28 ..26 ..40 . .32 ..17 ..23 ..16 ..27 .24 .22 .14 .18 .40 39 4 6

3 CONTENTS HELICOPTERS ...... 41 Combat (Combat Transport) Helicopters Mi-35/Mi-35P Combat Transport Helicopters ...... 42 Mi-35M Upgraded Combat Transport Helicopters ...... 43 Mi-28NE Combat Helicopter ...... 44 Ka-50 Single-Seat Combat Helicopter ...... 45 Ka-50-2 Tandem-Seat Modification of Ka-50 Combat Helicopter ...... 46 Military Transport and Special-Purpose Helicopters Mi-171Sh Combat Transport Helicopter ...... 47 Mi-17-1V Transport / Assault Helicopter ...... 48

CONTENTS Mi-19 Airborne Command Post Helicopter ...... 50 Mi-26/Mi-26T Heavy Transport Helicopters ...... 51 Ka-32 Utility Helicopter ...... 51 Shipborne Helicopters K-27PS Search-and-Rescue Helicopter ...... 52 Ka-28 ASW Helicopter ...... 53 Ka-29 Combat Transport Helicopter ...... 54 Ka-31 Radar Picket Helicopter ...... 55 Multirole Helicopters Ka-60/Ka-62 Utility Helicopters ...... 56 Ka-115 Utility Helicopter ...... 56 Ka-226 Utility Helicopter ...... 57 ANSAT Utility Helicopter ...... 57 Mi-2A Upgraded Utility Helicopter ...... 58 Mi-34U Trainer Helicopter ...... 58

UNMANNED AIR SYSTEMS ...... 59

REYS-D Unmanned Air Reconnaissance System ...... 60 PCHELA-1 Small-Size Tactical Air Reconnaissance System ...... 61

TRAINING SYSTEMS ...... 63

Technical Training Aids (Aircraft Simulators and Automated Training Systems) ...... 64 STBP-29 Special-Purpose Combat Trainer and IASO-29 Automated Training System ...... 64 MIG-29 Aircraft Integrated Simulation Systems for Avionics Suite and Weapons ...... 64 Technical Training Aids for Military Transport, Combat and Civil Aviation ...... 65 Mi-8/Mi-17 Helicopters Technical Training Aids ...... 66 Мi-24/Мi-35 Combat Ttransport Helicopters Technical Training Aids ...... 67 KRAB-1 Flight Procedures Trainer for Ka-50 Combat Helicopter ...... 68 Game Controllers for Virtual Training of Flying Personnel (Display Teams) ...... 68

AEROENGINES ...... 69

R25-300 Turbojet Engine ...... 70 R-95Sh, R-195 Turbojet Engines ...... 70 AL-21F-3 Turbojet Engine ...... 71 RD-33 Turbofan Engine Family ...... 71 AL-31F Turbofan Engine Family ...... 72

4 ROSOBORONEXPORT RD-1700 RD-600V TV3-117/TV7-117 PS-90А D-30КP Su-30MK MiG-AT MiG -29SМТ MiG-29SMT Avionics Suites . ..79 AVIONICS D-436TP D-30F6 NK-25 BGS-3 . Reprogrammable MemoryUnit BAGET -53 BTsVM-486 Airborne DigitalComputers MFPI-6 . Multifunctional Liquid-CrystalIndicators . Electromechanical Displays . Flight-Navigation SystemControl Consoles Displays INS-2000 LINS-2000 Navigation Systems KARAT Flight Mission KNEI-24 Mi-28NE Ka-31 Su-30MK 52Sh ..94 Helmet-Mounted Target DesignationandDisplaySystem . . Helicopter NightVision Goggles Sighting Equipment GOES-342 SHKVAL OEPS-27, OEPS-29 13S GOES-520 BUK OKHOTNYK Video InformationandLaserSystems BLIK pia aa . Optical Radar ie-mrvn usse . Video-Improving Subsystem ut-hne ae-emCnrlSse ...... 98 . Multi-Channel Laser-BeamControl System pia oainSse . Optical Location System aa ikdHlcpe voisSie..83 Radar PickedHelicopterAvionics Suite Airborne Graphic Station . Airborne GraphicStation ubfnEgn . Turbofan Engine lgtIfrainAqiiinadRcrigSse . ..86 Flight InformationAcquisitionandRecording System icatItgae lgtCnrlSses..81 Aircraft IntegratedFlightControl Systems utfntoa niainCnoe..89 Multifunctional IndicationConsole ubfnEgn . Turbofan Engine ubfnEgn . Turbofan Engine Turbofan . Engine ihigSse . Sighting System Electronic Indication and Navigation Systems ..84 Electronic IndicationandNavigationSystems obtHlcpe voisSie. ..84 Combat HelicopterAvionics Suite Turbofan Engine . Turbofan Engine ubsatEgn . Turboshaft Engine yasTroe nie..78 Bypass Turbojet Engine icatAinc ut . Aircraft Avionics Suite icatWaosCnrlSse . ..83 Aircraft WeaponsControl System nrilNvgto ytm..87 Inertial NavigationSystem ihigSse . Sighting System ihigSse . Sighting System ibreDgtlCmue aiy. . .91 Airborne DigitalComputerFamily mg rcsigSse ..97 Image Processing System ibreDgtlCmue aiy..90 Airborne DigitalComputerFamily ae nrilStlieSse ..87 Laser InertialSatelliteSystem icatAinc ut ..80 Aircraft Avionics Suite icatAtmtdCnrlSse . ..81 Aircraft AutomatedControl System lnigadPs-lgtCnrlSse ..85 Planning andPost-Flight Control System ROSOBORONEXPORT ubsatEgn aiy..76 Turboshaft Engine Family lcr-pia ihigSses..95 Electro-Optical SightingSystems ..94 . .88 ..93 . .92 . .73 ..75 ..74 ..73 ..89 ..74 ..94 ..95 . .92 .77 .88 .98 82 96 96

5 CONTENTS Airborne Radars and Active Radar Seekers OSA Airborne Radar ...... 99 BARS Airborne Radar ...... 99 ZHUK Family Airborne Radars ...... 100 KOPYO-21I/KOPYO-M Unified Airborne Radars ...... 101 KOPYO-25 Airborne Radar ...... 102 ARBALET Airborne Radar ...... 103 ARBALET-D Airborne Radar ...... 103 KOPYO-A Airborne Radar ...... 104 Weather and Flight Control Airborne Radars GUKOL-3 Airborne Radar ...... 105

CONTENTS GUKOL-7 Airborne Radar ...... 105 GUKOL-10 Airborne Radar ...... 106 9B-1103M Family Active Radar Seekers ...... 107 RVV-AE Air-to-Air Missile Active Radar Seeker ...... 108 Communications Systems K-DlAE/K-DlUE Standard Communications Sets ...... 109 AT-E Airborne Data Transfer Terminal ...... 109 AWACS Aircraft Airborne Communications System ...... 110 BKS-2ME Small-Size Communications System ...... 110 Ground Communications System ...... 111 K-DLI-03-1 Standard Airborne Data Communications Set ...... 112 KARDAN Telephone Encryption Equipment ...... 112 Electronic Warfare Systems OLEN Digital Information Encryption Equipment ...... 113 L-150 PASTEL Radar Warning System ...... 113 SUKHOGRUZ Electro-Optical Countermeasures System ...... 113 ECM Equipment. Helicopter and Aircraft Electro-Optical System ...... 114

ARMAMENT ...... 117 Guided Air-to-Air Weapons R-73E Short-Range Air-to-Air Missile ...... 118 R-33E Long-Range Air-to-Air Missile ...... 118 R-27 Medium-Range Air-to-Air Missile Family ...... 119 RVV-AE Medium-Range Air-to-Air Missile ...... 120 STRELETS Control Equipment and Launch Module Set ...... 121 IGLA-S Guided Missile ...... 121 Air-to-Surface Guided Missiles

Kh-22E Supersonic Long-Range Air-to-Surface Missile ...... 122 Kh-29 Short-Range Air-to-Surface Missile Family ...... 122 Kh-31 Supersonic Air-to-Surface Missile Family ...... 123 Kh-35E Anti-Ship Missile ...... 123 Kh-59ME Medium-Range Air-to-Surface Missile ...... 124 KORNET-E Antitank Missile System ...... 124 HERMES-A Guided Weapon System ...... 125 SHTURM Antitank Guided Missile ...... 126 ATAKA Antitank Guided Missile ...... 126

6 ROSOBORONEXPORT KORD MDM-3 UPK-23-250 GSh-30 2A42 GSh-301 GSh-23L Guns S-25-OFM P-50T BetAB-500 ODAB OFZAB OFAB FAB-500 M62 Air Bombs VMSK-4-15 VKK-15K ..145 LIFE SUPPORTEQUIPMENT DOZOR ADK PRIZMA Topaz-M ..141 INTEGRATED GROUNDMONITORINGEQUIPMENT ZSZh-66M A2111-0000 NGZh-4 UPG-300/UPG-300 RSBN-4N PRMG-5 PAR-10 ..137 AIRFIELD EQUIPMENT S3V APR-3E UMGT-1ME Guided Air-to-SubmarineWeapons KAB-1500 KAB-1500Kr KAB-500 Guided Bombs S-24B S-13 S-8 Air Rockets M6/M6T Aircraft . RocketFamily S uddBm . ASW GuidedBomb icatRce aiy. Aircraft RocketFamily EFamnainIcnir ob ..130 HE Fragmentation IncendiaryBombs niakGn. Antitank Gun Fuel-Air Explosive Bombs . Fuel-Air ExplosiveBombs rcieBm . Practice Bomb 27m ahn u . ..13 12.7 mmMachineGun icatRce . Aircraft Rocket EFamnainIcnir ob..130 Fragmentation IncendiaryBomb HE nln oioigSse ..144 On-line MonitoringSystem ibreBto ie ..12 Airborne BottomMines o-ietoa ai ecn..138 Non-Directional RadioBeacon i-anhdAWMsie ..129 Air-Launched ASWMissiles 0m ibreDul-arlGn..136 30 mmAirborneDouble-Barrel Gun lgtIfrainPoesn ytm ..142 Flight InformationProcessing Systems adn ecnSse . ..138 Landing BeaconSystem icatCno . Aircraft Cannon ibreSalSz agt..132 Airborne Small-SizeTarget icatCno . Aircraft Cannon Guided BombFamily ..127 High-Altitude Pressure Suit ..146 High-Altitude Pressure Suit Radio Navigation Ground Beacon ..139 Radio NavigationGround Beacon icatRce . . Aircraft Rocket uddBm aiy. ..128 Guided BombFamily Oil/Hydraulic Fluid Refiller ..140 Oil/Hydraulic FluidRefiller oceePecn ob..131 Concrete-Piercing Bomb efHmn opd ..128 Self-Homing Torpedo e uvvlHg-liueSi ..146 Sea SurvivalHigh-AltitudeSuit estl u o ..136 Versatile GunPod uddBm ihT ekr..127 Guided BombwithTVSeeker uoae igotcSse ..143 Automated DiagnosticSystem i/yrui li eilr..140 Oil/Hydraulic FluidRefiller ihEpoieBm ..130 High-Explosive Bomb ROSOBORONEXPORT estl oieHdalcSse ..139 Versatile MobileHydraulicSystem . .135 . .133 ..134 ..131 . .133 ..129 .135 .135 .134 .131 5 9

7 CONTENTS PPK-3-120 Anti-G Suit ...... 147 VK-3M Air Ventilation Suit ...... 147 ZSh-7V Helicopter Crash Helmet ...... 148

SPACE SERVICES ...... 149

KOSMOS-3M Launch Vehicle ...... 150 STRELA Launch Vehicle ...... 151 DNEPR-1 Launch Vehicle ...... 152 ROCKOT Launch Vehicle ...... 153 START/START-1 Launch Vehicles ...... 154 SOYUZ-U Launch Vehicle ...... 155

CONTENTS MOLNIYA-M Launch Vehicle ...... 156 PROTON-M Launch Vehicle ...... 157 AIR LAUNCH Space Transportation System ...... 158 KONDOR-E Space Remote Sensing System ...... 159

REPRESENTATIVE OFFICES ABROAD ...... 160

8 ROSOBORONEXPORT WCS NBC NAVSTAR MFD M LV LCD kW ISA IR IFF ICBM ICAO HUD hp HF HE GPS GLONASS EW ET VHF UHF UAV TNT STOL SNS SAM RWR RMS RPV RCS NVG FCS SAR ECM ECCM CEP AWACS ATGM ASW ASM AD TVC SHF ...... Identification ..Circular Er ...... InternationalStandard Atmosphe . . ..Radar ..SatelliteNavigat ..Remotely-Pilo ..Searc . ..SuperHig ..Ele ..UltraH ..Fire ..RadarWarning ...... Root Root . ..NightV ..WeaponsControl . ..Surface-t ..Air-to-Su ..Very Hi ..LiquidCr ..H ..GlobalPositionin ..Electronic Countermea ..Multifunc ..ThrustVe ..Nuclear, Biological&Che ..UnmannedAi ..Anti-Submarine ..InternationalCivilAviation Organisation ..ShortTake-Off & ..Inter-ContinentalBallisticMis ..Electronic Counter-Countermeasures ..Anti-Tank GuidedMi ..AirborneWarning&Control System ..GlobalNavigationSatelliteSystem ..NavigationSatelliteTiming &Ranging ROSOBORONEXPORT GLOSSARY . .LaunchVehicle . .ExternalTank . .HighFrequency . .horsepower . .Infra-Red . .Mach . .AirDefence . .HighExplosive . .kilowatt . .Trinitrotoluene ctronic Warfare Control System ead-Up Display Cross Section h-and-Rescue ror Probability igh Frequency Mean Square ision Goggles gh Frequency Friend orFoe rface Missile ystal Display o-Air Missile h Frequency tion Display ctor Control ion System ted Vehicle Receiver g System r Vehicle Landing System Warfare sures mical ssile sile re

9 GLOSSARY FOREWORD

The revised edition of the "Aerospace Systems" catalogue gives brief descriptions of Russian military/dual-use air and space systems and services offered for export by the Rosoboronexport State Corporation. It covers most important defence-related aerospace technologies developed in Russia, namely:

FOREWORD • Aircraft • Helicopters • Unmanned air systems • Flight simulators • Aeroengines • Avionics • Armament • Airfield equipment • Ground Monitoring Equipment • Life support equipment • Space systems and services The catalogue embraces both major military aviation air systems and support facilities, including manned and unmanned aircraft, airborne munitions, ground support equipment, engines, avionics, simulators, etc. The Corporation ensures proper operation of the equipment supplied, its maintenance, spare parts supply, servicing and upgrading, as well as personnel training, organisation of license production, repair and servicing, assistance in constructing airfields, air traffic control systems and command posts. It also offers customer-defined research and development projects, joint production and promotion of aviation materiel to foreign markets, upgrading of the vintage equipment and armament, etc. Rosoboronexport markets Russian space technologies under strict state control of the missile non-proliferation regime observance. Offered for export are Earth remote sensing, space communication/navigation systems, and development projects for customer-defined space-based systems, as well as services rendered by Russia’s space infrastructure (cosmodromes, space control centres, launch vehicles) in putting customer payloads into orbit. The item list of the catalogue is by no means exhaustive, but rather indicative of the major aerospace areas where products and services are available for export. The Rosoboronexport catalogue "Aerospace Systems" is intended for foreign Air Force com- manders and defence procurement experts as a reference publication.

10 ROSOBORONEXPORT AEROSPACE SYSTEMS

AIRCRAFT

ROSOBORONEXPORT 11 Tu-22M3E Long-Range Missile-Carrying Bomber AIRCRAFT BOMBERS

Mission paved airfields; as well as enemy manpower and materiel concentration areas. The aircraft can The Tu-22M3E aircraft is intended to carry out penetrate enemy air defences at different flight missile and bomb attacks against mobile and altitudes and speeds, depending on the situation. stationary targets in land and sea theatres of In sea theatres of operation, the Tu-22M3E operation. It is capable of stand-alone and group can engage groups of ships, including carrier operations in hostile air defence and ECM envi- battle groups, and can also be employed in ronments. water zone and fairway minelaying operations. In land theatres of operation the Tu-22M3E is capable of engaging installations of public and Armament military administration, defence industry targets, power supply systems and communications net- The airplane carries up to three Kh-22E mis- works; rendering ineffective air force bases and siles. Up to 24,000kg free-fall munitions, dis- tributed between the weapons bay, two fuse- Basic specifications lage and two underwing multi-shackle racks, Length, m 42.46 can comprise up to sixty-nine 250kg bombs, Wingspan, m 27.70/34.28 forty-two 500kg bombs, or eight 1,500kg Height on the ground, m 11.05 bombs. Max take-off weight, kg 124,000 A 23mm gun installed in the aft offers the Combat load, kg: rear hemisphere protection. normal 12,000 maximum 24,000 Equipment Max air speed, km/h 2,000 Cruising air speed, km/h 900 The onboard defence system comprises Service ceiling, m 10,200 - 14,000 active ECM pods to jam enemy ground/airborne Tactical radius, km 2,200 radars, and also chaff and flare dispensers. Take-off run, m 2,000 - 2,100 The avionics suite ensures automatic naviga- Landing roll, m 1,200 - 1,300 tion, aiming and piloting when flying a pre-pro- Powerplant 2 x NK-25 afterburning grammed or in-flight programmed mission. It turbojets also provides bomb dropping and missile Crew 4 launch control.

12 ROSOBORONEXPORT avionics systemalsoincludesalaser-TVstation acquisition rangeisfrom 30to100km.The time. Whereas theground (surface)target – engaged ata simultaneously andupto4 km. Thus,providing upto10targetstracked section of3sqmeters atarangeofleast120 array radarthatdetectsairtargetswithcross operating conditions.Itincorporatesaphased- mission accomplishmentintheentire rangeof terrains. with highprecision overflat andmountainous attack weaponsfrom highandlowaltitudes sea-surface andairtargets,unguided sion guidedairattackweaponsagainstground, following flight andemploymentofhigh-preci- capacity andsurvivability, low-altitudeterrain- AD weaponcontrol systems. aerial reconnaissance andneutralizeenemy's defence andECMenvironments; toconduct adverse weatherconditionsinhostileair mobile, aswellairtargetsundernormaland including pointandmultiple,stationary designed todestroy ground (surface)targets, Equipment Mission The avionicssuiteensures highlyautomated The two-seatSu-32fighter-bomber is The aircraft features highcombatpayload ROSOBORONEXPORT gun with150rounds. The aircraft isarmedwithabuilt-inGSh-301 25 rockets 250-and500-kgcalibre airbombs. as wellunguidedweapons:S-8,S-13andS- 500L (Кr),КАB-1500L(Кr)laser-guidedbombs, Kh-59МE, Kh-31А(P),KH-29ТЕ(L)ASMs;КАB- 27R1(ER1), R-27Т1(EТ1),R-73E,RVV-АЕAAMs; hardpoints andincludesguidedweapons:R- Armament full height,takefood,etc. where crew's members canstanduptotheir area insidedeepfuselagesectionaft ofcockpit, masks uptoanaltitudeof10km.There isarest members tooperateincockpitwithoutoxygen obtrdu,k 1,100 2xAL-31Fturbofaws 8,000 15 Crew 2 Powerplant Combat radius,km 38,240 Max airspeed,km/h: Combat load,kg Service ceiling,km Take-off weight,normal,kg Dimensions, m: Basic specifications The Su-32combatpayloadiscarriedon12 egh23.34 length ihlvl1,900 1,400 6.085 14.7 high-level ground-level wing span,m height Fighter-Bomber tem allowscrew air conditioningsys- The in durationflights. litate crew's operation tions significantly faci- fortable cockpitcondi- rumentation andcom- ments. trols andinstru- duplication ofcon- bers andavoids ween crew's mem- direct contactbet- gement provides a by-side arran- The two-seatside- mated ECMsystem. and apowerfulauto- Modern inst- Su-32

13 FIGHTER-BOMBERS AIRCRAFT Su-39 Aircraft

Mission

The Su-39 aircraft, equipped with Kopyo radar is a profound upgrading of the baseline Su-25 ground attack airplane. It is intended specifically for counteraction to small-size, well- protected targets (including new-generation NATO tanks), by day and night in all weather

AIRCRAFT conditions. The navigation system is supplemented with the A-737 satellite navigation unit, which Equipment enables automatic target acquisition with up to 15m position accuracy regardless of the dis- The onboard SUV-25T Voskhod weapons con- tance to the target. trol system is designed to identify and automat- The upgraded EW system comprises both ically track mobile small-size targets (tanks, built-in equipment and externally-mounted vehicles, boats, etc.), provide target designation pods. and automatic missile guidance and control for The airplane’s protection has also been

ATTACK AIRCRAFT ATTACK missile/gun/rocket. The Shkval-M optical-TV increased: the total weight of onboard surviv- sighting system performs target search and ability assets amounts to 1,115 kg. identification in the scanning mode. Automated A pressurised cockpit offers an increase in the navigation and target attack procedures enable maximum combat altitude to 12,000 m from a group of Su-39s to strictly maintain pre- the baseline aircraft’s 7,000 m. scribed time intervals, and, as a result, a well- coordinated group attack from different direc- Armament tions. The Su-39 automatically flies to the target area, and its pre-directed TV system is activat- The Su-39 weaponry fixed on ten external wing ed 10-12 km away from the target. The pilot hard-points includes 16 Vikhr (Vikhr-M) super- monitors automatic target selection, lock-on, sonic antitank missiles, Kh-29T air-to-surface and switching to the autotracking mode. After TV homing missiles or Kh-25ML, Kh-29L and S- the first target run the aircraft can either auto- 25L laser homing missiles, as well as 500kg matically complete a second run or return to KAB-500Kr bombs. The ordnance includes Kh- home base, if the pilot so decides (manual con- 58E or Kh-31P anti-radiation missiles. trol can be resumed only before landing). The aircraft can also carry R-73E, R-27R1 Another novelty in the aircraft’s avionics is and R-27ER1 air-to-air missiles; up to eight B- the pod-mounted Kopyo-25 radar. 8M1 or B-13L rocket pods (with 20 S-8 rockets and five S-13 rockets each respectively); and up Basic specifications to eight S-24 or S-25 rockets. The free-fall ord- Length (with airspeed boom), m 15.33 nance includes bombs of 100-500kg calibre. Wingspan, m 14.52 Eight KMGU cluster bomb pods can be addi- Height, m 5.20 tionally fitted for use against area targets. Max take-off weight, kg 19,500 The aircraft carries one built-in NPPU-8 Combat load, kg 4,000 mount with the 30mm GSh-30 gun Max air speed, km/h 950 (200-round ammunition). Service ceiling, m 10,000 Ferry range, km 2,500 Variants Take-off run (soil/concrete), m 750/680 The twin-seat combat trainer Su-25UBK is Landing roll (soil/concrete), m 750/650 designed for mastering piloting skills. Powerplant 2 x R-195 turbojets Crew 1

14 ROSOBORONEXPORT and aft hemispheres andagainsttheEarth’s radar provides missileguidanceintheforward attack oftwomostdangerous ones.TheKopyo ing ofuptoeighttargets,andsimultaneous with anewWCSensuringsimultaneoustrack- for improved field ofview. windshield andamodified hingedportioncover ECM systems. indigenous communications,navigationand Israeli-made passivejammingsystem,and navigation andvideorecording systems,an of theIndianAirForce features French-made example, theupgradedMiG-21bisUPGfighter foreign-made armamentandequipment.For ed. cockpit managementsystemsare alsoupgrad- power supply, airconditioning,fire-fighting, and and flight datarecording system. tems; aswelltheKaratintegratedmonitoring communication, ECM,andvideorecording sys- function LCDs andhead-updisplay, navigation, met-mounted targetdesignationsystem,multi- built around theKopyomultifunctionradar, hel- installation ofanewweaponscontrol system controls, andintroduction ofnew weapons. of thebaselinefighter design,equipmentand Modernisation packageincludesimprovements combat capabilitieswithminimumexpenditures. aims toconsiderablyimprove theMiG-21aircraft Equipment Mission The modernisationprogramme alsoimplies The MiG-21-93modernisationprogramme The MiG-21-93upgradedfighter isequipped The upgradedcanopyfeatures aframeless The MiG-21-93upgradecanmountoptional The MiG-21baselineflight control, electric ROSOBORONEXPORT Fighter ModernisationProgramme aircraft’s servicelife. 2000. with thatofF-16andMirage fourth-generation fighters makingitcomparable enhances itscombatefficiency tothelevelof defence systems. Stinger-type heat-seekingman-portableair self-defence againstair-to-airmissilesand and free-fall ordnance. face targets,andengagingthemwithguided detecting radar-contrastground andsea-sur- capable ofconductingtacticalreconnaissance, "Vertical". Inthemappingmode radaris is supportedbyaspecialradaroperationmode tudes downto30maboveground. Dogfighting background, withtargetacquisitionatlowalti- the MiG-21bis. bombs, retaining theorganicweaponsmixof R-73E air-to-airmissilesandKAB-500Krguided ment, includingRVV-AE,R-27T1,R-27R1and Armament rw1 Crew a -od +8 1xR25-300 17,000 Powerplant Max g-load 1,500 4.125 Range, km: 15.0 7.15 Service ceiling,m Max airspeed,km/h: Max combatload,kg Take-off weight,kg: Height, m Wing span,m Length, m Basic specifications Upgrading mayalsoincludeextensionofthe The MiG-21-93upgradingprogramme The BVP-21chaff/flare dispensers provide The MiG-21-93upgrademountsnewarma- rudlvl 1,300 high-level 1,350 low-level 840 high-level 2,175 ground level maximum 10,400 normal 9,200 MiG-21-93 afterburning turbojet

15 ATTACK FIGHTERS AIRCRAFT MiG-31E Interceptor

engaging any airborne threats, including cruise missiles, helicopters and high- altitude reconnaissance aircraft. The MiG-31E can inter- operate with various aircraft and provide target designation for up to three fighters,

AIRCRAFT such as the MiG-21-93, MiG- 23, MiG-25, MiG-29, and Su- 27, and mask their attack. Mission Equipment The MiG-31E interceptor aircraft is designed FIGHTERS to intercept and destroy air targets at low and The MiG-31E weapons control system is high altitudes, in the forward and aft hemi- built around a phased array radar. It can spheres, both in the lookup and lookdown simultaneously track up to 10 air targets and modes, in all weather conditions, despite target attack up to four. The surveillance, tracking manoeuvring and active/passive ECM. The air- and attack envelope is limited by ± 70 deg in craft can operate alone or within a group in the azimuth and +70…-60 deg in elevation. continuous or discrete field of control and guid- The radar can detect a target with a 19 sq.m ance commands. It is capable of semi- radar cross section at 200 km. autonomous or fully autonomous operations The WCS also includes an IR system provid- against manoeuvring and ECM-protected tar- ing concealed target acquisition and designa- gets. The MiG-31E is designed for employment tion, and operation in severe ECM environment. as part of the nation’s air defence system. It is The aircraft provides excellent interoperabil- capable of long-endurance patrolling and ity within a group owing to the onboard radar and data transmission equipment ensuring automatic data exchange between four inter- Basic specifications ceptors at a range of up to 200 km. The group Length (with airspeed boom), m 21.620 leader assigns targets to his wingmen. A group Wing span, m 13.456 of four MiG-31Es is capable of controlling an Height, m 6.465 800-900km-long frontline. Max take-off weight, kg 46,200 The aircraft features EW assets operating Max air speed, km/h: both in the radar and IR frequency bands. ground level 1,500 high-level 3,000 Armament Service ceiling, m 20,600 Interception range, km: The basic MiG-31E weapons mix includes M=2.35, H=18,000 m 720 four R-33E long-range missiles carried on a M=0.8, H=10,000 m 1,450 semi-recessed pylon under the fuselage, and R- M=0.8, H=10,000 m with one flight refuelling 2,250 40TD-1 and R-60MK missiles under the wing. Take-off run, m 1,200 The aircraft also has one GSh-6-23M six-barrel Landing roll, m 800 gun with the 260-round ammunition allowance. Required runway length, m 2,500 Max g-load 5.0 Powerplant 2 x D-30F6 afterburning turbofans Crew 2

16 ROSOBORONEXPORT MiG-29 Light tactical fighter

the radar, optical locating station or directly to the missile seeker, with an accuracy adequate enough for effective weapons employment.

Armament The aircraft weapons include the GSh-301 built-in gun, as well as the R-27R1 and R-73E air-to-air guided missiles, rockets and bombs Mission suspended under six external stores hardpoints. The MiG-29 light tactical fighter is designed AIRCRAFT to intercept and defeat air targets day and night under normal and adverse weather conditions Variants The MiG-29UB is designed for instructing and in free air space and against ground surface in training pilots to fly the aircraft, intercept air tar- natural clutter and ECM environment, using air- gets and engage air and ground targets within to-air missiles with semi-active radar/IR seek- the MiG-29’s altitude/airspeed combat enve- ers, as well as to destroy ground targets with FIGHTERS lope. It can also perform separate combat mis- unguided weapons in conditions of visual flight sions autonomously and within a MiG-29s rules. It operates over friendly territory and in group. the near-operative and tactical zones of the The MiG-29UB differs from the combat fight- enemy. er mainly by its two-seat cockpit, absence of the The aircraft features high combat effective- targeting radar and R-27R1 guided missiles. ness, outstanding maneuverability, high reliabil- The aircraft and its engines, flight-navigation ity and flight safety, and easy operation. system, armaments, communication aids and The MiG-29 and MiG-29UB aircraft are base- in-cockpit warning systems can be managed line models for upgrades of varied complexity, from both cockpits. The instructor’s cockpit including the MiG-29SE, MiG-29SMT, MiG- accommodates a failures simulation console 29UBT modifications. and a switching console to imitate operation of The aircraft has its air intakes closed to pre- the radar targeting system during air target vent foreign object damage of engines when interceptions with simulated R-27R1 missiles. moving on the ground, especially on poorly An interactive training system and simulators organized airfields and aprons. are used for on-ground formation of the flying Equipment and technical personnel. The weapons control system consists of a Basic specifications radar targeting system with the N-019 radar MiG-29 MiG-29UB and an electro-optical targeting/navigation sys- Take-off weight, kg: tem with an air target acquisition, lock-on and tracking optical locating system including an IR normal 14,900 14,600 search-and-track system and a laser range- max 18,000 finder, as well as a helmet-mounted target des- Powerplant RD-33 ignation system. Afterburning thrust, kgf 2 х 8,300 A unique avionic system has been created Max g-load 9.0 thanks to the radar, optical locator and helmet- Max airspeed, km/h: mounted sight data fusion and algorithms inte- ground-level 1,500 1,450 gration. Data exchange between the optical high-level 2,400 2,230 locator and radar has helped to notably Service ceiling, km 18.0 17.5 enhance noise immunity of the aircraft target- Flight range, km: ing system as a whole. The MiG-29 helmet- w/o EFT 1,500 1,460 mounted target designation system is used for with 1 х EFT / quick locking-on to air targets visually detected with 3 х EFT 2,100/2,900 2,000/2,800 by the pilot through the cockpit glass allowing Max external him to designate a target within one second to payload, kg 4,000 2,500

ROSOBORONEXPORT 17 MiG-29SE Light Tactical Fighter

Mission

The MiG-29SE light tactical fighter is designed for engagement of air targets, as well as ground and maritime targets. The fighter features high

AIRCRAFT combat effectiveness, outstanding maneuverability, high reliability, and flight safety. The MIG-29SE is simple and economical in operation, being main-

FIGHTERS An interactive training system, simulators tained on condition. It has an increased flight and the MiG-29UB aircraft are used for on- life in excess of 3,000 flying hours and a service ground formation of the flying and technical per- life of 30 years with possible prolongation. sonnel. The aircraft can be equipped and armed with Equipment systems and munitions of foreign origin.

The aircraft is equipped with the integrated weapons control system including the NO19- Armament ME upgraded radar ensuring multiple target engagement with the RVV-AE air-to-air missiles, The upgraded weapons system includes the optical locating station, and helmet-mounted R-27ER1, R-27EТ1, R-27Т1, R-27R1, R-73E target designation system. air-to-air missiles, GSh-301 built-in gun, air The aircraft is fitted with an in-flight refuelling bombs and rockets. system allowing it to receive fuel from both Russian and foreign air tankers.

Basic specifications Take-off weight, kg: normal 15,300 max 20,000 Powerplant RD-33 afterburning thrust, kgf 2 х 8,300 Max g-load 9.0 Max airspeed, km/h: ground-level 1,500 high-level 2,400 Service ceiling, km 17.75 Flight range, km: w/o EFT / with 3 x EFT 1,500/2,900 with 3 х EFT and one in-flight refuelling more than 5,400 Max external payload, kg 4,500

18 ROSOBORONEXPORT ed targetdesignationsystemmaketheavionics The opticallocatingstationandhelmet-mount- advanced air-to-surfaceoperationalmodes. range, multi-channelfire capabilityand multifunctional radarfeaturingincreased radar targetingsystemwiththenewZhuk-ME weapons control systemincludingamodified equipment ontheaircraft atcustomerrequests. 1553В standard enablesmountingofany effected incompliancewith theМIL-STD- and HOTAS arrangement.Systemintegration button-fitted liquid-crystalcolourindicators, cockpit environment withtwomultifunctional avionics suite,up-to-dateinformation/control with on-conditionmaintenance). service lifereaches 4,000hours (or40years – safety enhanced. lent manoeuvrabilitywithreliability andflight air-to-surface missions.Theaircraft hasexcel- acquired highcombatefficiency inair-to-airand As aresult ofthemodernization, theaircraft has (flight rangeandendurance)ataminimalcost. capabilities byincreasing itscombatradius provide thefighter withentirely newcombat upgrading oftheMiG-29tacticalfighter. Itisto Equipment Mission The aircraft features anopen-architecture The MiG-29SMTisthelatestcomprehensive The MiG-29SMTisfitted withmodern As aresult ofthemodernization, thefighter’s ROSOBORONEXPORT technical personnel. used foron-ground formationoftheflying and and theMiG-29UBTcombattraineraircraft are well asoptronic pods. bombs. also deliverunguidedweapons–rockets and missiles andKAB-500Lguidedbombs.Itcan pod, thefighter canemploytheKh-29Lguided rected bombs.Iffitted withanoptronic/laser to-surface guidedmissiles,andKAB-500Krcor- gun, Kh-31А,Kh-31P, Kh-29T(ТЕ),Kh-35Eair- 73E air-to-airguidedmissiles,GSh-301built-in АЕ, R-27ER1,R-27EТ1,R-27R1,R-27Т1,R- Armament a xenlpyod g5,000 Max externalpayload,kg Flight range,km: Max airspeed,km/h: Take-off weight,kg: Basic specifications evc eln,k 17.7 9.0 RD-33series3 Service ceiling,km Max g-load Powerplant An interactivetrainingsystem,simulators The aircraft guidedweaponsincludetheRVV- tgon-ee 1,500 1,800/3,100 15,800 w/o EFT/with3x at ground-level normal eulig morethan6,000 2,400 20,300 refuelling with 3хEFTandonein-flight 2х8,300 at highaltitude afterburning thrust,kgf max ing andrecording systems, as measures equipment,monitor- facilities, electronic counter- navigation andcommunication four. ously engagedisincreased to number oftargetssimultane- and sightingangleswhilethe greater targetacquisitionrange system hasresulted inmuch basis ofthemoderncomputing navigational equipmentonthe Integration ofthetargetingand suite functionallycomplete. ih utrl Fighter Light Multirole The aircraft isfitted withnew MiG-29SMT

19 FIGHTERS AIRCRAFT MiG-29K/KUB Shipborne Multirole Fighter Mission The MiG-29К/KUB ship-borne multirole fighter is designed to perform naval groupings’ air defence tasks, to gain air superiority, to engage surface and ground (coastal) targets, including small-size ones, with precision-guided enhanced operational range, multi-channel fire weapons, by day and night, in any weather con- capability and modern air-to-ground modes of ditions. The fighter is optimized for basing on operation. The optical locating station and hel- aircraft carriers of medium displacement. met-mounted targeting system make the avionic suite of the aircraft functionally complete.

AIRCRAFT The MiG-29K fighter is a new-generation MiG-29. It differs from the latest MiG-29SMT Integration of the targeting and navigational upgrade by increased internal fuel load, upgrad- equipment on the basis of the modern comput- ed engine with increased thrust and smokeless ing system has resulted in much greater target combustion chamber, digital multi-channel fly- acquisition range and sighting angles while the by-wire control system, and stores stations number of targets simultaneously engaged is FIGHTERS number increased to 8. For operations on the increased to four. aircraft carrier the aircraft has an arrester hook Armament and a reinforced landing gear. Its flight life and The weapons mix of the aircraft includes the service life are also increased – to 6,000 flying RVV-AE and R-73E air-to-air guided missiles, hours and 30-40 years correspondingly. The airair-to-surface guided weapons, such as the Kh- craft is maintained on condition. 35E and Kh-31A anti-ship missiles, Kh-31P anti-radiation guided missiles and KAB-500Kr Equipment guided bombs. Unguided weapons include the The aircraft has an open-architecture avion- FAB-500 air bombs and rockets. The aircraft is ics suite based on the MIL-STD-1553B multi- armed with the GSh-301 built-in gun. plexing bus enabling integration of onboard equipment and weapon systems of Russian Variants and foreign origins at customer requests. The MiG-29KUB ship-borne combat trainer is The MiG-29K aircraft is equipped with the designed for naval aviation pilots’ training and modern weapons control system including the mastering flying skills, monitoring their tech- Zhuk-ME new multifunctional radar with niques of flight management, navigation and combat employment, as well as pilot transition Basic specifications to the MIG-29K aircraft. In terms of its combat MiG-29К MiG-29KUB mission, the MiG-29KUB performs the entire Take-off weight, kg: scope of MiG-29K assigned combat tasks. normal 18,550 18,650 The MiG-29KUB has a high degree of design max 24,500 commonality with the MiG-29K aircraft. It is Powerplant RD-33МК also equipped with the Zhuk-ME airborne radar Afterburning thrust, kgf 2 х 9,000 and carries the same weapons mix. The aircraft Max g-load 8.0 can be a baseline model for creation of recon- Max airspeed, km/h: naissance, target designation, electronic coun- at ground level 1,400 termeasures, and flight refuelling modifica- at high altitude 2,100 2,100 tions. Service ceiling, km 17.5 The MiG-29К and MiG-29KUB aircraft have Flight range, km: an integral in-flight refuelling system and are w/o EFT 2,000 1,700 equipped with the UPAZ suspended universal with 3 х EFT 3,000 2,700 refueling unit providing for in-flight refuelling of Max external payload, kg both internal and external fuel tanks. An interactive training system and simulators with 3 х EFT and one are used for on-ground formation of the flying in-flight refuelling, kg 6,500 and technical personnel.

20 ROSOBORONEXPORT advanced weaponscontrol systemincludingthe and foreign originsatcustomerrequest. equipment andweaponsystemsofbothRussian plexing busenablingintegrationoftheonboard architecture basedontheMIL-STD-1553B multi- 29K/KUB by95%. MIG-29M/M2 fighter isunified withtheMiG- 40 years correspondingly. life are alsoincreased to6,000 flying hours and reinforced landinggear. Itsflight lifeandservice tions numberincreased to8.Theaircraft hasa channel fly-by-wire control system,stores sta- smokeless combustionchamber, digitalmulti- upgraded enginewithincreased thrustand upgrade bytheincreased internalfuelload, MiG-29. Itdiffers from thelatestMiG-29SMT refuelling system. tively. Theaircraft isequippedwithanin-flight conditions, canbeaccomplishedmore effec- in agroup ofMiG-29s,operationsinjamming attacks againstground targets,operationswith- sion), certaincombatmissions,especially istics, andeasyoperation. ness, outstandingflight performancecharacter- ment. er conditions,andincomplexjammingenviron- gets bydayandnightinfairadverse weath- designed todefeatairandground/surface tar- Equipment Mission The MiG-29M/M2avionicssuitehasanopen The MiG-29M/M2multirole fighter is The MiG-29Maircraft isequippedwiththe The aircraft ismaintainedoncondition.The The MiG-29Maircraft isanew-generation Thanks toasecondcrewmember (onM2ver- The aircraft features highcombateffective- ROSOBORONEXPORT neously engaged(uptofour). angles, aswellthenumberoftargetssimulta- increase targetacquisitionrangeandsighting ern computingsystemhashelpedtonotably navigational equipmentonthebasisofmod- and technicalpersonnel. are offered foron-ground formationoftheflying GSh-301 built-ingun. ed bombs,unguidedrockets, bombsandthe guided missiles,КАB-500Кr, КАB-500Lcorrect- Kh-29L, Kh-31А,Kh-31P, Kh-35Eair-to-surface R-73E air-to-airguidedmissiles,Kh-29T(ТE), RVV-АЕ, R-27ER1,R-27EТ1,R-27R1,R-27Т1, Armament rw12 1 Crew a prtoa -od 9.0 Flight range,km: 2х9,000 Max airspeed,km/h: g-load Max operational Afterburning thrust,kgf Take-off weight,kg: Basic specifications a xenlpyod g6,500 17.5 Max externalpayload,kg RD-33МК Service ceiling,km Powerplant An interactivetrainingsystemandsimulators The weaponscontrol systemmanagesthe tgon-ee 1,500 w/o EFT/ 17,800 at ground-level 17,500 normal nfih eulig gmorethan5,500 1,700/2,700 2,200 2,000/3,200 in-flight refuelling,kg with 3хEFTandone with 3хEFT 23,700 2,400 22,400 at highaltitude max Integration ofthetargetingand the aircraft functionallycomplete. system maketheavionicsuiteof tion andhelmet-mountedtargeting operation. Theopticallocatingsta- modern air-to-ground modesof multi-channel fire capabilityand with enhancedoperationalrange, new Zhuk-Mmulti-functionradar MiG-29M/M2 Multirole Fighter i-9 MiG-29М2 MiG-29М

21 FIGHTERS AIRCRAFT Su-27SKM Multirole Fighter

Mission

The Su-27SKM is a highly maneuverable single-seat multirole fighter. It is designed to gain air superiority, defeat air and ground targets in all weather with guided and unguided

AIRCRAFT weapons, while operating self- sustained or within an air group.

Equipment tem provides high-accuracy navigation in all stages of flight. The cockpit instrumentation The aircraft is equipped with the surveil- facilitates the pilot to operate effectively using a FIGHTERS lance/sighting (radar and optronic) systems combination of the large-size colour LC multi- that provide engagement of air and ground (sur- functional displays. The in-flight refuelling sys- face) targets, day and night, under fair and tem enables to increase the fighter's flight adverse weather conditions. The built-in laser endurance restricted by physical ability of a range-finder ensures efficient employment of pilot. high-precision weapons. The radar mapping of ground (water) surface Armament and target tracking provide pre-launch target designation and employment of missiles and air The Su-27SKM combat load is carried on ten bombs in any weather, day and night. external hardpoints and includes R-27 air-to-air The high-performance ECM equipment is missiles of all modifications, R-73E and RVV-AE installed on fighter to destroy the hostile radars AAMs, as well as Kh-31A, Kh-31P, Kh-29T (TE, by anti-radiation missiles. The navigation sys- L) ASMs and KAB-1500Kr and KAB-500Kr guided bombs. The unguided weapons comprise S- 8, S-13 and S-25 rockets and up to 500-kg cal- Basic specifications ibre air bombs. Length 21.9 The aircraft is also armed with a built-in GSh- Wing span, m 14.7 301 gun with 150 rounds of ammunition. Height, m 5.9 A combination of outstanding flight perform- Take-off weigh, kg ance and highly-efficient weapons mix makes normal 23,430 the Su-27SKM the most flexible, highly agile max 33,000 and powerful multirole fighter. Max combat load, kg 4,430 Max airspeed: ground-level, km/h 1,400 high-level, Mach number 2.15 Service ceiling, km 18,500 Flight range, km: high-altitude 3,530 low-altitude 1,340 Take-off run, m 450 Landing roll (with drogue chute), m 620 Max g-load 9.0 Powerplant 2 х AL-31F Crew 1

22 ROSOBORONEXPORT ment, arecording andmonitoringsystemallow- er-type, anIFFsystem,communicationsequip- tronic countermeasures equipment ofcontain- radar withhigh-precision navigationaids,elec- trol radar, anoptronic targeting/navigation no limitstoangleofattack. ing aerobatics atlow(uptozero) airspeedswith decreasing minimumflight speedandperform- incorporated intothecontrol loopfacilitates canard surfacesandmovablethrustvector operate withinanairgroup. ed andunguidedair-launchedweapons, ty, defeatground andsurfacetargetswithguid- Corporation. Itisdesignedtogainairsuperiori- tirole two-seatfighter manufactured bytheIrkut Equipment Mission aeofrn 550 17,300 Take-off run,m Service ceiling,km a -od 9.0 Crew 2 750 Max g-load Landing roll(withdroguechute),m 6.4 Flight range,km: 8,000 21.9 38,800 14.7 Max airspeed: Max combatpayload,kg Max take-offweight,kg Take-off weight,kg: Height ,m Wing span,m Length Basic specifications Advanced avionicssuiteincludesafire con- The Su-30МКisahighlymaneuverablemul- The fighter's integratedconfiguration with ihoerfeln 5,200 34,000 with onerefuelling 26,090 1.90 at highaltitude,Machnumber max normal ihattd / eulig3,000 1,350 high-altitude w/orefuelling at groundlevel,km/h ROSOBORONEXPORT (with theradarcross sectionof3m mode. Acquisitionrangeforafighter-type target while scanupto15airtargetsinautomatic assigned. ing thefighter toperformefficiently missions mation canalsobedisplayedontheindicator. map withassociatedoperational/tacticalinfor- weapon systemsoftheaircraft. Adigitalground consoles tomanagetheavionicssystemsand equipped withmultifunctionalcolourcontrol combat. Therear andfront cockpitsare fighter's effectiveness incloseairmanoeuvring nation tomissiles'IRseekers, greatly improves A helmet-mountedsight,supplyingtargetdesig- to 90kmandfind rangetothemup3.5km. ic locatorcandetecttargetsatadistanceofup classify upto10typesofairtargets.Theoptron- air spacescanning.Thefire control radarcan radar-contrast ground targetswhilecontinuing background. There isanoptionofattacking in free spaceand100kmagainsttheearth different types. built-in gunwithhighlyeffective ammunitionof 13 andS-25typesupto500-kgairbombs. vision/laser targetingsystem. be employedbythefighter fitted withathermal- seekers andKAB-1500LG corrected bombscan wide rangeofground andsurfacetargets. allows thefighter todefeatwithhighprecision a 1500Кr andКАB-500Кr(ОD)corrected bombs and commandguidancesystemsКАB- ed missileswithpassiveandactiveradar, TV Kh-29Т (ТЕ)high-precision air-to-surfaceguid- four targets. possibility ofsimultaneouslaunchesagainst siles providing hightargetkillprobability and ed missilesandR-73Eclose-rangeagilemis- RVV-AE andR-27medium-rangeair-to-airguid- unguided airbombsandrockets. surface guidedmissiles,corrected bombs, hardpoints andincludesair-to-airair-to- Armament The phasedarrayantennaradarcantrack The aircraft isfitted withthe30mmGSh-301 Unguided weaponsincluderockets ofS-8,S- The Kh-29Lmissileswithsemi-activelaser Employment oftheKh-31P, Kh-31А,Kh-59МE, The fighter canlaunchallmodifications ofthe The Su-30MKcombatloadiscarriedon12 Multirole Fighter Su-30MK 2 ) is120km

23 FIGHTERS AIRCRAFT Su-30MK2 Multirole Fighter

Mission

The Su-30MK2 is a highly manoeuverable multirole fighter. It is designed to destroy air and ground targets in all weather conditions with guided and unguided weapons, operating alone and as

AIRCRAFT part of an aircraft group in favour of gaining air superiority. The fighter's two-seat configuration enhances its combat effectiveness and helps pilots to master their piloting and combat FIGHTERS employment skills. designation and employment of missiles and air Equipment bombs in any weather, day and night. The high-performance ECM equipment is The Su-30MK2 is equipped with the surveil- installed on fighter to destroy the hostile radars lance/targeting (radar and optronic) systems by anti-radiation missiles . The navigation sys- that provide engagement of air and ground (sur- tem provides high-accuracy navigation in all face) targets, day and night, under fair and stages of flight. The cockpit instrumentation adverse weather conditions. The built-in laser facilitates the pilot to operate effectively using a range-finder ensures efficient employment of combination of the large-size colour LC multi- high-precision weapons. functional displays. The in-flight refuelling sys- The radar mapping of ground (water) surface tem enables to increase the fighter's flight and target tracking provide pre-launch target endurance/combat radius, restricted by physical ability of a pilot.

Basic specifications Armament Length 21.9 Wing span, m 14.7 The Su-30MK2 combat load is carried on ten Height , m 6.4 external hardpoints and includes R-27 air-to-air Take-off weigh, kg missiles of all modifications, R-73E and RVV-AE normal 24,900 AAMs, as well as Kh-35E, Kh-59MK, Kh-59ME, max 34,500 Kh-31A, Kh-31P, Kh-29T (TE, L) air-to-surface Max combat load, kg 8,000 missiles, and KAB-1500Kr and KAB-500Kr Max airspeed: guided bombs. ground-level, km/h 1,400 The unguided weapons include S-8, S-13 and high-level, Mach number 2.00 S-25 rockets and up to 500-kg calibre air Service ceiling, km 17,300 bombs. Flight range, km: The aircraft carries one built-in GSh-301 gun high-altitude 3,000 with 150 rounds of ammunition. low-altitude 1,270 Take-off run, m 550 Landing roll (with drogue chute), m 750 Max g-load 9.0 Powerplant 2 x AL-31F Crew 2

24 ROSOBORONEXPORT km againstairtargetswithRCS=3m date multi-channellongrangeradar(upto400 ing airsuperiority. and aspartofanaircraft group infavourofgain- ed andunguidedweaponsoperatingalone air andground targetsinallweatherwithguid- seat multirole fighter. Itisdesignedtodestroy 'air-to-surface' modes,aswell as welljointoperationbothin'air-to-air'and ing highresolution inthe'air-to-surface'mode, Equipment Mission The Su-35avionicssuiteincludes:anup-to- The Su-35isasupermaneuverablesingle- high-accuracy navigationsystem highly integratedavionicswithoverallcon- in-flight refuelling system,increasing flight multi-channel (againstairandground tar- range HOTAS controls, andwithimplementationof mal representation ofdisplayed dataand location system gets) highlysensitiveandjam-proof optical pilot system providing intelligentsupporttothe trol from openarchitecture datacontrol cockpit datamanagementfield withopti- ROSOBORONEXPORT 2 ), provid- with 150rounds ofammunition bombs. S-25 rockets andupto500-kgcalibre air 1500Kr(LG) andKAB-500Kr(OD)guidedbombs. Kh-31A, Kh-31P, Kh-29T(TE,L),aswellKAB- ASMs; long-rangeanti-shipmissiles;Kh-59MK, 27EP1, R-73EandRVV-AEAAMs;long-range 27R1, R-27ER1,R-27T1,R-27ET1,R-27P1,R- weapons, installedon12hardpoints include:R- a -od 9.0 2x117С 400to450 18,000 650to700 Crew 1 Powerplant 5.9 Max g-load 8,000 Landing roll(withdroguechute),m 21.9 Take-off run,m 15.3 Flight range,км: Service ceiling,km Max airspeed: Max combatload,kg Take-off weight,kg Height, m Wing span,m Length Basic specifications The aircraft alsohasabuilt-inGSh-301gun The unguidedweaponsincludeS-8S-13and ihattd 3,600 34,500 1,400 2.25 low-altitude 1,580 high-altitude high-level, Machnumber ground-level, km/h max normal 25,300 of guidancemode. weapons withdifferent types medium- andlongrange close-air combat,short-, comprising awiderangeof impressive armamentsuite Armament the Su-35itsfullcapability. manoeuvrability andgiving aircraft unsurpassed engines boastingthe thrust vector-controlled The Su-35organic The fighter carriesan Multirole Fighter Su-35

25 FIGHTERS AIRCRAFT Su-33 Shipborne Fighter AIRCRAFT FIGHTERS

Mission cial airborne communications and navigation equipment that ensures above-water flights and The Su-33 aircraft is designed to protect air- arrested landings. The aircraft takes off from aircraft carrier forces and warships against air craft carrier’s ramp, and lands using the arresting attacks by rotary- and fixed-wing aircraft, UAVs, hook. Its outer wing and horizontal stabiliser pan- and cruise missiles, as well as to engage sur- els are folding. The K-36 ejection seat with face targets with guided and unguided increased inclination ensures automatic low-alti- weapons. The aircraft is capable of self-sus- tude ejection in emergency situations. tained and group operations by day and night, in any weather, over international and enemy Equipment water areas. The Su-33 is also capable of providing support for naval aviation operations, The aircraft’s weapons control system fea- conducting air reconnaissance, and carrying tures a pulse Doppler radar operating in track- out buddy refuelling. while-scan and search-and-track modes The Su-33 has canards, modified high-lift wing against the earth/sea-surface background. The devices, in-flight refuelling equipment, and spe- Su-33 carries an optronic target acquisition system with a helmet-mounted target designator, a quadruple-redundant fly-by-wire system, Basic specifications and an automatic angle-of-attack/g-load limit- Length (with airspeed boom), m 21.185 ing system. Wing span, m 14.70 Height, m 5.72 Armament Take-off weight, kg: normal 25,000 The Su-33 weaponry is carried on 12 external maximum 33,000 hardpoints, and includes R-27R1(ER1), R- Max combat load, kg 6,500 27T1(ET1) and R-73E air-to-air missiles, rock- Max high-level air speed, km/h 2,300 ets, and guided bombs of up to 500kg calibre. Service ceiling, m 17,000 Fitted with a ventral UPAZ flight refuelling sys- High-level service range, km 3,000 tem, the aircraft will be able to transfer up to Max g-load 8.0 6,000 kg of fuel to other fighters in mid-air. The Powerplant 2 x Al-31F 3rd series Su-33 carries one built-in GSh-301 gun with afterburning turbofans 150 rounds of ammunition. Crew 1

26 ROSOBORONEXPORT stability andcontrollability parameters tothose ty systemandallowstheinstructortoadjust system, whichfunctionsasanactiveflight safe- tional characteristicsare concerned. far asitstechnicalspecifications andopera- integration intodifferent nationalairforces, as warplanes. F-15, F-16,Eurofighter Typhoon, F-22,andF-35 MiG-29 familyaircraft, aswellMirage2000, generation jetfighter, includingtheSu-30and sufficient pilottrainingtofly anyfourth-orfifth- capacities. ware allowingfurtherbuild-upofthesystem’s combined bycommonopen-architecture soft- management system.Allthesecomponentsare lators, abasictrainingaircraft, andatraining which comprisesground trainingassets,simu- ponents oftheintegratedflight trainingsystem, aircraft. ers inmanoeuvre units,and asalightcombat cadets, forretraining pilotstofly combatfight- advanced trainingofmilitaryflight school Equipment Mission The Yak-130 isfitted withadigitalfly-by-wire The Yak-130 isdesignedforbasicand The Yak-130’s highversatility facilitatesits The Yak-130 traineriscapableofproviding The Yak-130 trainerisoneofthemajorcom- ROSOBORONEXPORT bat capabilities. probe considerablyenhancingtheaircraft com- ECM) pods.Itisequippedwiththerefuelling cialised (weaponguidance,reconnaissance, rockets, bombs,externalfueltanks,andspe- such asair-to-airandair-to-surfacemissiles, are usedforcarryingupto3,000kgofpayload Armament oepat 2xAI-222-25 +8/-3 up to 40 180 195 Crew 2 1,060 Powerplant 4.76 3,000 Landing speed(trainerversion),km/h Take-off speed(trainerversion),km/h 9.72 Flight attackangles,deg 11.493 Operational g-load 2,000 Service combatradius,km: Service range,withoutexternalfueltanks,km Max airspeed,km/h Max combatload,kg Take-off weight,kg: Height, m Wing span,m Length, m Basic specifications Eight underwingpylonsandoneventralpylon ihetra ultns 915 525 5,700 with externalfueltanks without externalfueltanks normal, trainerversion max 9,000 mountainous areas. bat efficiency, especiallyin demonstrating increased com- standoff pinpointstrikes RPV, theYak-130 candeliver used jointlywiththePchela an electro-optical station.If grated OsaorKopyoradar, or tion aircraft. layout tothoseoffifth-genera- plays completelyidenticalin equipped withelectronic dis- The aircraft cockpitsare of theaircraft beingsimulated. The aircraft cancarryaninte- Combat Trainer Yak-130 or DV-2Sturbofans

27 COMBAT TRAINERS AIRCRAFT MiG-AT Combat Trainer AIRCRAFT

Mission Equipment

The MiG-АТ aircraft is a classic configuration The aircraft is equipped with integrated fly-by- monoplane with a low mid-wing, two-seat tan- wire control system with digital and analogue COMBAT TRAINERS COMBAT dem cockpit and two bypass turbojet engines. parts redundancy. It provides required charac- The aircraft’s aerodynamic layout and param- teristics of stability and controllability, automat- eters allow it to perform flights practically in all ic limitation of angle of attack; engine thrust subsonic flight modes characteristic of modern control, pre-selected radio altitude hold, spin and prospective combat aircraft. recovery and bringing of the aircraft to straight Two Larzac 04R20 engines provide high and level flight. steady-maneuvering loads, takeoff characteris- The MiG-AT combat trainer ensures effective tics and rate of climb. high-quality preparation of flight personnel within the short time thanks to its design simplicity, high reliability of its airframe, power plant and systems, long service life and low-cost life Basic specifications cycle, high maintainability, and excellent flight Weight, kg: characteristics. normal/max take-off 5,210/8,150 An interactive training system and simulators max fuel are offered for on-ground formation of flying and in internal tanks 1,680 technical personnel. in external tanks 2 х 470 Powerplant 2 х Larzac 04R20 Take-off thrust (ISA), kgf 2 х 1,440 Airspeed, km/h: max level speed 850 take-off (with full fuel load) 183 landing 175 Max flight altitude, m 14,000 Max flight range, km 2,000 Operational g-load +8/-3 Service life, flying hrs 15,000 Dimensions: length 12.01 wing span 10.16 height 4.01

28 ROSOBORONEXPORT ther build-upofadditionalequipment,including Modular designoftheASWsystemenablesfur- system andelectronic reconnaissance system. computer system,IRandtelevisionimaging netic anomalydetectionequipment,managing avionics suiteincludesradar, sonobuoys,mag- well asplantingoflinearminebarriers. The rine detection,trackingandengagement,as off range.ItsASWcapabilities includesubma- engaging enemysurfacevesselsfrom astand- vival equipment.TheIL-114MPiscapableof onboard detectionsystems,andairdrops sur- locates missingpersons withthehelpof crew SAR operationsinemergencycases.The and surfacevessels.Itcanalsobeemployedin electronic reconnaissance data onunderwater and surfacetargets.TheIL-114MPgathers tion, trackinganddestructionofunderwater water zones,andprovides detection,identifica- designed foraerialpatrolling inlittoralandblue state border/economic area trespassing and their movementparameters; reveals casesof vessels, identifies andlocatesthem,determines environmental monitoring. and seacoast,aswellairpollutioncontrol and ial patrolling ofexclusiveeconomiczones,ports The IL-114MPmulti-purposepatrol aircraft is The IL-114Ppatrol aircraft isdesignedforaer- The IL-114Psearches foranddetectssurface ROSOBORONEXPORT ment containers. loudspeaker pods,gunpod,andsurvivalequip- tography system. ment, andenvironmental monitoringandpho- nication andautomaticdatatransmissionequip- computer system,recording equipment,commu- meeting theMIL-STD-1553Bstandard. installation ofanyequipmentorsubsystems rw22 2-4 2 2-4 1,000 1,300 2x AI-20D 2xTV7-117 * -atarangeof370km 500 Operators 800 9.186 Crew 30.00 500-8,000 29.654 350-400 Powerplant 9.186 100-8,000 Landing roll,m 30,000 Take-off run,m 350-400 27.40 30.00 Patrol durationatarange 26,000 Patrol altitude,m Patrol speed,km/h Max take-offweight,kg Height, m Wing span,m Length, m Basic specifications External equipmentincludessearchlight and fu o30k,hs81 9-12* 8-12 of upto300km,hrs Multi-Purpose PatrolAircraft evision imagingsystems,managing includes surveillanceradar, IRand tel- "on-condition" maintenancescheme. systems are operatedaccording tothe variety ofclimates.Theaircraft andits weather conditions,dayandnight,ina autonomous operationinadverse casualties, andcargotransportation. for search, rescue andevacuationof passers. Theaircraft canalsobeused provides targetdesignationoftres- The onboard electronic equipment The IL-114Piscapableof IL-114MP Patrol Aircraft ubposturboprops turboprops IL-114P L14 IL-114MP IL-114P eis2series5 series 2

29 MARITIME PATROL AIRCRAFT AIRCRAFT IL-76MD/IL-76MF Medium-Range Military Transport Aircraft

Mission

The IL-76MD/IL- 76MF aircraft are designed to airdrop troops, transport ground forces and materiel (including

AIRCRAFT medium-weight tanks) with crews, deliver urgent cargos to troops, and transport casualties.

Variants been rearranged to enable flights without the The IL-76MD is capable of airlanding combat radio operator. The crew has been cut down to materiel (with crews), cargoes, or fuel in special four people - two pilots, navigator, and flight tanks in the pressurised cargo hold. The twin- engineer. deck version of the aircraft is capable of accom- The aircraft avionics ensure airdropping by modating 225 personnel (145 people - without day and night, in good and adverse weather, in the second deck). hostile air defence environment. The avionics Its medevac modification can evacuate 114 include navigation/targeting system, long- casualties. range navigation system, satellite navigation MILITARY TRANSPORT AIRCRAFT MILITARY The IL-76MF is a derivative of the IL-76MD, system (on customer request), radio communi- with a new engine control system. The commu- cations equipment, mid-air collision avoidance nications instrument panels and controls have system, and flight data recorder. The aircraft can carry four UAK-10 or nine UAK-5 aircraft containers, or four UUK-20 Basic specifications ground/sea containers. IL-76MD IL-76MF Length, m 46.60 53.19 The IL-76MF is capable of transporting up to Wing span, m 50.50 50.50 305 persons (in the twin-deck version), or 150 Parked height, m 14.42 14.42 casualties, or military hardware with crews, or Cargo hold dimensions, m: fuel in special containers, as well as airdropping length 25.54 31.14 troops (186 persons), materiel and cargoes. height 3.40 3.40 Both aircraft can be operated from soil air- width at floor 3.45 3.45 fields, and are superior to foreign counterparts in Max take-off weight, kg 190,000 210,000 terms of cargo hold volume and autonomous Max payload, kg 47,000 60,000 operation capability. Cruising air speed, km/h 780-800 780-800 Cruising altitude, m 9,000-12,000 9,000-12,000 Service range, km: with max payload 4,200 4,200 with 40,000 kg 7,200* 5,400 Take-off run, m 1,700 1,800 Landing roll, m 1,000 990 Powerplant 4 x D-30KP-2 4 x PS-90A turbofans turbofans Crew 6 4 * - with 20,000 kg

30 ROSOBORONEXPORT station withrefuelling podcontrols isarranged. station intherear fuselagearefuelling operator elling systemadaptedtoforeign aircraft. The aircraft canbefitted withanupgradedrefu- on aspecialportsidepylonintherear fuselage. wingtips. ThePAZ-1M refuelling podiscarried two standard UPAZ refuelling podsatthe 45,928 litres are mountedin thefuselage,and removable fueltankswithatotalcapacityof in-flight andground refuelling. Two auxiliary people orupto48tonnesofcargo. a transportversion capableofairlifting upto70 elling pods,theIL-78MKcanbeconvertedinto craft from thewingtiprefuelling pods. rear fuselagerefuelling pod,ortwotacticalair- 78MK canrefuel oneheavyaircraft from the km, andupto30,000kgat3,500km.TheIL- 74,000 kgoffuelatarefuelling rangeof1,000 elling ranges.Itiscapableoftransferringupto craft providing increased fueltransferatrefu- visual approach andcontact. elling canbecarriedoutbydayandnightwith for ground refuelling oftacticalaircraft. Airrefu- refuelling oftacticalandheavyaircraft, andalso Equipment Mission The IL-78MKmountsspecialequipmentfor The IL-78MKflying tankerisdesignedforair In placeofthestandard pressurized gunner By removing thefuselagefueltanksandrefu- The IL-78MKisaderivativeoftheIL-78air- ROSOBORONEXPORT Convertible FlightRefuellingTanker and therefuelling podmaintenancesuite. pylons, containers withground refuelling hoses, underwingandfuselage elling podstothe craft, auxiliaryequipmentforhoistingtherefu- IL-76MDair- organic ground equipmentofthe er ag,k 9,500 4xD-30KP-2turbofans 2,200 440-600 8,000-11,000 2,000-9,000 750-840 Crew 7 Powerplant 74,000 Take-off run(maxtake-offweight),m Ferry range,km Refueling altituderange,m Refueling airspeed,km/h Cruising altitude,m 46.60 50.50 Cruising airspeed,km/h 14.76 Max transferredfuelweight,kg Max landingweight,kg: Max take-offweight,kg: Parked height,m Wing span,m Length, m Basic specifications Max payload,kg: The aircraft ismaintainedwiththeuseof oceerna 155,000 concrete runway olaril 33,000 43,000 138,000 157,500 210,000 soil airfield concrete runway soil airfield soil airfield concrete runway IL-78MK

31 FLIGHT TANKERS AIRCRAFT IL-76P Fire-Fighting Aircraft AIRCRAFT

Mission One IL-76P employed intermittently for three

FIRE-FIGHTING AIRCRAFT The IL-76P is designed to fight fires by dump- to four hours against a strong ground-level for- ing extinguishing liquids on fire areas. est fire on an area of 50 hectares can reduce The liquids dispenser can be mounted on any firefront expansion rate by two to three times. Il-76 transport without its extra retrofitting. The most efficient technique consists in employing two to three IL-76P aircraft in turns Equipment to deliver the OS-5 extinguishing liquid. Fire- fighting operations can be started by new line Two VAP-2 tanks contain 42,000 litres of water unit crews after only a short training course. or special extinguishing liquids. The tanks are attached to the cargo hold floor by the organic mooring chains. A four-person team can load and Basic specifications moor one tank within 1.5 to 2 hours. It takes 10- Water dispersing speed, km/h 260-400 12 minutes to fill the VAP tanks with the extin- Water dispersing altitude, m 50-100 3 guishing liquid. VAP tanks total capacity, m 40,000 Covered zone length, m with the extinguishant density The aircraft is capable of dumping on the ground of over 2 L/m2 450-900 40,000 litres of water from an altitude of 50 m in four seconds. Dumped consecutively or simultaneously from two tanks at the airspeed of 280 km/h and the altitude of 80 m, water covers an area of 600x80 m with the density exceeding five litres per square metre in the centre and gradual- ly decreasing towards the periphery. In about eight seconds all water can be dumped from both tanks.

32 ROSOBORONEXPORT also available. gas/oil fields. Customisedaircraft versions are shift teamsatgeologicalexpeditionsitesand patrol, andreconnaissance missions, anddeliver goes, equipment,andpassengers, carryoutSAR, Mission riigattd,m1,0 10,800 10,000 10,800 36,500 650-700 10,000 Service range,km: 34,800 650-700 8.65 Cruising altitude,m 31.89 Cruising airspeed,km/h Max payload,kg Take-off weight,kg 8.65 31.89 Cargo holdsize,m: Parked height,m Wing span,m Basic specifications oepat2xD-36turbofans Powerplant egh 80828.068 28.068 Length, m rw242-4 Crew 2-4 The An-74aircraft isdesignedtotransportcar- ihmxpyod2001,500 2,000 with maxpayload 10.50 10.50 length withramp ihfl ultns4504,800 4,500 2.20 2.15 with fullfueltanks 2.20 2.15 width atfloor height ROSOBORONEXPORT n7T20An-74TK-200 An-74TK-100 An-74T-200 An-74T-100 eis3 series2A series 3A allow forall-weather, day-and-night operation. navigation andradiocommunicationssystems mountainous runways.Theintegratedflight landings atsteepanglesonsubstandard Equipment Multi-Purpose Transport Aircraft A largecargohatchmeetssizerequirements of The aircraft canperformshorttake-offs and ramp reduces loading/unloadingtime. towed machinery. Aslidingcargohatch modates easilyself-propelled and ers, onpallets,andinbulk,accom- most cargoestransportedincontain- accommodate alight-weightvehicle. tive aircraft. Itssecondcargoholdcan ports. sons), andpassenger/cargotrans- 200 are cargo,passenger(52per- payload capacities. are transportversions withenhanced The An-74-200Disanadministra- The An-74TK-100andAn-74TK- The An-74T-100andAn-74T-200 An-74

33 MULTI-PURPOSE TRANSPORT AIRCRAFT AIRCRAFT An-38 Multi-Purpose Transport Aircraft AIRCRAFT

Mission personnel and cargo airdrops, maritime reconnaissance, and medical evacuation. The An-38 transport aircraft is designed to transport passengers and cargoes (in contain- Equipment ers too) on local routes. The An-38 can also be employed for aerial photography, geological sur- Different versions may have different passen- veys, patrol missions, fire-fighting operations, ger/cargo combinations. Cargoes up to nine meters long can be loaded through the rear MULTI-PURPOSE TRANSPORT AIRCRAFT MULTI-PURPOSE cargo hatch. Basic specifications Length, m 15.67 The An-38 can be operated from short Wing span, m 22.063 unpaved and ice/snow-covered runways, from Parked height, m 5.050 mountainous airfields situated at up to 2,600 m Cargo hold dimensions, m: above the sea level, and is operational within length 9.00 the ambient temperature range of -50o to height 1.60 +45oC. width at floor 1.55 Max take-off weight, kg 9,500 The integrated flight navigation system enables Max payload, kg 2,500 all-weather, day-and-night operation. Cruising speed, km/h 340-380 Cruising altitude, m 3,000-4,200 The aircraft is maintained on condition, with- Range (H=3,000 m, ISA), km: out overhauls throughout the entire service life. with max payload 990 with max fuel load 1,790 The An-38 is certificated in compliance with Runway length required, m 895 the Russian AP-25 flight standards. Powerplant 2 TPE-331-14GR- The An-38-100 version is powered by the TPE 801E turboprops 331-14GR-801E. Crew 2 Passenger seats 27

34 ROSOBORONEXPORT loading/unloading. rampintherear fuselagefacilitatescargo The passenger andfreight transportation. training, andairmobilemissions. ping andaerialphotography, patrol/transport, ical evacuation,environment monitoring,map- night, infairandadverse weatherconditions. can operateinanygeographicarea bydayand aircraft goes inthepressurised cargohold.The is designedtotransportpassengers andcar- Mission The Su-80GPmulti-purposetransportaircraft The Su-80GPfeatures highcost/efficiency of The Su-80GPcanalsobeemployedformed- ROSOBORONEXPORT ground airtemperatures ranging from -50 equipped airfields andsoilrunways,inthenear- for 50flight hours, orfor15days,from non- data oncolourLCDs. systems andequipment,presentation of control andnavigation,monitoringofaircraft Equipment +45 asne et 30 2xCT7-9B 840 Passenger seats 7,600 Crew 2 460 Powerplant 3,300 Landing roll(withthrustreversal),m 5.52 Take-off run,m 18.26 23.17 470 14,000 Range, km: Max altitude,m Max cruisingairspeed,km/h Max payload,kg Max take-offweight,kg Parked height,m Wing span,m Length, m Basic specifications Multi-Purpose Transport Aircraft The Su-80GPcanbeoperatedautonomously The integratedavionicssuiteprovides flight ih190k ala 2,450 1,400 with 1,950-kgpayload with 30passengers o C. Su-80GP turboprops o C to

35 MULTI-PURPOSE TRANSPORT AIRCRAFT AIRCRAFT An-3T Multi-Purpose Transport Aircraft

Basic specifications Length, m 14.029 Wing span, m 18.176 Parked height, m 5.00 Cargo hold dimensions, m: length 4.20 The An-3T aircraft is designed to transport pas- height 1.85 sengers and cargoes on local routes. A derivative of width at floor 1.65 the An-2 aircraft, it can be realised in transport, Max take-off weight, kg 5,800 AIRCRAFT convertible cargo/passenger, agricultural, fire- Max payload, kg 1,800 fighting, airmobile, and medevac versions. Cruising air speed, km/h 220-255 The turboprop engine of the aircraft provides Service ceiling, m 4,400 increased payload capacity, and outstanding Cruising altitude, m 2,000 take-off/landing characteristics. The aircraft Service range with 1,500 kg, km 550 features modern flight navigation and electric Runway length required, m 500 equipment, central warning system, and air con- Airfield altitude ditioning/heating system for the cockpit and above sea level, m up to 2,000 cargo hold. Powerplant 1 x TVD-20-03 turboprop The An-3 is certificated in compliance with Crew 2 the Russian AP-23 flight standards. Passenger seats 12 Be-103 Multi-Purpose Amphibian

The Be-103 light amphibious aircraft is designed for passenger and cargo transportation; medical evacuation; fire prevention, sur- MULTI-PURPOSE TRANSPORT AIRCRAFT MULTI-PURPOSE veillance, and maritime environmental monitor-

Basic specifications Length, m 10.65 ing operations; recreational flights; and agricul- Wing span, m 12.72 tural applications. Height, m 3.757 The Be-103’s amphibious capability allow it Cargo hold dimensions, m: to operate in areas with sufficient water surface length 3.65 (rivers, lakes) and remote regions where runway height 1.23 construction is either impossible or economi- width 1.25 cally unfeasible. Take-off weight, kg 2,270 Certificated in compliance with the AP-23 Payload, kg 385 requirements, the Be-103 also got the ICAO cer- Max air cruising speed, km/h 260 tificate in Dec. 2001. Service ceiling, m up to 3,000 The aircraft is fitted with integrated flight nav- Max range, km 1,250 igation and communications systems enabling Take-off run (water/surface), m 440/310 operation in adverse weather conditions, by day Landing roll (water/surface), m 320/240 and night. On customer request the aircraft can Wave height, m up to 0.5 be fitted with autopilot, satellite navigation sys- Powerplant 2 x TCM-IO-360ES tem, and weather radar. All versions can be piston engines equipped with a copilot (instructor) flight control Crew 1 station. Passenger seats 5

36 ROSOBORONEXPORT natural disasters. Thisversion isfitted withmar- tion ofcasualtiesinareas ofman-madeand al andinstrumentalsearch, rescue andevacua- face. in operationstoremove oilfilm from watersur- extinguish shipfires, anddisperse oilabsorbers can alsobeemployedtoputoutburningfuel, trees orhills. scooping/dumping nearobstacles,suchas fighting inmountainousterrainandwater rate isamostvaluablecharacteristicforfire- the fire zonewithoutrefuelling. Itshighclimb capable ofdeliveringupto270tonswater field-to-reservoir rangeof10km,theBe-200is an airfield-to-fire rangeof100kmandanair- one byinacrew-selected sequence.Given tanks. Thetanksare emptiedsimultaneously, or to dumpwateronfire sitesfrom theonboard deep. and internalwaterstripsatleasttwometres any season.Theaircraft canbeflown from sea day andnight,inanyweatherconditions, communications systemsenableoperationsby cargoes, tocarryoutSARoperations. to fight forest fires, totransportpassengers and Variants Equipment Mission The Be-200fire-fighting version isdesigned The aircraft’s integratedflight navigationand The Be-200amphibiousarcraft isdesigned The Be-200SARversion isdesignedforvisu- If fitted withspecialdispersers, theBe-200 ROSOBORONEXPORT 24 passengers. administrativeversion cantransport18to The sengers andupto3,000kgofcargo. capable ofsimultaneouslytransporting19pas- 64 passengers. tion, theaircraft iscapableoftransporting32to Depending onthepassengercabinconfigura- craft intoapassengerversion withinonehour. standard pallets.Thecrew can converttheair- aehih,mupto1.2 turbofans 2xD-436TP 14 Crew 2 Powerplant 3,600 Water intaketimewhengliding,sec Wave height,m 8,000 Landing roll,m: 710 Take-off run,m: Max range,km 43,000 Service ceiling,m Max cruisingairspeed,km/h 8.90 31.43 32.78 Tank capacity,cu.m: Max take-offweight,kg Cargo holddimensions,m: Parked height,m Wing span,m Length, m Basic specifications The Be-200passenger/cargoversion is e tt 3 950 1,300 700 1,000 1.50 12.00 Sea State surface water 2.60 surface 1.90 water 17.00 chemicals water width atfloor height length for transportingcargoesinbulkoron ted withallthenecessaryequipment tonnes ofcargo.Thecargoholdisfit- capable oftransportingupto7.5 stretcher casualties. to 60seatedcasualties,orup30 porting upto50rescue troops, orup ment. Theaircraft iscapableoftrans- itime search andsurveillanceequip- Multi-Purpose Amphibian The Be-200transportversion is Be-200

37 MULTI-PURPOSE AMPHIBIANS AIRCRAFT M-55 GEOFIZIKA High-Altitude Aircraft AIRCRAFT

Mission The M-55 can fly six-hour-plus high-altitude

RESEARCH AIRCRAFT missions with a 1,500-2,000kg equipment pay- The M-55 Geofizika high-altitude aircraft is load used for direct measurements and analy- designed for stratosphere research (at altitudes sis of the ambient environment, as well as for of up to 20 km), surveillance, and radio com- remote chemical and microphysics research at munications missions. a range of several kilometres. Within one hour The M-55 can perform the following monitor- the aircraft can monitor at least 100,000 ing missions: atmospheric control, including sq.km. vapour and aerosol contamination studies; The M-55’s unique altitude characteristics water area control, including surface monitor- and excellent lifting capacity make it a valuable ing, fishery supervision, and waterway naviga- asset for high atmospheric research. Its two tion control, including detailed mapping and engines provide enhanced flight safety: with evaluation of damage caused by catastrophes one engine failed the M-55 can continue flight and natural disasters, by day and night, in con- at an altitude of 12-14 km and safely land at ditions of poor visibility; support of search-and- home base. The M-55 can be operated from air- rescue operations, harvest forecasting, and fields situated at up to 4,000 m above the sea aerial monitoring of construction sites. level, in ambient temperatures of -40 to +60oC.

Equipment Basic specifications Length, m 22.868 The M-55 is a versatile high-altitude air plat- Wing span, m 37.464 form with a wide mission scope. Parked height, m 4.83 The overall volume of its equipment compart- Max take-off weight, kg 24,500 ment equals 11 cu.m. Optional external con- Payload, kg up to 2,200 tainers can house extra 1.2 cu.m of equipment. Cruising air speed, km/h 750 The aircraft’s baseline design and the capa- Service ceiling, m 20,500 bilities of its systems and power plant ensure Patrol endurance, hrs 6.0 normal operation of radar, optical, and radio Take-off run, m 970 relay equipment sets. Landing roll, m 820 Powerplant 2 x D-30V12 turbofans Crew 1

38 ROSOBORONEXPORT system. satellite communicationssystemandavideo seat sofas.Theconference hallisfitted witha armchairs, aconference table, andtwoseven- lounge isadjacenttoapersonal bathroom. a bed,foldingdesk,andwardrobe. The chair, atwo-seatsofathatcanbeconvertedinto aides compartment. conference hall,first classcompartment,and VIP passengercabincomprisinglounge, unavailable fortheground analoguesofsuch bat readiness oftroops control networksare ('Selena-АМE' code). radio-relay andcommunicationsequipment radio-relay station. can operatebothasacommandpostand when ground communicationisdisrupted.It reliable anduninterruptedcommunication and radio-relay aircraft isdesignedtoensure The Yak-42D administrativeaircraft hasa The IL-22-M11RTairbornecommandpost The conference hallhasfourmovableswivel The VIPloungeisfitted withaswivelarm- Its range,mobilityandcharacteristicsofcom- The aircraft isequippedwiththe83т035АМ ROSOBORONEXPORT Airborne CommandPostandRadio-RelayAircraft cate. direction' principle. information ona'from anydirection-to-any and againstfalsified dataentry. Itcanrelay using equipmentforcryptographicprotection ubro ai-ea hnes9 19 Number ofradio-relaychannels Number ofcommunicationchannels Basic specifications evc ag,k 5,585 2,200 36.38 34.88 9,600 810 57.5 * -ISA,+35 1,920 Max airfieldaltitudeabovesealevel,m Runway lengthrequired,m Service range,km Max cruisingaltitude,m Cruising airspeed,km/h Max take-offweight,t Wing span,m Length, m Basic specifications Crew ieo lgt r morethan9 Time offlight,hrs The aircraft hasacorresponding flight certifi- ehia ru 4 technical group prtoa ru 6 operational group communications systems. integrated flight navigationandradio be fitted withRussian-orforeign-made kitchen appliances.TheVIPversion can dates 18businessclassseats. the aisle. four twinseatsandtwofoldingtablesin o VIP AdministrativeAircraft The aircraft isadditionallyfitted with The aidescompartmentaccommo- The first class compartmentfeatures C IL-22-M11RT and DMWchannels, radio-relay, MW, DM munication linksvia radio-relay andcom- conflicts. pared conditionsofwar dynamic andunpre- very importantunder systems andthisis The aircraft provides Yak-42D *

39 SPECIAL-PURPOSE AIRCRAFT AIRCRAFT Tu-214 Business Aircraft

The Tu-214 mid- range passenger aircraft is designed to carry passengers, luggage and cargo on domestic and international trunk routes to a distance of up to 7,200 craft completely meets ICAO noise and emis-

AIRCRAFT km. The aircraft can accommodate up to 210 passengers. sion requirements. The Tu-214 features improved aerodynamic On customer request the aircraft can be pow- characteristics, low fuel consumption, reason- ered by the Rolls-Royce engines and fitted with able operating costs and lower physiological Honeywell, Allied Signal or Litton avionics. workload on the crew. The airplane's high aero- Basic specifications dynamic efficiency ensures impressive and safe Length, m 46.16 cruising flight and landing at low speeds. The Wing span, m 41.8 automatic flight control and navigation system Max take-off weight, t 110.75 provides accurate aircraft navigation along the Cruising air speed, km/h 850

BUSINESS AIRCRAFT entire envelope of assigned flight paths. The Max cruising altitude, m 12,600 improved comfort level of the cabin helps the Max service range, km 7,200 passengers to withstand long flights. The air- Powerplant 2 x PS-90A turbofans

IL-96-300 Business Aircraft

The IL-96-300 long- range wide-body airliner is designed to carry passengers, luggage and cargo on domestic and international trunk routes to a distance of up to 13,500 km. The aircraft has a maximum take-off weight of 250 tonnes, and can producers. The cabin interior improvements accommodate up to 289 passengers or almost provide maximum comfort and fully meet inter- 40 tonnes of commercial payload, with fuel con- national requirements for VIP cabins. sumption up to 7.3 tonnes per flight hour. The IL-96-300 features advanced digital Basic specifications avionics, inertial navigation system and satel- Length, m 55.35 lite navigation tools, as well as fly-by-wire con- Wing span, m 60.105 trols. The airliner is able to perform landings in Max take-off weight, t 240 weather conditions of ICAO IIIA category. Cruising air speed, km/h 850 The IL-96-300 VIP-version's interior is made Max cruising altitude, m 12,000 on the basis of original design concepts with the Service range, km 10,000 use of certified materials supplied by leading Powerplant 4 x PS-90A turbofans

40 ROSOBORONEXPORT AEROSPACE SYSTEMS HELICOPTERS

ROSOBORONEXPORT 41 Mi-35/Mi-35P Combat Transport Helicopters HELICOPTERS

Mission Equipment COMBAT HELICOPTERS COMBAT The Mi-35/Mi-35P helicopters are designed The helicopter’s avionics and instruments to provide close air support to ground troops, enable all-weather, day/night operations in any engage small-size armoured and unarmoured climate. ground and sea targets, escort troops on the march, airlift and provide close air support to Armament airborne and special operations teams, and carry out medevac, reconnaissance and other The Mi-35s can carry up to eight operations. Ataka/Shturm ATGMs, up to 128 S-5 rockets in The helicopters can airlift eight air assault UB-32 pods, up to 80 the S-8 rockets in B8V20- troops with side arms, or four casualties plus A pods, up to four S-24 rockets, UPK-23-250 one medical attendant, or 1,500kg cargo in the gun pods, pods with grenade launchers or cargo compartment, or 2,400 kg on a sling. machine guns, 50 to 500kg bombs, two KMGU- 2 small-size cargo containers, and incendiary Basic specifications tanks weighing up to 500 kg. Take-off weight, kg: The gun armament comprises one USPU-24 normal 11,200 swivelling cannon turret with one four-barrel maximum 11,500 YakB-12.7 machine gun (Mi-35) or one NPU-30 Payload, kg: gun mount with the twin-barrel 30mm GSh-30 normal (cargo compartment) 1,500 cannon and 250 rounds of ammunition (Mi- maximum (underslung) 2,400 35P). Either combat version is equipped with a Air speed, km/h: self-defence and survivability enhancement maximum 320 system. cruising 280 Hovering ceiling, m 1,750 Service ceiling, m 4,500 Range, km 450 Ferry range, km 1,000 Powerplant 2 x TV3-117VMA turboshafts Crew 2

42 ROSOBORONEXPORT Mi-35M Upgraded Combat Transport Helicopter

computer, and jam-proof communications equipment. The upgraded avionics suite enables ground surveillance (with 20 to 25m standard deviation), round- the-clock low-altitude

flights with visual obser- HELICOPTERS vation of underlying terrain, take-offs from/ landings at unequipped sites, day/night reconnaissance with target location and designation, and attacks against Features ground and air targets in any combat environments. The Mi-35M upgraded helicopter features enhanced combat efficiency thanks to

Armament HELICOPTERS COMBAT improved flight performance, round-the-clock employment capability, and modernised The helicopter’s round-the-clock combat effi- weapons systems. ciency is enhanced thanks to installation of The upgraded helicopter is capable of carrying eight highly effective ATGMs, four Igla-V air-to- out a wider range of combat missions, including air missiles, up to 10 S-13 rockets, the GSh-23 air reconnaissance with real-time target location cannon with 450-round ammunition load, and and designation, by day and night, in all weather improved weapons control system, computer conditions. system, and software. The upgraded helicopter is fitted with new On customer request the helicopter moderni- main and tail rotors, a new swash plate assem- sation programme can be carried out in several bly, a shorter modernised wing with an integrat- stages. ed cargo lifting system, a non-retractable landing gear, increased-capacity external fuel tanks, Basic specifications and an upgraded power plant. These measures Take-off weight, kg: increase the helicopter's hovering ceiling up to normal 10,900 4,000 m and its service ceiling up to 5,700 m, maximum 11,500 enhance survivability and flight safety, and ren- Payload weight, kg: der maintenance much easier. normal 1,500 maximum (underslung) 2,400 Equipment Air speed, km/h: maximum 315 The Mi-35M is equipped with advanced cruising 260 avionics and night vision systems, including Hovering ceiling, m 4,000 night vision goggles, operated at night with sub- Service ceiling, m 5,700 dued cockpit instrument lighting; GOES-342 Range, km: electro-optical system with a laser range finder, without extra fuel tanks 415 GLONASS/NAVSTAR satellite navigation sys- with extra fuel tanks 1,085 tem, electronic multifunction displays, onboard Powerplant 2 x VK-2500 turboshafts Crew 2

ROSOBORONEXPORT 43 Mi-28NE Combat Helicopter HELICOPTERS

Mission system; and a flight mission data processing system. The Mi-28NE gunship is designed to engage The Mi-28NE is the world’s best helicopter in armoured and soft-skinned ground, sea and air terms of battlefield survivability. Its automated targets, provide close air support to ground control system restores proper engine operation troops, escort tactical airborne troops, conduct after firing-induced stalls, thus extending the COMBAT HELICOPTERS COMBAT air-to-air combat and air reconnaissance in all unguided weapons delivery range to cover the weather conditions, during stand-alone and entire combat altitude and airspeed envelope. group missions with automated target designation and distribution. Armament The Mi-28NE is capable of automated terrain- following at low and very low altitudes (10 to 25 m), The Mi-28NE armament includes up to 16 employing its radar and electro-optical surveil- Ataka-V ATGMs, up to eight Igla missiles, up to 80 lance and sighting systems. Excellent power-to- S-8 rockets in B8V20-A pods, up to 20 S-13 rock- weight ratio allows for operations in alpine terrain, ets in B13L1 pods, and up to four KMGU-2 small- at high ambient temperatures. The Mi-28NE is size cargo containers. The helicopter carries a capable of performing combat manoeuvres with built-in NPPU-28N swivelling gun mount with one vertical overload of up to 2.6 g, sideways and tail- 30mm 2A42 cannon (250-round ammunition first flights at a speed of up to 100km/h, and heli- load), and UPK-23-250 gun pods. copter aerobatics. Basic specifications Equipment Take-off weight, kg: normal 11,000 The integrated avionics suite includes a high- maximum 12,100 precision navigation system (comprising the iner- Air speed, km/h: tial, satellite, and geophysical orientation sys- maximum 305 tems); a stabilised sighting system with cruising 270 optical/IR/TV channels featuring video/radar Hovering ceiling, m 3,600 image quality improvement and synthesis sub- Service ceiling, m 5,700 systems; a thermal imaging system with a laser Range, km: rangefinder; a mast-mounted radar; helmet- mounted target designation and display systems; normal 450 an onboard computer; an electronic display sys- ferry 1,100 tem with MFDs; an automated data transfer sys- Powerplant 2 x TV3-117VMA turboshafts tem; a self-defence system; an automated control Crew 2

44 ROSOBORONEXPORT provided withanejectionseat. Ka-50pilotis round hits,andECMassets.The cockpit capableofwithstanding12.7mm is provided bytheinnovativedesign,armoured tion, andweaponsdelivery. weather, round-the-clock flight control, naviga- ing ambushes. and speed,canbeefficiently usedinhover- km/h, irrespective oftheground winddirection especially intheairspeed envelopeofupto100 The helicopterboastsexcellentcontrollability, advantage inhighlymanoeuvrabledogfights. urban terrain,andgivesthehelicopteraclear cient combatoperationinrugged,alpine,and performance enableseffi- for alongperiodoftime. tions from unprepared sites ducting autonomousopera- copter iscapableofcon- on thebattlefield. Theheli- air targets,andpersonnel moured materiel,low-speed engage armoured andunar- copter isdesignedto Equipment Mission The onboard avionicssuitesupportsall- The Ka-50combatheli- The helicopter’shighbattlefield survivability The Ka-50’suniqueflight ROSOBORONEXPORT 460-round ammunitionload. one built-in2A42restricted-swivel cannonwith ets inB8V20-Apods.Thehelicoptercarries ATGMs, fourIgla-Vmissiles,upto80S-8rock- Armament ag,k 450 13 2xTV3-117VMA 4,200 Crew 1 Powerplant Range, km Hovering ceiling,m 2,500 Climb rate,m/s Air speed,km/h: Max combatloadweight,kg Take-off weight,kg: Basic specifications The Ka-50armamentcomprises12Vikhr cruising 275 maximum 300 maximum 11,300 normal 9,800 Single-Seat CombatHelicopter Ka-50 turboshafts

45 COMBAT HELICOPTERS HELICOPTERS Ka-50-2 Tandem-Seat Modification of Ka-50 Combat Helicopter

Mission

The Ka-50-2 combat helicopter is designed to engage armoured and other surface and air targets; provide close air support to ground

HELICOPTERS troops on the battlefield; escort tactical airborne troops; conduct air-to-air and air reconnaissance missions, provide real-time information support to ground troops and target designation to air- ital terrain map-based navigation; very low-alti- borne and ground weapons systems. tude terrain-following/obstacle avoidance flight; acquisition and designation of ground, The Ka-50-2 is a tandem two-seat derivative surface and air targets, and their engagement of the Ka-50 combat helicopter featuring 85 per in any combat environment. The avionics suite COMBAT HELICOPTERS COMBAT cent commonality with the baseline model in manages employment of all types of onboard terms of design, power plant, systems, and weapons; presentation of target, flight, and navi- equipment. gation data on multifunction displays and the helmet-mounted target designation/display sys- Equipment tem; and provides target designation to other combat helicopters and ground-based gun/mis- The avionics suite comprises an integrated sile systems. flight navigation system, a helmet-mounted target designation system, a sighting system with The electro-optical system detects and pin- a laser-beam-riding channel, the Arbalet radar, points targets at a range of up to 8 kilometres an onboard digital computer, and a multiplex by day and up to 7 kilometres at night and pro- data bus. vides target designation to the onboard weapons systems. The radar can detect ground The multifunction avionics suite provides dig- targets at a range of up to 12 km in the air-to- surface mode and air targets at a range of up to 25 km in the air-to-air mode. The radar can Basic specifications simultaneously track up to 20 targets. Take-off weight, kg: normal 9,800 Armament maximum 11,300 Air speed, km/h: The Ka-50-2 armament comprises 12 maximum 300 Vikhr ATGMs, four Igla-V missiles, up to 80 S-8 cruising 275 rockets in B8V20-A pods. The helicopter carries one built-in 2A42 restricted-swivel cannon with Climb rate, m/s 13 460 rounds of ammunition. Hovering ceiling, m 4,200 Normal range, km 450 Powerplant 2 x TV3-117VMA turboshafts Crew 2

46 ROSOBORONEXPORT in thehoveringmode. and theSU-Rdeviceforrapidtroop downroping crane jibforhoistingpersonnel andcargoes, attendant. up to12stretcher casualtiesandamedical fuselage). Themedevacversion cantransport troops orvariouscargoes(insideunderthe holes inthesidewindowsanddoorway. fire theirsidearmsthrough sixswivellingport- on theswivellingnosegunmount.Troops can pods, and7.62mmPKTmachinegunsmounted with S-8rockets, uptotwoUPK-23-250gun Ataka/Shturm ATGMs, uptofourB8V20-Apods the field. converted intotheassault/medevacversions in day/night operations.Thehelicoptercanbe instruments enablingall-weather, all-climate, portation andmedicalequipment,avionics various weapons,aself-defencesystem,trans- casualties. search-and-rescue operationsandevacuate port militarycargoesandtroops; tocarryout ground/surface targetsandpersonnel; totrans- icopter designedtoengagesmall-size Variants Mission The Mi-171Shcombatversion isfitted with The Mi-171ShisanupgradeoftheMi-171hel- The Mi-171ShhastheLPG-150winchwitha The transportversion canairlift upto20 The Mi-171Shhelicoptercancarryuptoeight ROSOBORONEXPORT equipment. with installationofRussian-orforeign-made can bemodified intotheMi-171Shvariants armour plates,andprotected fueltanks. exhaust screens, flare dispenser, removable evc eln,m 6,000 2xTV3-117VMturboshafts 3,980 Crew 3 Powerplant Range, km: Service ceiling,m Hovering ceiling,m Air speed,km/h: Max liftingcapacity,kg: Take-off weight,kg: Basic specifications On customerrequest theMi-171helicopters Survivability isincreased thankstotheuseof ihu uiir ak 580 1,065 ferry (withauxiliarytanks) 4,000 without auxiliarytanks cruising 230 maximum 250 underslung 4,000 cargo hold maximum 13,000 normal 11,100 Combat Transport Helicopter Mi-171Sh

47 TRANSPORT HELICOPTERS HELICOPTERS Mi-17-1V Transport/Assault Helicopter

assault positions of the troops carrying out independent operations, airdropping tactical air assault forces, landing special operations teams, and evacu- ating combat casualties. The helicopter can HELICOPTERS provide fire support to infantry and airborne troops and conduct air reconnaissance on the battlefield. Additionally, the helicopter can conduct almost entire scope of Mission the tasks accomplished by its civil prototype, by being fitted with search-and-rescue, fire-fight- The Mi-17-1V transport/assault helicopter is ing, parachute jumping (paradropping) and air designed to perform transportation tasks with a photographic equipment. capability of engaging soft-skinned materiel The Mi-17-1V helicopter is manufactured in TRANSPORT HELICOPTERS and manpower. The Mi-17-1V is capable of air- transport/assault, transport and medevac ver- lifting materiel and ammunition to operational sions.

Equipment Basic specifications Take-off weight, kg: The avionics suite provides flight and employ- normal 11,100 ment of weapons during day and night under max 13,000 standard and adverse weather conditions. T/O weight normal max The avionics suite includes electronic display Airspeed, km/h: and navigation high-precision system, satellite max (from 0 to 1,000 m) 250 230 navigation system, night vision systems (night cruise (from 0 to 1,000 m) 220 to 230 205 to 215 vision goggles and optronic system of full-time Hovering ceiling, m 3,980 1,500 operation), weather radar, searchlight and other Service ceiling, m 6,000 4,800 types of both Russian and foreign instruments. Payload, kg: The survivability system includes the exhaust normal 2,000 jet IR screens, chaff (IR and radar) dispenser, max 4,000 jammer and a set of removable armour plates. Flight range, km: The helicopter is equipped with the tanks that with main fuel tanks 650 615 are self-sealed by the foam polyurethane filler. with one extra fuel tank 900 850 with two extra fuel tanks 1,150 1,110 Variants Number and type of engines, engine power, hp 2 х ТVЗ-117VM / 2,200 The Mi-17-1V transport version can carry up Crew 3 to 36 troopers or cargo, including wheeled vehi- Dimensions overall (length х height х width), m: cles of up to 4,000 kg in the cargo compartment helicopter 25.3 х 5.54 x 4.5 or up to 5,000 kg on the external store. The hel- cargo compartment 5.34 х 2.34 х 1.8 icopter allows airdrop of up to 22 troops or air- Rotor diameter, m 21.3

48 ROSOBORONEXPORT the followingsystems: capability, itcan befitted with copter's fullday-and-night In order toboosttheheli- adverse weatherconditions. delivery infairandpartly- night flights andweapons instruments ensure day-and- Features treatment. ation, allwoundedandsickreceive medical sick (onstretchers andonseats). Duringevacu- also provided forevacuationofwoundedand sick andwithfirst aidkits.Amixedversion is is equippedwith12stretchers forwoundedand ground. an altitudeof50to55(3540)meters above rescue hoistwhenthehelicopterishoveringat lift orlowertwo(one)menbymeansofaspecial lower cargoofupto300(150)kgaswell with theSLG-300 (orLPG-150M)winchtolift or types. to fire smallarmsoftheAKM,RPKandPK equipped withsixswivelpadstoallowtroopers holders). beam holders andupto9versions employing4 to 10versions ofhelicopterpayloadusingsix weapons inanymixusingthebeamholders (up The weaponcontrol systemprovides theuseof machine gunsthatcanberemotely controlled. compartments accommodatePKTorPKTM GSh-23 guns.Thehelicopternoseandstern four UPK-23-250gunpodswiththe23mm incendiary tanks.Gunsincludeuniversal twoor type), bombsofupto500kgincaliberand siles oftheS-8typeorupto192S-5 weapons (upto80unguidedair-to-surfacemis- means ofaroll-type cargohoist,i.e.rappelling. landing ofcargoesandupto20troops by The Mi-17-1Vavionicsand The helicopterambulance(medevac)version The helicopter’srescue version isprovided The helicoptercargocompartmentis The transport/assaultversion usesunguided electronic navigationand ROSOBORONEXPORT ter armament. target, aswelltargetingtheorganichelicop- laying markandmeasuringaslantrangetothe screen ofthemultifunctiondisplay, guidanceof features, obstaclesagainstvideoimagesonthe detection andidentification oftargets,terrain adverse weatherconditions:mapping,search, tronic systemprovides understandard and on multifunctiondispays. well asdisplayofflight-navigation information and itstransmissiontointerfacedsystems,as processing anddisplayofsurveyinformation ital mapinthenon-volatilememory;reception, age ofnavigationpoints,routes andground dig- correction usingsatellitenavigationdata;stor- provides flight deadreckoning andcoordinates The GOES-321Mgyrostabilised opticalelec- The electronic navigationanddisplaysystem GEO-ONV-1 nightvisiongoggles adaptation ofitslightingfacilitiestonight electronic system GOES-321M gyrostabilised optical display system vision goggles.

49 TRANSPORT HELICOPTERS HELICOPTERS Mi-19 Airborne Command Post Helicopter

Mission

The Mi-19 heliborne command and control center provides higher reliability and better continuity, survivability and mobility of command and control.

HELICOPTERS The heliborne command and control center is used for automated and non- automated control over for- mations and units both directly and via ground con- two R-163-10V, two R-800L2E, E805КZ, trol posts while in-flight and on the ground, and and R-888 radio stations, multiplexer, R- also as an automatic radio-relay station. 098 (data transmission equipment), ‘Olen’ The center elements are as follows: and ‘Kardan’ encryption protection equip- Mi-17V helicopter ment, ‘Termit’ communication channel helicopter technical equipment. switch, and P-515 interphone facilities Crew: automation equipment system based on flight crew - 3 personal computer, computer-aided work- TRANSPORT HELICOPTERS tactical HQ – 5 stations, interfaces, and documentation communication operators – 2. equipment antenna feeder assembly set. Equipment The command and control center can also be The data transmission and communications equipped with the МТ-3E terminal of the data system: communication airborne system.

Basic specifications Mi-17V helicopter Crew 9 or 10 (3 pilots, 2 communication operator and 4-5 tac HQ officers) Take-off weight, kg: 12,200 Airspeed, km/h max 230 cruise 210 Flight altitude, m 5,000 Endurance, hrs 3 Flight range, km 535 Types of communications: open voice secure voice secure data transmission Communication range at flight altitude of 1,000 m, km: in decameter (DMW) band up to 1,000 in decimeter (DW) band up to 550 in meter (MW, MW-DW) band up to 400

50 ROSOBORONEXPORT ment. Thefollowingversions are available: operations, includingoperationinicingenviron- tion, ditchingcapability, andall-weatherflight sive seawaterenvironment, highflight automa- small size,highairframeresistance toaggres- trollability, excellentpowerplantcharacteristics, baseline machine’smanoeuvrability, highcon- inheritsthe the Ka-27shipbornehelicopter. It tanks inthecargoholdordraintankonasling. mounted inthecargohold. to 60stretchers. for smallarms. through portholesfitted withswivellingmounts porting upto82troops, whocanconductfire goes. hoists are usedtoloadnon-self-propelled car- Two 1,500kgwinchesand6,000kgelectric rear cargohatchfitted withaloweringramp. and fire-fighting versions are available. troop-carrying, medevac,flight refuelling tanker inside oroutsidethefuselage.Thetransport, troops andmateriel,transportcargoes The Ka-32utilityhelicopterisacivilversion of The Mi-26helicopterisdesignedtoairlift The Ka-32Aisdesignedfortransportationof Ka-32S shipborneversion. Ka-32A utilityversion oftheKa-32T; Ka-32T transportversion; The fire-fighting version mountsfourwater The tankerversion hasarefuelling system The medevacversion canaccommodateup The troop-carrying Mi-26iscapableoftrans- The transpoortMi-26isloadedthrough the ROSOBORONEXPORT and assembly. shore gas/oilpipelinesservicing,construction loading/unloading, icereconnaissance, off- medical evacuation,search-and-rescue, ship and large-sizecargoonexternalhardpoints, personnel andcargointhecompartment, sion-specific equipment. radio communications,navigation,andmis- evc eln,m 4,600 1,520 Range, km: Service ceiling,m Hovering ceiling,m Air speed,km/h: Payload weight,kg: Take-off weight,kg: Basic specifications ag,k 900 2xTV3-117VK 6,000 3,500 Crew 1-3 Powerplant Range, km 4 Service ceiling,m Hovering ceiling,m 11,000 5,000 Air speed,km/h: Passengers 16 Casualties onstretchers Underslung payloadweight,kg Take-off weight,kg Basic specifications 60 2xD-136turboshafts Powerplant Casualties onstretchers Troops 82 Crew 5 The Mi-26Tisacivilversion withauxiliary cruising 255 maximum 295 56,000 maximum 20,000 normal 15,000 max withexternalcargo maximum 54,000 normal 49,600 cruising 230 maximum 250 800 590 ferry 1,920 with fullfueltanks with 20-tonnecargo Heavy Transport Helicopters Mi-26/Mi-26T (TV3-117VMA) turboshafts Utility Helicopter Ka-32

51 TRANSPORT HELICOPTERS HELICOPTERS Ka-27PS Search-and-Rescue Helicopter HELICOPTERS

Mission Equipment SHIPBORNE HELICOPTERS

The Ka-27PS helicopter is designed to carry The onboard integrated flight navigation sys- out maritime search-and-rescue and salvage tem provides stabilised flight, automatic pre- operations in any season, by day and night, in programmed and radar-assisted high-precision good and adverse weather at Sea State 5. navigation to a pre-selected area with automat- The Ka-27PS is a SAR version of the ship- ic hovering there. borne ASW helicopter with a new fuel system The helicopter carries a salvage jib with a lifting and an upgraded radar. The radar is interfaced capacity of 300 kg. Up to 3,000 kg of cargo can with specialised equipment to detect surface be transported under external pylons. The Ka- targets fitted with radar transponders. 27PS is outfitted with a life boat and auxiliary Speedboat-type targets are detected at a range lighting equipment. It can additionally carry indi- of up to 25 km, and radar transponders at a vidual man-portable oxygen bottles for first aid range of up to 100 km. purposes. Ditching is facilitated by inflatable ballonets. Basic specifications To enhance flight safety in icing conditions Normal take-off weight, kg 10,900 the helicopter is equipped with electrothermal deicing systems for main rotor blades, engine Air speed, km/h: air intakes and cockpit canopy. maximum 270 cruising 230-240 Climb rate, m/s up to 14 Hovering ceiling, m 3,700 Range, km 800 Max endurance, hrs 5 Powerplant 2 x TV3-117VMAP turboshafts Crew 3 Casualties on stretchers 4

52 ROSOBORONEXPORT of thehelicoptertoapreset area inanyweath- system). Theavionicssuiteprovides navigation ing system(asurveillanceradarandasonar integrated flight navigationsystemandasight- in thesearch, search/attack, orattackvariants. facilitated byinflatable ballonets. from/landing onarocking deck. Ditchingis Ka-28’s landinggearisdesignedfortakingoff blades are foldedforshipborneparking.The operation from aircraft carriers. Mainrotor tion from lightdisplacementvessels,andgroup over 200km,atSeaStateupto5. night, inallweatherconditions,atarangeof points, inanyclimateandseason,byday maritime ASWmissionswithnoreference way- 500 m. up to75km/h,atamaximumdepthof submerged submarinesmovingataspeedof for, detect,track,andengagesurfaced Equipment Mission The helicopter'savionicssuiteincludesan The Ka-28helicopterisdesignedtosearch The helicoptercanbeconfigured tooperate The Ka-28iscapableofautonomousopera- The Ka-28iscapableoflongendurance ROSOBORONEXPORT detection, andlocation. provides surfaceandunderwatertargetsearch, of sonobuoysonthewatersurface.Theunit er/display unitisusedforautomaticmonitoring ship; andlandingapproach. Aspecialreceiv- ter; weaponscontrol; return flight tothemother help ofthesonarsystemandmagnetome- er conditions;submarinedetectionwiththe marine markingbombs. missiles, OMAB-25-12DandOMAB-25-8N Armament oepat 2xTV3-117VMAR 2.15 3,500 Powerplant 12,000 Search endurance,hrs Range, km: Service ceiling,m Air speed,km/h: Max take-offweight,kg Basic specifications Crew 3 The Ka-28armamentincludesAPR-3EASW erhvrin 1,160 900 search version search/attack version cruising 210-220 maximum 270 ASW Helicopter Ka-28 turboshafts

53 SHIPBORNE HELICOPTERS HELICOPTERS Ka-29 Combat Transport Helicopter HELICOPTERS

SHIPBORNE HELICOPTERS Mission Variants

The Ka-29 combat transport helicopter is The Ka-29 can be configured into a combat designed to airlift armed marines from war- or cargo version. The conversion can be per- ships, provide close air support to airborne formed directly in service units. troops, engage naval and ground targets (including armoured ones), and transport Armament cargo. It can be operated from various ship types and airfields in all latitudes, by day and The Ka-29 combat version is equipped with night, in any weather. the onboard sighting system supporting employment of the following weapons: up to eight Shturm ATGMs; up to 80 S-8 rockets in the B8-V20-A pods, air bombs, incendiary tanks, and the UPK-23-250 gun mounts. Basic specifications The transport version carries a 7.62mm Take-off weight, kg: nose machine gun with 1,800-round ammuni- normal 11,000 tion load. The cargo compartment accommo- with external cargo 12,600 dates up to 16 troops with side arms, or four Lifting capacity, kg: stretcher casualties and seven sitting casual- normal 1,850 ties with one medical attendant, or up to maximum underslung 4,000 2,000kg cargo. Cruising air speed, km/h 235 The helicopter can also be fitted with rescue Hovering ceiling, m 3,700 equipment for maritime search-and-rescue Service ceiling, m 4,500 operations. Range, km 460 Up to 4,000kg cargo can be carried on exter- Powerplant 2 x TV3-117VMAR nal hardpoints. turboshafts Crew 2

54 ROSOBORONEXPORT radar coverage. of 100-150km,andsurfacevesselswithinthe gets (fixed- androtary-wing aircraft) atarange ing andsimultaneouslytracking20to40tar- radariscapableofacquir- ry parameters. The nation ofthetarget’scoordinates andtrajecto- semi-automatic targetdetection,anddetermi- with a10secscanningcycle,automaticand vides omnidirectional airspace surveillance radarpro- lance radarandanIFFsystem.The mand andcontrol transmission oftarget-relevant datato face andairtargets,targetidentification, and in allweathers. unprepared sitesinanyseason, bydayandnight, capable ofoperatingfrom ships,airfields and to commandandcontrol posts.TheKa-31is target tracking;andautomaticdatatransmission wing aircraft, includinglow-altitudeairtargets; detection ofsurfacevessels,fixed- androtary- for airspace andsea-surfaceradarsurveillance; Equipment Mission The avionicssuiteenablesdetectionofsur- The Ka-31radarpickethelicopterisdesigned posts. Itcomprisesasurveil- ROSOBORONEXPORT com- 150 kmfrom altitudesof1,500to3,500m. control tactical datatransmissionto tem ensures telecodecommunicationsand home base.Theonboard communicationssys- grammed route withautomaticreturn tothe tions, guidethehelicopteralongapre-pro- ously measure thehelicopterandshipposi- along typicalroutes inpatrol areas, continu- or homebase,provide automaticnavigation matically guidethemachinetomothership attack, hoveranddescentmodes.Itcanauto- stabilise thehelicopter'saltitudeandanglesof tem isusedtogenerateanddisplayflight data, arledrne r 2.5 2xTV3-117VMAR 3,500 12,500 Crew 2 Powerplant Patrol endurance,hrs Max patrollingaltitude,m Air speed,km/h: Max take-offweight,kg Basic specifications The onboard integratedflight navigationsys- patrolling 100 maximum 220 posts ataminimumrangeof Radar PicketHelicopter command and Ka-31 turboshafts

55 SHIPBORNE HELICOPTERS HELICOPTERS Ka-60/Ka-62 Utility Helicopters

The Ka-60 utility helicopter is designed to carry out reconnaissance operations, transport 10 to 12 airborne troops, ship ammunition and other cargoes to combat operation areas, evacuate casualties, fly surveillance, patrol, and search-and- rescue missions, and as a training

HELICOPTERS asset. The helicopter can operate by day and night, in all weather conditions. The Ka-60 design provides max- Basic specifications imum safety for crew and trans- Ka-60 Ka-62 ported troops. Its avionics suite Max take-off weight, kg 6,500 6,250 depends on the helicopter version, Max payload, kg: the assault/transport being the inside fuselage 2,000 2,000 basic one. underslung 2,750 2,500 Air speed, km/h: In the single-seat vesion the maximum 300 300 pilot's seat is installed in the star- cruising 265 270 board half of the cockpit. Wide side Hovering ceiling, m 2,100 3,000 doors facilitate troops moun- MULTIROLE HELICOPTERS MULTIROLE Service ceiling, m 5,150 5,500 ting/dismounting and cargo load- Range, km 700 780 ing. Side wing panels can carry var- Powerplant 2 x RD-600V 2 x RD-600V turboshafts turboshafts ious types of weapons. Crew 1-2 1-2 The Ka-62 is a civil version of Troops/passengers 14 16 the Ka-60 helicopter.

Ka-115 Utility Helicopter

Basic specifications The Ka-115 utility heli- Max take-off weight, kg 1,970 copter is designed to airlift Max cargo weight, kg: personnel and cargoes in inside the fuselage 700 the cargo compartment, underslung 1,000 transport underslung car- Max air speed, km/h 250 goes, perform search-and- Cruising airspeed, km/h 230 rescue, patrol, and medevac operations, charter Climb rate, m/s 11.5 flights, etc. Hovering ceiling, m 2,350 Its design provides max- Service ceiling, m 5,200 imum comfort and safety Max range, km 780 for the crew and passen- Powerplant 1 x PW206D gers. Cargo is loaded and turboshaft unloaded through the side doors and rear hatch. The hel- Crew 1 icopter is capable of transporting large-size cargoes up to Passengers 5 four metres long.

56 ROSOBORONEXPORT behind thecockpitisequippeddependingon sion. Thepassenger/cargocompartment for passenger, orfortraineeinthetrainingver- half ofthecockpit;portsideseatisintended variety ofweapons. ing smallmid-sectioncapableofcarryinga ing combatreconnaissance two-seaterfeatur- military mission-specific modifications, includ- fire-fighting, agricultural,training,andvarious trative, patrol, medevac, ing versions alsocanbedeveloped:adminis- follow- transport passengers andcargoes.The Emergency Situations),gas/oil-field servicing, search-and-rescue model, thefollowingversions are available: tomer requirements. address anyoperationalconditionsandcus- cockpit. Thehelicoptercanbeeasilymodified to ules underthecentralcompartmentbehind ger/cargo cabinorvariedmission-specific mod- design accommodatingadismountablepassen- The Ansatutilityhelicopterisdesignedto The Ka-226utilityhelicopterfeatures modular The pilot'sseatisinstalledinthestarboard Apart from thebaselinepassenger/cargo ROSOBORONEXPORT (for theRussianMinistryof search-and-rescue, enable nightoperations. weather radarandelectro-optical equipmentto canalsocarry digital flight control system.It wheeled orski-typelandinggear. hatch. Thehelicoptercanbefitted witheither and unloadedthrough twosidedoors andarear seats are energyabsorbing.Cargoisloaded pilotandpassenger the helicopterversion. The be employedforvariousmilitarymissions. crane, trainer, andVIP. Thehelicoptercanalso air ambulance,police,fire-fighting, flying oepat 2xAllison 600 6,200 2,500 Powerplant Max range,km Service ceiling,m Hovering ceiling,m 3,400 Air speed,km/h: Max payload,kg: Max take-offweight,kg Basic specifications a ag,k 635 5,700 3,300 2xPW-207Kturboshafts 280 Passengers 10 Crew 1 Powerplant Max range,km Service ceiling,m Hovering ceiling,m Max airspeed,km/h Max payload,kg: Take-off weight,kg: Basic specifications Passengers 9 Crew 1 The helicoptermountsanelectro-hydraulic nietefslg 1,400 cruising 195 maximum 205 underslung 1,500 inside thefuselage nietefslg 1,000 underslung 1,300 inside thefuselage normal 3,000 maximum 3,300 Utility Helicopter Utility Helicopter 250-C20B turboshafts Ka-226 ANSAT

57 MULTIROLE HELICOPTERS HELICOPTERS Mi-2A Upgraded Utility Helicopter The Mi-2A helicopter has transport, trainer, medevac, reconnaissance, airborne command post, VIP, and gunship versions.

Basic specifications Take-off weight, kg: maximum 3,700

HELICOPTERS normal 3,550 Max payload, kg: inside the fuselage 1,000 The Mi-2 upgrading programme is aimed at underslung 800 extending the helicopter’s service life, increas- Passengers 9 ing reliability and flight safety, and improving its Air speed, km/h: flight performance. maximum 235 The first stage of the upgrading programme cruising 215 envisages enhancement of the helicopter's reli- Hovering ceiling, m 2,100 ability, improvement of its flight performance, Service ceiling, m 5,000 and repairs. The second stage includes service Range, km 450 life extension and fitting the helicopter with new Powerplant 2 x AI-450, equipment, a new power plant (Russian- or for- GTD-350W, Arrius turboshafts MULTIROLE HELICOPTERS MULTIROLE eign-made), new main rotor blades, rotor hubs, Crew 1-2 and rotor drive system. Mi-34U Trainer Helicopter

The Mi-34U trainer helicopter is based on the certificated Mi-34S utility helicopter. Designed as a training asset for military and civil aviation flight schools and flying clubs, the Mi-34U can

Basic specifications Take-off weight, kg: maximum 1,350 normal 1,300 Max payload, kg: inside the fuselage 240 underslung 300 Air speed, km/h: maximum 215 also be used for demonstration flights including cruising 175 helicopter aerobatics. Hovering ceiling, m 1,000 The baseline Mi-34U can be converted into Service ceiling, m 4,500 administrative, passenger, police patrol, ambu- Range, km 400 lance, agricultural, and other versions, devel- Powerplant 1 x M-14V-26V piston engine oped for the baseline model. Crew 2

58 ROSOBORONEXPORT AEROSPACE SYSTEMS

UNMANNED AIR SYSTEMS

ROSOBORONEXPORT 59 REYS-D Unmanned Air Reconnaissance System

Mission

The Reys-D system is designed to carry out air reconnaissance, additional target and terrain reconnaissance, and battle damage assessment at a depth

UNMANNED AIR SYSTEMS of 150 km behind the forward edge of the battle area. The system includes: the Reys-D reusable unmann-ed air vehicle Equipment the SPU self-propelled transporter/launcher providing UAV transportation, aiming The integrated flight navigation system of the and launch Reys-D UAV ensures its flight along a pre-set tra- the TZM transporter/refueller designed to jectory with high-precision approach to the desig- transport and refuel a SPU-mounted UAV nated reconnaissance areas, and landing after the POD-D3 mobile data processing and completing the mission. decoding centre The reconnaissance equipment container is mobile checking/testing system compris- quartered in a detachable nose part of the UAV ing two test vehicles and a power source fuselage. The following two mission payloads are RECONNAISSANCE SYSTEMS for routine UAV maintenance possible: technological equipment system. the AP-402M aerial camera and the The Reys-D is capable of carrying out air recon- Zima-M IR reconnaissance equipment naissance in any weather, by day and night, in the AP-402M aerial camera and the Aist-M hostile air defence and eventual NBC contamina- television system. tion conditions. The Reys-D is a fully autonomous system It is capable of detecting enemy objects, enabling round-the-clock covert deployment receiving and recording reconnaissance data in from unsurveyed sites. In the high alert status, real-time both on board the reconnaissance UAV the UAV can be launched within 10-12 minutes and at the ground-based data processing and after receiving the corresponding launch com- decoding centre. The system identifies targets, mand, as well as immediately after the march determines their coordinates, prints out photo- (the SPU vehicle can run a distance of up to 500 graphs and reconnaissance reports. km). It takes 35-40 minutes to prepare the UAV for launch after the march. The pre-launch prepa- Basic specifications rations can be done by a crew of three. Launch weight (with booster), kg 1,600 Thirty seconds after the UAV has flown over the Range, km 360 designated area, the POD-3D system operator Air speed, km/h 850-940 receives the reconnaissance data, complete with Altitude range, m 50-2,000 coordinates referenced to the flight route. Dimensions, m: length 8.06 Variants wing span 2.24 height 1.54 On the basis of the Reys-D UAV the Reys-DM Pre-programmed altitude changes 15 air target capable of imitating various manoeu- Reconnaissance area number 7 vring targets flying at speeds of 500 to 900 km/h Total area, reconnoitred has been developed. in one flight, km2 up to 2,100

60 ROSOBORONEXPORT Ural truckschassis. est fires. transmission lines,anddetectfor- provide maintenanceofpower patrol roads, gasandoilpipelines, tactical depth.Itcanbeusedto get andterrainreconnaissance at naissance, performadditionaltar- designed tocarryoutairrecon- Mission The Pchela-1 systemis The Pchela-1 RPVsystemismountedonthe The systemincorporates: technical supportvehicle. ing fourRPVs andexpendablemeans transporter-loader vehicle,accommodat launch testequipment transporter-launcher vehicle,withpre- mated work-stations) mobile ground control post(with twoauto- containers (upto10RPVs) Pchela-1 RPVintransport ROSOBORONEXPORT Small-Size Tactical AirReconnaissanceSystem ing simultaneousremote control oftwoRPVs are displayed.Thesystemiscapableofprovid- RPV’s flight pathandcurrent coordinates also maintenance. Ontheoperator'smonitor tor's monitorinreal time,aswellpost-flight naissance datawithpresentation ontheopera- remote flight control, reception oftherecon- launch preparation oftheRPV, itslaunchand a anhwih,k 138 3.5 2 Dimensions, m: 120-180 Ground crew: Number ofsimultaneouslycontrolledRPVs upto2,000 Wind speed,m/s: RPV launchsitealtitude(aboveS/L),m Max launchweight,kg Flight endurance,hrs Air speed,km/h Flight altitude,m: TV-camerawith zoom-lens, Recce payload: Basic specifications The systemoffers fullyautonomouspre- igsa 3.4 3 upto8 3 upto10 height 1.41 wing span length 2.7 transporter-launcher vehicle mobile groundcontrolpost 100-1,000 100-3,500 at landing at launch over terrain over seasurface IR line-scannermountedongyrostabilizedplatform IR linescanner(andforward-lookingradar) mounted ongyrostabilizedplatform PCHELA-1 multi-camera TVsystem

61 RECONNAISSANCE SYSTEMS UNMANNED AIR SYSTEMS UNMANNED AIR SYSTEMS (with data reception) from the command and pre-programmed onboard autopilot or ground launch post. operator. The vehicle is recovered by parachute The system can be deployed by means of on any level. The four-point non-retractable standard airdrop facilities in any region of the landing gear can sustain a 10 g-load at landing. world. The Pchela-1 is made of fibreglass and features The Pchela-1 RPV uses two solid-propellant low-damage landing capability and high boosters to take off from a short guide rail. Its repairability. flight can be controlled by commands of the It is transported with folded wings in a transport/launch container protecting it during airdrops and providing quick deployment.

Equipment

The onboard equipment of Pchela-1 includes RECONNAISSANCE SYSTEMS a combined reconnaissance set comprising a TV or IR system mounted on a gyro-stabilised ventral platform. The TV camera field of view can vary within a range of 3-30 degrees. The IR system’s ground coverage totals three fourths of the RPV's altitude at three millirads resolution.

62 ROSOBORONEXPORT AEROSPACE SYSTEMS

TRAINING SYSTEMS

ROSOBORONEXPORT 63 TECHNICAL TRAINING AIDS (AIRCRAFT SIMULATORS AND AUTOMATED TRAINING SYSTEMS)

Modern technical training aids include specialized hardware, general and special software and real controls of aircraft and instruments. They are based on high technologies and mathematical modeling of the aircraft (helicopter) flight dynamics on test benches and geographic information computer technologies that are used in off-cockpit display systems and provide realistic flight environment in the trainer.

STBP-29 Specialised Combat Simulator

TRAINING SYSTEMS and IASO-29 Automated Training System The specialised combat simulator is designed for flying personnel to study and master air materiel, undergo training/retraining and maintain their airmanship. It also assists in the evaluation of the flying personnel readiness for piloting, air navigation and combat employment of the MiG-29 (MiG-29SMT) aircraft individually and in two-plane formation using the avionics suite and in co-operation with ground management equipment in the enemy’s fire and jam- MiG-29 AIRCRAFT SIMULATORS AIRCRAFT SIMULATORS ming countermeasures environment.

The training suite includes: training of flying personnel, engineers and tech- fixed-cockpit flight simulator nicians for operation and maintenance of air- external visual system craft and ensures high quality of training. It is of computing system. modular design and its computing environment The training system is controlled from the features an open architecture. instructor’s seat. For practicing in two-plane for- IATS hardware/software incorporates: mation and simulation of air combat with really collective and individual training systems controlled enemy aircraft, the system is flight procedures simulator, including a equipped with the auxiliary pilot’s seat. cockpit simulator that imitates the pilot’s The training system is effective for mastering seat according to the organization list and the multimode avionics suite, weapon control functional logic of controls and equipment computing system and flight-navigation com- of the aircraft cockpit as well as control plexes. computer system that also imitates opera- The interactive automated training system tion of the equipment and weapons of air- (IATS) is designed for classroom and primary craft in real time reference and information system.

MiG-29 Aircraft Integrated Simulation Systems for Avionics Suite and Weapons

The avionics suite and weapons integrated themselves and thus allow integration and test- simulation systems of the MiG-29, MiG-29SMT, ing of aircraft systems and comprehensive MiG-29K and MiG-29M/M2 aircraft are scaled- monitoring of computation processes in air- down simulators. borne computers and data flow in communica- These systems simulate maximum realistic tion lines between the systems. physical impacts upon the avionics suite, The simulation systems employ a unique dig- weapons control system and the weapons ital simulator of radar signals of the new gener-

64 ROSOBORONEXPORT flight missions(navigation,combatemploy- most importantelementsofhigh-complexity afford opportunityforflying personnel topractice piloting. flying personnel togaincomprehensive skillsin trainers are anintegrationelement thatallows full-scale preparation ofcrews forflights. The borne weaponsandaircombattactics. (ground) targets,combatemploymentofair- techniques, airnavigation,guidanceat bination ofspecialtrainingprograms forpiloting tematization ofprofessional skills,usingacom- new generation. flying personnel, usingtheequipmentof classrooms. and flight procedure simulators andcomputer Su-30 anditsversions incorporatespecialised Su-22М4, Su-24,Su-27anditsversions and Аn-24, Аn-26,Аn-72,Аn-74,Аn-124,Su-22М3, 154, Тu-204,Тu-334,Il-76,Il-96,Il-114,Аn-12, case offailures. employment bothinstandard situationandin provides practicingofalltypesweapons being apartoftheintegratedsimulationsystem gets. Theweaponsexternalstore simulator employment ofafighter againstair(ground) tar- fare systemsandadisplaysystemforcombat for IRSTs, signalsimulators forelectronic war- ation andasimulatorofheat-emittingtargets Technical trainingaidsdesignedfortheТu- Specialised operational flight simulators Integrated simulators inthisclassprovide a A modularapproach totrainingincludessys- Integrated simulators are designedtotrain ROSOBORONEXPORT Technical Training Aids for Military Transport, AidsforMilitary Technical Training trainers available. maintenance ensure effective operationofthe thesis. Up-to-datetechniquesofrepair and new digitalsystemsofdisplayedsituationsyn- simulators delivered earlier can befitted with equipment, displaysystem,etc.onsite.The of thecomputingsystem,simulatorcontrol the trainingprocess. Itenvisagesreplacement trainers opensthenewprospects ofimproving of thestandard documents. nance ofaircraft according totherequirements a sequenceofactionsinoperationandmainte- preset leveloftheoretical knowledge, practicing tems ofthespecified aircraft. sonnel mastersomeindividualairbornesys- for flying personnel totraininairrefueling. for theSu-30,Su-24,Tu-95 andTu-160 aircraft for thefirst timedevelopedandmanufactured specialised airrefueling simulators havebeen ment andin-flight refueling). For example,the craft. the crew fullymasterallcapabilitiesoftheair- hone theirbattletechniques.Thisinturnhelps tic tacticalsituationallowflying personnel to models andweaponsplussimulationofrealis- ers anddatahighway. Full-size aerodynamic center thatemployshigh-enduniversal comput- controlled bythesimulationsystemcomputing The feasibilityofcomprehensive upgradingof Computer classrooms are designed toforma Flight procedure simulators helpflying per- Operation ofallscaled-downsimulators is Combat andCivilAviation

65 AIRCRAFT SIMULATORS TRAINING SYSTEMS Mi-8/Mi-17 Helicopters Technical Training Aids

Integrated simulators of Mi-8/Mi-17 (Mi-17- All tasks to be performed during training can 1V, Mi-17V-5, Mi-171Sh, Mi-26) helicopters can be divided into three groups: be of motion and fixed types. flight tasks Simulators are designed to train flying per- helicopter piloting tasks sonnel and engineers, maintain their skills at a combat tasks. required level and retrain the crews of other types of rotary-wing aircraft in a fully realistic Automated training systems (ATS) are cockpit and flight instrument environment with designed for classroom training of flying per- standard consoles and controls. sonnel, engineers and technicians in the inter- TRAINING SYSTEMS The simulators motion system provides simu- active mode. These systems form a single func- lation of acceleration effects. It is electrically tionally interrelated base of theoretical knowl- operated and has six motion levels. edge and monitor programs using computer technologies and afford individual training of each trainee, subject to his spe- cialization and initial level of skills. The externally-slung cargo operator procedures simulator of the load on external store simulates the operator station (fenced door, rope "spider") also provided with a stereoscopic system to visualize

HELICOPTER SIMULATORS the behaviour of the load and cable through the cockpit door. The appropriate software is delivered to follow the behaviour of the load and the cable and their influ- ence upon the helicopter flight.

The fixed simulator includes: realistic helicopter cockpit environment digital computing system and software external visual system of the ‘Aurora’ type (with a hemi-spherical projection-screen system with cockpit cut- off angles – in horizontal plane - 220 degrees – in vertical plane - 65 degrees displayed database preparation system instructor’s station and integrated check system vibration, shaking and acoustic effects simulation systems.

66 ROSOBORONEXPORT designed forclassroom trainingofflying per- combat tasks. ly: flight tasks,helicopterpilotingtasksand ulator maybedividedintothree groups, name- operated andhassixmotionlevels. lation ofaccelerationeffects. Itiselectrically actions inspecialconditions. modes andcombatmissionspluspracticing ties forthecrews tomastermainoperation ment environments, providing newopportuni- sonnel inarealistic cockpitandflight instru- copters canbeofmotionandfixed types. (Mi-24V, Mi-24P, Mi35P, Mi-35,Mi-35M)heli- Integrated simulators oftheMi-24/Mi-35 Automated trainingsystems(ATS) are All trainingtaskstobeperformedonthesim- The fixed simulatorincludes: The simulatormotionsystemprovides simu- Simulators are designedtotrainflying per- and acousticeffects. simulation systemsofvibration,shaking system instructor’s stationandintegratedcheck displayed databasepreparation system helicopters external visualsystemfordayandnight digital computingsystemandsoftware environments realistic pilot’sandnavigator’scockpit ROSOBORONEXPORT Mi-24/Mi-35 their specializationandinitiallevelofskill. aging complexcombatmissions,considering enable thepilotstoacquire firm skillsinman- process improvement. lators openthenewprospects inthetraining plus theflight procedures andintegratedsimu- systems ofthespecified typesofhelicopters active mode.Up-to-dateautomatedtraining sonnel, engineers andtechniciansintheinter- Functional databasesandmonitorprograms Combat TransportHelicopters ehia riigAids Technical Training

67 HELICOPTER SIMULATORS TRAINING SYSTEMS KRAB-1 Flight Procedures Simulator for Ka-50 Combat Helicopter The Krab-1 is designed to train pilots and to maintain, improve and restore their skills in handling airborne weapons (Vikhr ATGM, UASM S-8, 2А42 gun) of the Ka-50 helicopter. The simulator incorporates a cockpit with standard controls, a visual situation display simulator, an instructor’s station, a computing system and a cockpit-to-computing system adapter. TRAINING SYSTEMS The visual situation display simulator provides a realistic environment of landscape, artificial objects, weapons, HUD indicating marks and animation of explosions, smoke and fires.

At his workstation, the instructor can form training assignments archive the training results, display flight- navigation information and enter failures.

Game Controllers for Virtual Training of Flying Personnel

HELICOPTER SIMULATORS (Display Teams)

Game controllers are effective to practice execution of combat missions by a unit and to simulate a dogfight. Subject to demand, simulators and their basic software can be used for different types of Russian aircraft and helicopters. Modern game controllers enable flying personnel to execute combat missions at different kinds of landscape, simulating real distortions of environment in various weather conditions.

Aircraft simulators in this class are designed for virtual training of flying personnel in computer classrooms to help them master individual and group advanced piloting. They are actually computers with joysticks, integrated into a local area network.

68 ROSOBORONEXPORT AEROSPACE SYSTEMS

AEROENGINES

ROSOBORONEXPORT 69 70 TURBOJETS AEROENGINES Dimensions (withoutaccessories),mm: niedywih,k 80 860 830 9.0 8.7 66 0.890 67 Engine dryweight,kg 0.860 Gas temperaturebeforetheturbine, Pressure ratio Air consumption,kg/sec at take-off,kg/kgf/h Specific fuelconsumption Thrust, kgf: Basic specifications a imtr 7 805 772 max diameter 4,500 length 2,700 – 4,300 4,100 emergency (H=0,M=0) max continuous(H=0,M=0) 2,880 fixed-area type. There isnoafterburner, andthenozzleisofa and high-pressure turbinesare single-staged. bustion chamberhastwinnozzles.Thelow- cannularcom- high-pressure compressor. The sor withoutaguidevane,andfive-stage There isathree-stage low-pressure compres- two-shaft configuration andamodulardesign. burner allowshigh-altitudeaircombat. two-stageafter- and afixed-area nozzle.The single-staged low-andhigh-pressure turbines, compressor, acannular combustionchamber, compressor andafive-stage high-pressure afterburner hasathree-stage low-pressure Turbojet Engines R-95Sh, R-195 Turbojet Engine R25-300 niedywih,k 1,215 9.1 * -9,900kgfatM=1.0 Engine dryweight,kg 68.5 Dimensions, mm: Gas temperaturebeforetheturbine, 0.91 Pressure ratio Air consumption,kg/sec Specific fuelconsumption,kg/kgf/h Thrust (H=0,M=0,ISA),kgf: Basic specifications The R-95ShandR-195enginesfeature a The R25-300two-shaft, two-rotor enginewith a imtr 907 max diameter length 4,615 7,100* afterburner 6,850 emergency thrust ROSOBORONEXPORT o K 1,148 1,188 R-95Sh R-195 o K 1,353 95Sh engine. The R-195isfullyinterchangeable withtheR- and enhancedstabilityduringmissilelaunch. improved maintainability, reduced IRsignature, R-95Sh engine.Itfeatures increased thrust, bat proven cases). operability after considerabledamage(com- can withstand23mmround hits,andretain high reliability andcombatsurvivability. They forced gearboxdrivechain. lade drivegeneratorwithmultiplierandarein- MiG-21-93 aircraft. Ithasanintegratedhydrob- designed topowertheMiG-21familyaircraft. er andemergencythrust.Theengineis engine hastwoafterburning modes:afterburn- change, andeasysingle-handlecontrol. The burning modescontrol withsmooththrust ient maintenance,acontinuousrangeofafter- aircraft. 25UBK, andSu-25SMKaircraft. Variants The R-195engineisaderivativeofthe The enginesare notedforeaseofoperation, The R25-300-94isdesignedtopowerthe The engine’smainadvantagesare conven- The R-195engineisdesignedfortheSu-39 The R-95Shengineisfitted onSu-25K,Su- AL-21F-3 Turbojet Engine

installed to ensure internal cooling. The fully variable area propelling nozzle consists of the subsonic convergent and supersonic divergent rims.

Basic specifications Thrust (H=0, M=0, ISA), kgf: max continuous 7,800 min afterburner 9,700

The AL-21F-3 engine features a single-shaft full afterburner 11,250 AEROENGINES configuration. The 14-stage compressor has a Specific fuel consumption, kg/kgf/h: sophisticated control system. The cannular com- economy power (H=0, M=0) 0.80 bustion chamber has 12 flame tubes. cruising mode 0.76 The three-stage turbine is of an impulse-reaction max continuous 1.86 type. The blades of the first and second turbine Air consumption, kg/sec 104 Pressure ratio 14.55 stages are cooled with the bleed air taken from TURBOJETS the compressor. The afterburner has three annu- Gas temperature before the turbine, oK 1,385 lar stabilisers and six fuel manifolds with spray Dimensions, mm: and swirl-type nozzles. A perforated screen is length /diameter 5,340/1,030 Engine dry weight, kg 1,800

RD-33 Turbofan Engine Family

Mirage F1 fighter upgrade. It has a bottom gear- box, and can also be fitted on MiG-21 and Mirage III aircraft upgrades. The RD-33 engine has a two-shaft turbine con- The RD-93 engine was developed for the figuration with exhaust mixing in the afterburner. Chinese FC-1 aircraft. The engine features a modular design. The low- The RD-133 engine is designed for the MiG- pressure compressor has four stages; the high- 29 aircraft. It features a fully variable nozzle pressure compressor has nine stages. The engine with thrust vectoring and a new automatic has a short annular combustion chamber and hydromechnical electronic control system. single-stage low- and high-pressure turbines. The afterburner is common for both ducts. The engine features a variable-area supersonic propelling Basic specifications nozzle. RD-33 RD-133 Due to good gas-dynamic stability, the RD-33 Thrust (H=0, M=0), kgf: engines do not impose any limitations on pilot- max continuous 5,040 5,600 ing and feature high spool-up capacity. full afterburner 8,300 9,000 The RD-33 is designed to power the MiG-29 Specific fuel consumption, fighter family. max continuous (H=0, M=0), kg/kgf/h 0.74 0.77 Bypass ratio 0.46 0.437 o Variants Gas temperature before the turbine, K 1,680 1,720 The RD-33 Series 3 engine with an extended Dimensions, mm: service life is designed to power MiG-29M, MiG- length 4,230 4,230 29M2, MiG-29K and MiG-29KUB aircraft. max diameter 1,040 1,040 The RD-33N engine is designed to power the Engine dry weight, kg 1,055 1,145

ROSOBORONEXPORT 71 72 TURBOFANS AEROENGINES niedywih,k 150 ,4 1,570 1,547 1,530 Engine dryweight,kg 0.670 0.685 Dimensions, mm: 0.670 economy power(H=0,M=0) 12,500 consumption, kg/kgf/h 12,500 Specific fuel 12,500 Thrust, fullafterburner,kgf Basic specifications a imtr ,4 110 1,280 1,140 1,240 max diameter length 4,950 4,897 4,990 standard andtropicalised variants. Theyare high gas-dynamicstabilityofthecompressor. engine features asurgeterminationsystemand ic, whiletheauxiliaryoneishydraulic.The up system.Themaincontrol systemiselectron- a loopedoilsystem,andanautonomousstart- design. Theenginehasatop-mountedgearbox, supersonic nozzlehasavariable-area The afterburner iscommonforbothducts. flow indry-thrustengineoperationmode.The duct, andisfitted withadevicepreventing air bine coolingsystemisplacedintheexternal control. Theair-to-airheatexchangerofthetur- pressure turbines haveactiveradialclearance annular type.Thesingle-stagehighandlow- first group ofstages.Thecombustorisan high-pressure compressor hasavariable-area pressor andatwo-shaft turbine.Thenine-stage with afour-stagevariablelow-pressure com- Turbofan EngineFamily AL-31F The AL-31Fenginesare availablebothin The AL-31Fengineshavemodulardesign, ROSOBORONEXPORT AL-31F AL-31FN AL-31FP irregularities andpulsing. extreme conditionswithairintakepressure and durability, enablingtheiroperationin 200 km/h. operation modeatnegativeairspeeds ofupto enable executionofaerobatics inthedynamic 2.0, incontrolled, invertedandflat spins,and intake surgemodesatMachnumbers ofupto lope, andprovide stableoperationindeepair operational inawidealtitude/airspeed enve- the Su-30MK. of theAL-31Fenginewithaswivelingnozzlefor craft. gearboxes designedfortheChineseJ-10Aair- AL-31F enginefeaturingbothbottomandtop power theSu-33aircraft. craft. tion intheSu-27,Su-30,Su-32,andSu-35air- Variants The enginesboasthighgas-dynamicstability The AL-31FPengineisanotherdevelopment The AL-31FNengineisadevelopmentofthe The AL-31FSeries3engineisdesignedto The AL-31Fengineisdesignedforinstalla- NK-25 Turbofan Engine

The NK-25 three-stage bypass turbofan flows. The engine has an anti-surge protection engine features turbine blade radial clearance with automatic recovery of the initial operation active control and stator rings perforation for mode. The engine control system is electronic. increased compressor stability. The rotor blades The NK-25 engine is designed for the and the nozzle vanes are cooled with vortex Tu-22M3E multirole aircraft.

Basic specifications AEROENGINES Thrust at take-off (H=0, M=0, ISA), kgf 25,000 Specific fuel consumption at take-off, kg/kgf/h 2.08 Pressure ratio 25.9 Bypass ratio 1.45 o Gas temperature before the turbine, K 1,600 TURBOFANS

D-30F6 Turbofan Engine

systems. The electro-hydraulic engine control system is backed up with the hydraulic system activated if the electronic one has failed to ensure flight safety and effective mission accom- plishment. The engine has unique altitude and airspeed performance, providing maximum airspeed of 3,000 km/h at altitude and 1,500 km/h near ground. The D-30F6 engine is designed to power the The D-30F6 engine features a two-shaft con- MiG-31E fighter/interceptor. figuration with exhaust mixing from both ducts. The engine consists of seven modules. It has a low-pressure five-stage compressor, a high-pres- Basic specifications sure ten-stage compressor and a cannular com- Thrust, kgf: bustion chamber. The low- and high-pressure tur- max continuous (H=0, M=0, ISA) 9,500 bines are two-staged. The nozzle vanes and high- full afterburner 15,500 pressure turbine rotor blades are cooled. The Specific fuel consumption, kg/kgf/h: afterburner houses the exhaust mixer and has max continuous (H=0, M=0) 0.20 four ring flame stabilisers. The multivane super- full afterburner 1.90 sonic nozzle is cooled. The engine design Bypass ratio 0.57 enables onboard parameter monitoring. Air consumption, kg/sec 150 Reliability of the engine is ensured by the protec- Pressure ratio (total) 21.15 o tion, backup, and early malfunction detection Gas temperature before the turbine, K 1,640 Engine dry weight, kg 2,416

ROSOBORONEXPORT 73 74 TURBOFANS AEROENGINES yasrto .62.2 2,650 269 2.36 2,668 279 * -ISA+30 Engine dryweight,kg Gas temperaturebeforetheturbine, Air consumption,kg/sec Bypass ratio Specific fuelconsumption,kg/kgf/h: Thrust, kgf: Basic specifications aeofmd H0 =) .1 0.490 2,750 0.700 2,750 0.510 0.710 cruising mode(H=11,000,M=0.8) take-off mode(H=0,M=0) 12,000* (H=11,000, M=0.8) 12,000 max cruising take-off mode(H=0,M=0,ISA) The high-pressure turbinehas twostages,and engine hasacannularcombustionchamber. first rotor andaneleven-stagesecondrotor. The The two-rotor compressor has athree-stage figuration withexhaustmixingfrom bothducts. ICAO noiseandemissionrequirements. sions. ture inversions duringforest fire-fighting mis- operation inspiteofsharpairinflow tempera- environment. Theenginedemonstratesstable is easytomaintain,andcanbeoperatedinsea time operatingexperienceoftheD-36engine.It the Be-200aircraft. attachment fittings. hydromechanical control systemanduniversal equipped withathrustreverser, anelectronic- pressure turbineisthree-staged. Theengineis pressure turbineissingle-staged,andthehigh- has anannularcombustionchamber. Thelow- sure compressor hassevenstages.Theengine compressor hassixstages,andthehigh-pres- ic fanisofasingle-stagetype.Thelow-pressure supports. Ithasamodulardesign.Thetranson- configuration withminimumnumberofbearing Turbofan Engine D-30KP Turbofan Engine D-436TP The D-30KPenginefeatures atwo-shaft con- The enginecomplieswithstandingandfuture It boastshighreliability ensured byalong- The D-436TPturbofanengineisdesignedfor The D-436TPturbofanfeatures athree-shaft ROSOBORONEXPORT o 3K D-30KP II D30KP I ,2 1,356 K 1,424 thrust mode. affect theengineperformance attheforward stage andaclamshellreverser, whichdoesnot ture cooledrotor bladesof thefirst turbine mixer andamixingchamber. nozzle, commonforbothducts,hasablade the low-pressure turbinehas fourstages.The perature of+30 design take-off thrustatthe ambientairtem- Variants developed fortheA-40aircraft. Il-76MD, Il-76TP, Il-78,andA-50aircraft. Specific fuelconsumption,kg/kgf/h: Thrust, kgf: Basic specifications niedywih,k 1,450 22.17 1,373 Engine dryweight,kg Dimensions fandiameter,mm Gas temperaturebeforetheturbine, Pressure ratio(total) yasrto 4.98 Bypass ratio This isRussia’sfirst production enginetofea- The D-30KPSeries2engineprovides the The D-30KPVversion (withoutreverser) is The engineisinstalledontheIl-76TD, aeofmd H0 =) 0.370 take-off mode(H=0,M=0) H1,0 ,M07,IA 1,500 cruising mode(H=11,000m,M=0.75)0.608 (H=11,000 m,M=0.75,ISA) 7,500 cruising mode take-off mode(H=0,M=0,ISA+15) o C. o K 1,520 PS-90A Turbofan Engine AEROENGINES TURBOFANS

The PS-90 turbofan engine features a two- Variants shaft configuration with exhaust mixing from The PS-90A-76 derivative has an extended both ducts. It has a reverser inside the bypass service life and improved acoustic and emis- duct. The engine comprises 11 modules. The sion characteristics. It is designed to power the single-stage fan has titanium blades. The low- Il-76MF aircraft, and can also be installed on pressure compressor has two stages, and the the Il-76T/TD and Il-86 aircraft. high-pressure compressor has 13 stages. The The PS-90A2 derivative boasts enhanced engine has a cannular combustion chamber. reliability, improved efficiency, and simplified The cooled high-pressure turbine has two maintenance. stages, and the low-pressure turbine has four stages. The engine has a two-channel digital control system. Advanced control and monitoring system provides timely engine malfunction Basic specifications detection and on-condition maintenance. PS-90A PS-90A2 The unified PS-90A engine is designed to Thrust, kgf: power the Tu-204, Tu-214, Tu-330, Il-76MF, Il- take-off mode (H=0, M=0, ISA) 16,000 16,000 76T/TD, and Il-96-300 aircraft. In 1992 the cruising mode engine got the Interstate Aviation Committee (H=11,000 m, V=850 km/h) 3,500 3,700 and ICAO noise and emission certificates. Specific fuel consumption, kg/kgf/h Introduction of more stringent ICAO require- cruising mode (H=11,000, ments will not pose a problem for PS-90A-pow- V=850 km/h) 0.595 0.595 ered aircraft as only minor upgrading of the Air consumption, kg/sec 470 470 standard engine and air intake noise-absorp- Dimensions, mm: tion system will be required. fan diameter 1,900 1,900 length 5,333 4,964 Engine dry weight, kg 2,950 2,950

ROSOBORONEXPORT 75 TV3-117/TV7-117 Turboshaft Engine Family

VK2500 BK-1500B AEROENGINES

The TV3-117VM/TV3-117VMA turboshaft engine family features a single-shaft configuration. The 12-stage compressor has a variable-area guide vane. The combustion chamber is of a straight-flow annular type. The engine has a two- TV7-117CM stage free turbine with the overspeeding protec- TURBOSHAFTS tion. The exhaust pipe deflects the gas flow by 60 Turboshaft engine family incorporates the deg. The engine has an electronic-hydromechani- VK-800, VK-1500VM, VK-2500, VK-3000 cal control system. (TV7-117) and VK-3500 engines. The engine is designed to power the High-end technologies, latest electronic digi- Mi-8AMT, Mi-8MT, Mi-8MTV, Mi-14, Mi-17, tal systems, soft/hardware and monitoring and Mi-171, Mi-172, Mi-24, Mi-28, Mi-35, Ka-27, diagnostic equipment considerably improve Ka-28, Ka-29, Ka-31, Ka-32, Ka-50, and Ka-52 capabilities of helicopters equipped with the helicopters. new turboshaft engines. The TV3-117 is one of the world’s most effi- These engines differ from the old versions in cient engines in its class. It is easy to operate, extended overhaul period of the engine hot maintain and repair. Introduction of the emer- components, extra gas-dynamic stability at gency thrust mode allows the helicopter to land varying duties, engine parameters accuracy and safely with one engine failed. A dust guard can engine control quality, enhanced monitoring be installed. depth providing operation of the engine accord- Operation of the TV3-117 engine for 25 years in ing to its technical condition and better weight 60 countries has proved its exceptional reliability. characteristics and overall dimensions. The TV3-117VM/VMA is certificated by the The VK-800 turboshaft engine of the fifth gen- Aviation Register of the Interstate Aviation eration is designed to equip the Mi-54, Ansat Committee and by corresponding bodies of and Ka-226 type helicopters. The VK-800V Canada, China, and India. derivative was developed for the power units of helicopters of small and large load-carrying

Basic specifications Engines VK 800 VK 1500VM VK 2500 VK 3000 VK 3500 (TV7-117V) Power, hp / EM 1,000 1,800 to 1,900 2,700 3,750 4,000 takeoff 800 1600 2,400 2,800 3,000 cruise 450 1,100 1,750 2,000 – Specific fuel consumption, kg / (hp.h) take-off 0.238 0.240 0.210 0.199 0.199 cruise 0.291 0.265 0.230 0.220 – Location Mi-54, Ansat, Mi-8, Ка-60, Mi-17, Mi-24, Mi-38, Ка-32, Mi-38 Ка-226 Ansat Mi-28N, Ка-32, Ка-50-2 Ка-50-2

76 ROSOBORONEXPORT gear boxcandeceleratetheoutputshaft to6,000 ate atunpavedairfields. Theengineintermediate dust protector thatallowsthehelicoptertooper- features are asfollows: 1,200 to1,800hppowerclass.Itsdistinguishing RD-600V istheengineofnewgeneration twin-engine helicopters anditsderivatives.The design isinstalledontheKa-60/62multipurpose teristics, theengineholdsafirm placeamong engine. Byitsfuelefficiency andweightcharac- power derivativeofthewell-knowTV3-117VMA ted withtheTV2-117engines. tion. ItwasdevelopedfortheMihelicopters fit- ative withthepowershaft inabackward posi- high efficiency. tics ofthemainunitsengineprovide its operation. Moreover, theenhancedcharacteris- and reduces expensesforitsmanufacture and turbines. Allthissimplifies theenginedesign gal compressor andthesingle-stageun-cooled requirements ofthetestedmodelacentrifu- uration. Theengineparameters meetthe capacity, bothintwin-andsingle-engineconfig- The RD-600Vturboshaft engineofmodular The engineemploysabuilt-inhigh-effective The VK-2500turboshaft engineisahigh- The VK-1500VMengineisaturboshaft deriv- high degree ofcompression. pressor withacontrolled starter, featuringa four-stage miniature axial-centrifugalcom- hours es theengineoverhaulperiodto10,000 segmented two-wallflame tubethatincreas- automatic electronic digitalcontrol system new memorystorage two-stage powerturbine reverse-flow combustionchamber ROSOBORONEXPORT 38 helicopters. has twoversions: ized withthebaseengineby90%.The certified TV7-117turboshaft engine.It isunit- vides itshighreliability andlongservicelife. tem improves theengineperformanceandpro- the bestworld’smodels.Moderncontrol sys- rsuerto12.7 220 Overhaul period Engine dryweight,kg 1,550 Pressure ratio Specific fuelconsumption,g/(hp Power, hp Power, hp/EM Basic specifications i lwrt,k/ 4 Air flowrate,kg/s The VK-3500engineisdesignedfortheMi- The newVK-3000(TV7-117V)isbasedonthe Interstate Aviation Committee(АRIAC). cate registered intheAviation Registerofthe of thisengine. safety andreliability ofhelicopters thatmakeuse emergency warninggreatly improves afactorof fully automaticdigitaltwo-channeltestsystemof dimensions. vides itsbestweightcharacteristicsandoverall main rotor drivegearboxofthehelicopterandpro- rpm thatconsiderablysimplifies thedesignof aef 209 220 time betweenoverhauls,hrs takeoff evc ie r 10,000 service life,hrs cruise 225 cruise 1,000 takeoff 1,300 helicopters. upgrading theMi-28andKa-50/Ka-50-2 position –TV7-117VKenginefor with thepowershaft inabackward copter anditsderivatives TV7-117V(VМ) enginefortheMi-38heli with thepowershaft inaforward position– The RD-600Vengineisprovided withthecertifi- The advancedsystemoffaultsmonitoringand Turboshaft Engine RD-600V . h)

77 TURBOSHAFTS AEROENGINES 78 TURBOJETS AEROENGINES Bypass Turbojet Engine RD-1700 thrust of2,000to3000kgf. family ofthebypassturbojetengineswitha the cooledblades. compressor andatwo-stageturbinewith a two-stagefan,four-stagehigh-pressure engine usesatwo-shaft configuration, has fixed- andvariable-area nozzles.The afterburner wasalsodevelopedwiththe fixed-area nozzle.Theengineversion with bojet enginewithoutafterburner witha (МiG-АТ version). designed fortheMiG-UTStraineraircraft The RD-1700isabaseengineforthe The RD-1700isaminiature bypasstur- The RD-1700bypassturbojetengineis ROSOBORONEXPORT i lwrt,k/ 30 1,700 Dimensions Ratio Air flowrate,kg/s Specific fuelconsumption,kg/(kgf Maximum thrust,kgf Basic specifications niedywih,k 298 Engine dryweight,kg egh m1,915 length, mm imtr m621 14.1 diameter, mm bypass 0.78 pressure . h) 0.7 AEROSPACE SYSTEMS

AVIONICS

ROSOBORONEXPORT 79 AVIONICS SUITES

The avionics suite of modern and future air- airborne radars) and systems of communica- craft is an integrated complex of weapons and tions, identification and protection, which are flight control subsystems, general and special integrated by multiplex information communi- hardware/software and airborne equipment, cation channels. which functions are determined by missions, The Su-32, MiG-29 aircraft and its deriva- employment and specific features of aircraft. tives, Su-32, Su-37, Mig-31, MiG-AT aircraft, The architecture and technical level of the air-to-air and air-to-surface guided missiles avionics suite components for each specific and guided aerial bombs hold a firm place type of aircraft (helicopter) characterizes its air among modern and perspective models of air- property and defines further perspective of craft (helicopter). Automatic weapons and flight

AVIONICS AVIONICS upgrading and improvement of its functional control systems are divided into the following capabilities. types: Main components of the avionics suite are automatic missile and aircraft flight flight-navigation system incorporating automatic control systems weapons and flight systems, digital computer, fly-by wire systems information modules (electro-optic sensors and integrated flight control systems, etc.

MiG-29SMTAircraft Avionics Suite AVIONICS SUITES AVIONICS The MiG-29SMT avionics suite provides: SBKV-2V-1 strapdown attitude-and-head- automatic desired track flight, automatic ing reference system and manual change of waypoints in flight, SVS-2TSU-30MKI air signal system positioning under inertial and air course SUO-30 PK-29 weapons control system conditions, corrections from the satellite KOLS-13S IRST station navigation system SHCH-ZUM helmet-mounted target desig- employment of a wide range of aircraft mis- nation system siles, such as ‘air-to-air’ and ‘air-to-sur- VIM landing and navigation equipment. face’ guided missiles equipped with A-323 short-range landing and navigation infrared, active, passive, radio-controlled, radio system TV and laser target seekers, as well as VND-94 ranger finder unguided aircraft missiles ILS-31 head-up display built-in high-accuracy testing and trans- Reprogrammable memory unit mission of data on current status of the Aircraft sighting system coverage controls avionics suite for display and recording. The avionics suite features a certain margin of computing power to increase its functional capabilities on the customer’s request.

The aircraft avionics suite navigation and sighting system includes: BTSVM-486-2M aircraft digital computer BSPI-6M information conversion and interface unit two (four) MFI-10-6M colour 10-inch multifunction liquid-crystal displays BFS-3M signal shaping unit BKTS1-1 TV signal switching and conversion unit Sigma -95NA LINS laser inertial satellite system

80 ROSOBORONEXPORT fly-by wire systemsandcanprovide: form allfunctionsofautomaticflight control and ance atlowaltitudes,etc. flight (flying around obstacles),terrainavoid- in dogfighting, formationflight, low-altitude thrust control, landingapproach, maneuvering following functionaltasks,namely:engine and verticalplanesallowaircraft tosolvethe and director control offlight pathinthelateral to forward flight from anyattitude.Automatic flight speed.Thesystemcanalsobringaircraft pitch, roll andheading,altitudeparameters and aircraft withrespect toitscenterofgravityin provide automatedstabilizationandcontrol of The SAU-451-05SMTsystemisdesignedto The KSU-821systemsare designedtoper- pre-selected radioaltitudeholdandwarning automatic stabilizationofflight angles stabilization ofbarometric altitude bringing aircraft toforward flight from any angle ofstall stalling angleofattackandlocationat and auralwarningaboutreaching thepre- automatic limitationofanglesattack angles ofattackandoverload indication ofcurrent andpre-stalling automatic spinrecovery suppression ofatmosphericturbulence lesser maneuveringwingloads handling required characteristicsofstabilityand attitude according toflight regimes trimmed positionofthecontrol stick balance high-lift devicecontrol andaerodynamic automatic enginethrustcontrol approach director andautomaticcontrol atlanding ROSOBORONEXPORT composition. the typeofaircraft andhasitsownspecific sile andintegratedcontrol systemsdependson ers. electrical, electrohydraulic orpneumaticboost- chanics, large-scaleintegrationcircuits and microelectronics, optoelectronics, microme- environment usingthelatestelementsof built around analog-digitalordigitalcomputing nertdFih oto Systems Integrated FlightControl Hardware/software inconjunctionwithmis- All circuit configurations ofthesystemsare results. transmission ofinformationmonitoring monitoring withlocalizationoffaultsand automatic preflight andcontinuousin-flight and handlingcharacteristics quick reprogramming ofaircraft stability tions indication ofmechanism’sneutralposi- trimming inpitch,heelandheading MiG-29SMT Automated ControlSystem MiG-AT Aircraft Aircraft

81 AVIONICS SUITES AVIONICS Su-30MK Aircraft Avionics Suite The Su-30MK avionics suite is designed to operating with GLONASS and GPS systems provide automatic desired track flight, automat- at any point of the Earth ic and manual change of waypoints in flight, Aircraft sighting system coverage controls. positioning under inertial and air course conditions, corrections from satellite navigation sys- The navigation and sighting system of the Su- tem and employment of the weapons system. 30MK aircraft is designed to ensure control The aircraft avionics suite incorporates: over a wide range of aircraft weapons, among PNK-10-PU2 flight-navigation complex which are ‘air-to-air’ and ‘air-to-surface’ guided

AVIONICS AVIONICS including missiles equipped with infrared, active, passive, - aircraft digital computer radio-controlled, TV and laser target seekers as - TS-060 inertial navigation system well as unguided aircraft missiles of different - short-range navigation radio system systems. - air signal system Centralized entry of flight information into air- - radio altimeter craft systems, display of the required graphic, - limiting signal system imagery and mixed information on colour multi- - automatic control system function LCDs, simplicity in handling integrated systems allow the aircraft to fully use its techni-

AVIONICS SUITES AVIONICS BTSVM-486-2 aircraft digital computer cal, functional and combat capabilities. BSPI-6 information conversion and inter- The Su-30MK aircraft avionics suite was face unit developed in accordance with the adopted BTSVM-486-2-based display processors standards. This, in turn, provides its compatibil- SUO-30 PK weapons control system ity with different types of interface. MFI-10-5 colour 10-inch multifunction liq- The suite affords automatic and built-in high- uid-crystal displays (LCD) accuracy testing. Its open architecture allows BKTS1-1 TV signal switching and conver the customer to change configuration, expand- sion unit ing or minimizing the scope of duties. BRP-3 reprogrammable memory unit KBP-1 integrated power unit A-737 satellite navigation system receiver

Su-30MK

82 ROSOBORONEXPORT face withavionicssuite,weapons,emergency interface andperipheralunitsthatafford interface withtheavionicssuite. ment ofaircraft weaponsandensure theirinter- designed tocontrol preparation andemploy- of theKa-31includes: helicopter onships. tus ofhelicoptersubsystemsandbasingthe automatic monitoringandindicationofthesta- to effectively search fortargets.Italsoensures tion informationtothehelicopter’sradiofacility flight regimes andtransmissionofflight-naviga- vide automaticcontrol ofthehelicopterinall The systemisequippedwithintellectual The Su-30MKweaponscontrol systemis The Ka-31avionicssuiteisdesignedtopro- The avionicssuite’sflight-navigation system A-380MK systemofnavigationandlanding navigation aids,including: SAU-37D automaticdigitalcontrol system on ship plays 10-5I multifunctionalliquid-crystaldis- 3 multifunctionalconsolesandtwoMFI- cockpit managementsystemusingtwoPS- 53-16 helicopterdigitalcomputers) integrated computersystem(twoBaget- - - - satellite navigationsystem heading reference system SBKV-2V-2 strapdownattitude-and- INS-2000 inertialnavigationsystem ROSOBORONEXPORT Radar PicketHelicopterAvionics Suite combat capabilitiesoftheaircraft (helicopter). sequential upgradingandthisgreatly expands with weapons. dition ofthesystemcomponentsandinterface ment andbuilt-intestsystemthatcheckscon- the availableincorporatedcomputingenviron- face oftheavionicssuitewithweaponsdueto during weaponsemployment,intellectualinter- to-surface missiles,highsafetyandreliability and future weapons,suchasair-to-airandair- ty andblocksincorrect actionsofoperator. vides generalindicationofthecircuit operabili- checks powercircuits ofaircraft weapons,pro- ter incorporatesthetroubleshooting unitthat nel, andground monitoringequipment.Thelat- operation unit,localdatacommunicationchan- Aircraft Weapons ControlSystem A modulardesignofthesystemallowsits The systemensures control overavailable standby. cator, INP-Rflight director course indicator, horizon, standby;PNP-72-15course indi------set ofstandbyinstruments:AGR-81gyro system. long-range radioengineeringnavigation automatic direction finder radio altimeter air signalsystem Doppler ground speedanddrift meter Su-30MK Ka-31

83 AVIONICS SUITES AVIONICS Mi-28NE Combat Helicopter Avionics Suite The Mi-28NE combat helicopter avionics - air signal system suite provides: - radio altimeter around-the-clock combat employment of - automatic range finder helicopters in adverse weather conditions - long-range radio engineering navigation execution of combat missions at extreme system low altitudes four MFI-10-7V multifunctional liquid-crys- cooperation with helicopters of the team, tal displays and two MFPU multifunctional airborne and ground command stations consoles and air traffic controllers gyro-stabilized electro-optic surveillance employment of weapons both by the pilot and sighting system operating in visible and the operator and infrared bands AVIONICS AVIONICS adaptation of new and already employed two-band helicopter radar weapons ultra-violet, laser and electronic radiation on-condition operation of helicopters at detection system of the helicopter great distances from airfields and bases. automatic control system weapons control system The avionics suite incorporates: helmet-mounted target designation and Baget-53-15-based integrated computer display system system that allows processing of informa- switching and matching units tion by common interface data transmission and communication

AVIONICS SUITES AVIONICS navigation aids, including: system. - INS-2000 inertial navigation system - SBKV-2V-2 strapdown attitude-and- By its technical characteristics, the helicop- heading reference system ter avionics suite meets the requirements of a - satellite navigation system modern avionics suite of the fifth generation. - Doppler ground speed and drift meter KNEI-24 Electronic Indication and Navigation System The KNEI-24 for the Mi-35M is designed to reception, processing and providing the enhance accuracy of helicopter navigation and helicopter crew with flight-navigation and to receive and process information from flight- surveillance information. navigation and special equipment. It provides: The standard electronic indication and navi- dead reckoning of current coordinates of the gation system incorporates: helicopter and their correction, using infor- two colour 211x158-mm multifunction liq- mation from satellite navigation systems uid-crystal displays and button mask to nonvolatile storage of the database on control operation regimes of the IV-86-1 navigation waypoints and routes and ter- system rain the digital map multifunctional computer system input/output device Basic specifications satellite navigation systems (SN-3700) Doppler radio-navigation and air course method two indicators of gyro horizon (AGR-29RS-15) of dead reckoning of helicopter coordinates is provided power supply unit Accuracy of helicopter coordinates SVS-V1-1 air signal system. determination while operating In conjunction with the gyro-stabilized with satellite navigation system, m 50 flight/surveillance (surveillance/sighting) sys- and in differential regime, m 1 to 5 tem, these systems allow the helicopter crew to Capacity of memory-stored data for programmable day-and-night map, search, detect and identify waypoints, airfields, radio beacons up to 99 targets and obstacles against video pictures on Time of readiness, min 1 the multifunction displays as well as measure System weight, kg 35 target coordinates (slant range) and employ standard weapons of the helicopter.

84 ROSOBORONEXPORT raster mapswithoutanyrestrictions onthethe- Defense. Itsupportstheuseofbothvectorand standards oftheUnitedStatesDepartment ing theMIL-C-89038andMIL-PRF-89020A digital mapsofRussiaandalsothemeet- minutes. tors. Time toprepare aplandoesnotexceed40 level offlight crews andanumberofotherfac- ation andweatherconditions,terrain,training account allfactors oftactical,navigationalsitu- al airfields. 36-ship formationbasedeitheratoneorsever- flight documents. aircraft equipment,preparation andprintingof memory storageofFlash-typetoenterdatainto cartographic flight informationintoportable situation displays,loadingofflight missionsand preparation ofterraindigitalmapsforairborne missions forairbornesystemsandflight crews, ters, conversion ofoperating plansintoflight 29SМТ planes,Mi-35МandMi-28Nhelicop- Su-24, Su-27,Su-30МК,Su-35andMiG- preparation offlight missionplansforateamof The systemisdesignedtoprovide automatic The systemallowsallformatsofdigitaland Flight missionsare plannedtakinginto The systemallowscoordinated planningfora FLIGHT MISSIONPLANNINGANDPOST-FLIGHT CONTROLSYSTEM ROSOBORONEXPORT tronic countermeasures and dog-fighting. navigation, patrolling, escorting,refueling, elec- aircraft systemundercombatconditions. the flight crew actionsandfunctioningofthe obtained after post-flight objectivecontrol of is provided withthebuilt-intestcontrols. dimensional graphicinterfaceoftheuser, that and navigationalsituations. parametric andgraphicallibrariesoftactical ing inservicethusallowingausertocreate his ning adoptedintheCustomer’sAirForce. tion tothetechnologiesofcombatactionsplan- updating, providing itsunconditionalvalidity. parameter oftheplancausesitsautomatic integrated environment andachangeinany and helicopter-mountedversions. conditions. Thesystemcanbebothofvehicle- equipment operationundernormalclimatic weather conditions.Theoffice version allows computers isalwaysavailableforuseunderany version basedontheBaget-1/Elbrus-90micro- The systemalsoprovides plansforstriking, Planning functionsmayalsoincludethose The systemisfitted withanadvancedthree- All databasesofthesystemensure theiredit- Open architecture ofsoftware affords adapta- A planofaviationcombatactionshasan conditions. Thecontainer ment andinanyweather tile electromagnetic enviro- laptop canbeusedinhos- sion basedontheFM7000 example, theportablever- the Customermayneed.For operating conditionsthat ment tobeadaptedany container) allowtheequip- sions (portable,office, and photos ofanyscale. supports theuseofspace of scale1:40000and Electronic ChartoftheWorld is provided withthe 1: 32000000.Thesystem scales are from 1:5000to ater ofoperations. The systemdesignver- Chart

85 AVIONICS SUITES AVIONICS KARAT Flight Information Acquisition and Recording System AVIONICS AVIONICS AVIONICS SUITES AVIONICS

The Karat flight information acquisition and The Karat-B software provides quick readout recording emergency/operation system is of information during technological work and designed to acquire, monitor, record and monitoring of any parameter of the equipment. process flight information. It consists of two Another specific feature of the system is its modules – an airborne one (Karat-B) and an modular design. Such architecture of the sys- ground one (Karat-N). tem plus a unique program product ensures its The Karat-B provides acquisition, processing adaptation to any type of aircraft. The Karat-B and recording of information coming from sen- meets the requirements of the TSO C 124 inter- sors and airborne equipment via digital and national standard and features modern proces- analog communication lines, storage of the sor, conversion and interface modules, which, recorded information in case of an air accident, unlike previous analogues, greatly enhanced automatic monitoring of airborne equipment reliability, accuracy and depth of the equipment functioning on ground and in flight. The Karat-B- monitoring. 25 upgraded system may also operate as a recorder of aircraft information.

Basic specifications Recording of parametric information, h 2 System provides: reception and processing of information coming: via the ARINC-429 communication lines 8 channels from autonomous sensors as single signals 128 inputs from autonomous sensors as analog signals 40 inputs shaping of control commands 24 outputs Memory capacity, Mbytes 10, max Built-in test system available Weight, kg less than 16

86 ROSOBORONEXPORT device. tems. TheLINS-2000alsocontainsantenna the GPS/GLONASS satellitenavigationsys- tronics, computerandincorporatedreceiver of laser gyroscopes, accelerometers, serviceelec- tion parameters ofaircraft (helicopter). designed todefine andgenerateflight-naviga- INS-2000 inertialnavigationsystemsare egt g2 17 21 200x209406 MIL-STD-1553B, 385x264195 Interface – Weight, kg Dimensions, mm Time ofreadiness Basic specifications entm-ewe alrs r 5,000 Mean-time-between failures,hrs Errors (2s): INS-2000 The LINS-2000laserinertialsatelliteandthe The LINS-2000systememploysannular ihgrcmas i 54 15 with gyrocompass,min npee edn,mn1 0.5 6angularminutes 6.0angularmin/h 10 0.18 1.0(INSmode) 18angularminutes 1.85(autonomousmode) 2.0(INSmode) on presetheading,min 3.78(INSmode) true heading roll andpitch ground speed,m/s coordinates, km/h ROSOBORONEXPORT LINS-2000 INS-2000 n 0m(N oe and30m(SNSmode) and 40m(SNSmode) n . SSmd)and0.2(SNSmode) and 0.2(SNSmode) N-00LINS-2000 INS-2000 ter. Meantimebetweenfailures is5,000hours. INS mayalsobeequippedwithamagnetome- device ofthesatellitenavigationsystem.The navigation system. tronics, computer, interfaceunitandsatellite dynamically adjustedgyroscopes, serviceelec- The systemalsoincorporatestheantenna The INSinertialnavigationsystemusesthe Laser InertialSatelliteSystem, Inertial NavigationSystem communication channel multiplex data LINS-2000

87 NAVIGATION SYSTEMS AVIONICS Flight-Navigation System Control Consoles

Multifunctional liquid-crystal (LC) control con- Lighting facilities are adapted to the use of soles provide reception, storage and processing night vision goggles. Consoles are provided with of information coming from external sources, a built-in test system and engraved and multi- display of digital/letter and graphic information functional buttons. Mean time between failures on the cathode-ray and LC displays, information is 5, 000 hours. on controls’ status displayed on the console face panel and brightness control.

Basic specifications PS–2ZHK PS–3 PS–5 ZHK PS–7V

AVIONICS AVIONICS Display type Colour LC Cathode-ray Colour LC Colour LC Display format 480 x 640 pixels 10 lines by 21 symbols 480 x 640 pixels 480 x 640 pixels Display space, mm 100 x 130 80 x 15, 80 x 90 100 x 130 100 x 130 2

DISPLAYS Brightness cd/m >1000 200 >1000 >1000 Power supply 27 V 115 V 400 Hz AC 27 V 27 V Power consumed 25 W 100 W 40 W 40 V Interface ARINC 429 ARINC 429 ARINC 429 ARINC 429 Dimensions, length/ width / height, mm 170 x 200 x 85 147 x 192 x 278 170 x 200 x 150 146 x 200 x 150 Weight, kg 2.5 2.5 4 3.5 Viewing angles, deg in azimuth: ±20 ±30 +20/-10 +20/-10 in elevation: ±20 ±30 ±60 ±60 Processor I 186 I 186 I 386 I 386 Temperature, OC -40 ÷ +60 -60 ÷ +60 -40 ÷ +60 -40 ÷ +60

Electromechanical Displays

Basic specifications RMI-5 INP-92 IKP-92 Number of input lines 5 6 6 Dimensions, mm 85x95x200 120x120x240 120x120x240 Weight, kg 2 4 4 Voltage, V 27 27 27

88 ROSOBORONEXPORT with thesymbolicsoverlaid.TheMFPI-6isfitted tures highresolution toshow anyvideopictures readout inanyoutdoorlighting.Thedisplayfea- LC active-matrix(AM)displayallowsinformation and combathelicopters. sole isdesignedtoequipcockpitsofaircraft liquid-crystal AMdisplaysofhighbrightness displays are full-colourdisplaymoduleswitha on themgreatly helpsflight crew takedecisions. helicopters. Agoodpresentation ofinformation designed toequipdifferent typesofaircraft and egt g≤4 27V(2sides), automatic/manual 130х100mm oncustomer’srequest Power consumed Weight, kg Brightness 1,000 night visiongoggles Compatibility with VGA(1024х768pixels) Control panel Display space Full-colour AMLC screen ≤6 Basic specifications cd/m ≤6 5.10 9,max 9,max 255х205х135 255х205х135 211х160 255х205х135 Weight, kg 255х205х160 255х205х160 Dimensions, mm 211х160 ARINC-429, 211 х158 ARINC-429, 210х158 Interface ARINC-429, Temperature, ARINC-429, 211х158 Display space,mm ARINC-429, Basic specifications iesos m130х190 Dimensions, mm The MFPI-6multifunctionalindicationcon- Multifunction liquid-crystaldisplaysare The full-colourdisplaymodulewitha4x5inch The MFI-10-6М(MFI-10-6М1)andMFI-10-7 O 5 5/4 6 6 ±60 ±60 ±60 +55/-40 ±50 C I-T-53 RB S,SAA 30 TNG35VSTANAG3350V STANAG3350V STANAG3350V RGB,SSI, MIL-STD-1553B TNG35BKSI,PAL STANAG 3350B ROSOBORONEXPORT PK, 10BaseT S22,R-3C I-T-53 I-T-53 MIL-STD-1553V RS-232C, MIL-STD-1553V MIL-STD-1553V F 0 F 05MI1- F-06MFI-10-7 MFI-10-6 MFI-10-6 MFI10-5 MFI 104 brightness control(widerange) 30 W(100withheating) Multifunction Liquid-Crystal Displays Multifunction Liquid-Crystal 2 Multifunctional IndicationConsole , max 5,000 hours. in awiderange.Meantimebetweenfailures is automatic andmanualbrightnesscontrol with- vision goggles.Itscontrol consoleprovides borne indicators. Itiscompatiblewithnight buttons andreplaces electromechanical air- with thecontrol consolewith29multifunctional time betweenfailures isatleast5,000hours. in facilitiesandfeature ahighresolution. Mean duce two-dimensionalchartsduetotheirbuilt- vision goggles,require noforced cooling,repro- any outdoorlighting,compatiblewithnight and contrast,providing informationreadout in MFPI-6M (MFI-10-6М1) MFI-10-6М MFPI-6

89 DISPLAYS AVIONICS BTsVM-486 Airborne Digital Computer Family

The airborne digital computer is built around open modular architecture to ensure optimal selection of specific modifications for the required memory capacities and composition of interface channels of aircraft and helicopter avionics suites. As part of the aircraft (helicopter) ground flight preparation equipment, the computer is

AVIONICS used to plan flight routes and prepare the 2D and 3D maps. Debugger: Multi-windows symbol debugger of real time with remote debugging via the RS- 232C, ARINC-429 channels (GOST 18977-79). Functional program packages: navigation and control, 2D and 3D-graphic of real time, indication and control, high-precision navigation and flight control at low altitudes, combat missions.

AIRBORNE DIGITAL COMPUTERS AIRBORNE DIGITAL Basic specifications Processors AMD 486DX4-100, AMD Elan SC520-100, Graphical processor MIPS R4640-200 Memory, Mb static RAM from 4 to 16 Mbytes FLASH to 512 Mbytes Input/output device Channel of multiplex data MIL STD-1553B with redundancy, communication via operating as controller, terminal and monitor Channel of sequential data ARINC-429, communication via to 48 independent inputs and 24 independent outputs Channel of parallel data communication Q-BUS with functions of master and slave Output TV signals via STANAG 3350B, RS-343 (2D and 3D pictures in real time) Programme development tools Operating system 32-digit multitask system of real time RelMK32 Programming languages С++, Assembler Software Programme library - real-time nucleus - input/output - mathematic 1 3 Casings (construct) ARINC 404 within dimensions of /2 , /4 and 1 ATR (GOST 26765 16-87 within dimensions of 2.5 and 3 К) Mean-time-between failures 10,000 hours

90 ROSOBORONEXPORT BAGET-53 Airborne Digital Computer Family

The Baget-53 family airborne digital computers are designed to equip navigation and navigation-sighting systems of aircraft and helicopter. The computers have open modular architecture, sophisticated software, set of single commands and modules of sequential data communication. They employ a VME system bus and an automatic control system.

The computer software includes the real-time AVIONICS operating system, tests of built-in, scaled-up and autonomous control and input/output libraries.

BAGET 53-18

Basic specifications Central processor module: Based on МP R3081 50 MHz, 1890BM2T 80 MHz static RAM 6 Mbytes program ROM 16 Mbytes interrupt controller, timer, PDP controller sequential port RS232C COMPUTERS AIRBORNE DIGITAL FLASH-memory module 256 Mbytes Single command module 32 inputs, 32 outputs MPI module as per GOST 2676551-86 (Q – bus) Multiplex data communication module as per GOST 26765.52-87 (4 channels with redundancy, functions: controller, terminal, monitor) Sequential data communication module as per GOST 18977-79 (16 inputs, 8 outputs with debugging program for frequencies of 12.5, 50, 100 kHz), built-in controller 386ЕХ, 25 MHz Construct as per GOST 26765.16-87 (4К, 3К) in variants of connectors layout, both on front and rear panels (cut-in connector) Module construct ‘Euromechanics 6U’ with board measuring 160 х 233.4 mm

ROSOBORONEXPORT 91 Reprogrammable Memory Unit

The reprogrammable memory unit is designed for operation with the standard cards of the FLASH-memory. It has a socket for connection of the standard of type I and type II with a capacity from 1 to 512 Mbytes and performs writing and reading functions. The unit can be used for loading flight missions and for airborne recording. Standard hardware and software for the cards of the PCMCIA standard are used as the ground facili-

AVIONICS ties for preparation of flight missions and post-

flight data processing. BRP-3

Basic specifications Interface 2 input and 1 output channel of the ARINC-429 standard (GOST 18977-79) Mean time between failures 10,000 hours Power supply 115 V 400 Hz (11 W) and 27 V (25 W) 1 Construct 404 /4 ATR (GOST 26765 16-87 within dimensions of 1К) Weight, kg 3 BGS-3 Airborne Graphic Station AIRBORNE DIGITAL COMPUTERS AIRBORNE DIGITAL

The BGS-3 airborne graphic station is designed to provide: synthesis of 2D and 3D pictures with the flight-navigation information overlaid shaping of the ‘flyby’ and ‘bypass’ paths at low altitudes of flight shaping of terrain avoidance warning signals at low altitudes, landing and takeoff correction of coordinates with reference to the surface relief and ‘urban zones’ by the correlation-extreme method to reduce psy- chophysical stress suffered by the flight crew during take-off, landing and low-altitude flights.

Basic specifications Central processor based on AMD Elan SC520-100 Graphical processor based on MULTIKOR-11 Plug-in module of FLASH-memory PC CARD ATA, Gbytes 1 Power consumed, W ≤ 80 Mean-time-between failures, flying hours ≥ 10 000 Dimensions, mm 157 x 194 x 320 Weight of monoblock with memory unit, kg 8

92 ROSOBORONEXPORT mounted onlightconductors, control panels, goggles’ operationalwaveband. optical filters suppressing illuminationinthe internal lightingisadaptedbymeansofspecial trucks againstvegetationbackground. towers, forest borders, stand-alonetrees, and range of500mforelectricpowerlines,tangent change. blinding iflightingconditions tem activatedtoprevent crew matic brightnessadjustmentsys- cathode andanintegratedauto- a highspectralsensitivityphoto- cal biplanarimageintensifiers with rate third-generation electro-opti- pit. flight instrumentationinthecock- obstacle detectionandreading unequipped andunprepared sites; ing performedatnighton altitude flight, approach andland- trol duringtake-off, hovering,low- goggles (NVG)forvisualflight con- Abteis c 22 2 20 10 27 0.515 1 ±4 40 22 8 0.85 27 0.510 56to72 ±4 1 40 56to72 0.65 AA batteries,pcs Power supply,aircraftelectricsystem,V Weight (withoutstoragebattery),kg Dioptre lensadjustmentrange,dioptre Eyepiece-to-eyepiece adjustmentrange,mm Exit pupildistance,mm Exit pupildiameter,mm Angular resolution,parallellines/mrad Binocular coveringpower,deg Magnification, power Basic specifications Helicopter pilotsusenightvision In theGEO-ONV-1gogglesIRfilters are For NVGusethehelicopter’sexternaland The gogglesfeature aminimumdetection The binoculargogglesincorpo- ROSOBORONEXPORT intensity. essary colour, directional diagram,andlight elements are soorientedastoprovide thenec- light-emittingcrystalsinthe The structures usedinlight-emittingdiodes. are represented bynarrow-band lightemission ence coating.The sem coloured glasswithsolidmulti-layered interfer- sources. Thefilters are madeofhigh-quality bines lightfilters andsemiconductorlight cockpit lightingtotheO Equipment designedtoadaptthehelicopter and flight instrumentsinthehelicoptercockpit. Helicopter NightVision Goggles E-N- OVN-1 Skosok GEO-ONV-1 iconductor lightsources VN-1 SkosokNVGcom-

93 SIGHTING EQUIPMENT AVIONICS Helmet-Mounted Target Designation and Display System

day-and-night surveillance of airspace and display of current flight, navigation, sighting and other graphic information execution, jointly with the avionics suite, of navigation, surveillance and sighting missions.

Basic specifications Measurement range

AVIONICS angular coordinates of helmet position, deg: azimuth -90 to +90 elevation -60 to +30 The helmet-mounted target designation and Measurement error display system is designed to operate as part of angular coordinates helicopter equipment and provides: of helmet position, angular min 15, max around-the-clock operation of the helicop- Field of view of helmet-mounted ter under standard and adverse weather micro-display, deg 30 - 40 conditions Weight of helmet-mounted elements, g 500, max SIGHTING EQUIPMENT 52Sh Optical Location System

The 52Sh optical location system is designed Basic specifications to detect targets by their heat signatures, auto- Angle of view range, deg: matically track air targets, find range to air and azimuth ± 60 ground targets for gunfire delivery, and designate elevation 22.5/+52.5 ground targets with the laser beam for laser Weight, kg 200 guided missile employment. The system incorporates a field-of-view stabil- The 52Sh optical locator is designed for the isation system, a thermal direction finder, and a Su-35 aircraft. laser rangefinder/designator. 13S Infrared Search and Track System

The 13S IRST is designed for the MiG-29 aircraft to search, detect and track targets against their thermal radiation at all altitudes, in the lookup and lookdown modes, day and night and in the jamming environment as well as provide air or ground target ranging by means of a laser range-finder. High maintenance performance is provided by the built-in test system that allows quick evaluation of the main channels operability.

94 ROSOBORONEXPORT bombs. ed bombs,rockets, conventionalandretarded guided munitions,laser-andtelevision-guid- anti-tank missiles,deliveryofair-to-surface automatic modes,guidanceof in themanual,programme-corrected, and images. Thesystemprovides targettracking face, andairtargetsbytheirtelevision detect andidentifymobilestationarysur- gunfire delivery aswell). find rangetobothairandground targets(for track airtargetsintheIRband,locateand tems are designedtosearch for, acquire and interface unit. bilised actuator, andacommunications laser-beam-riding control channel,agyro-sta- matic televisiontargettrackingdevice,anATGM minator, adaytimeTV-opticalsystem,anauto- egt g 7 78 174 Weight, kg Angle ofviewrange,deg: Basic specifications The Shkvalsightingsystemisdesignedto The OEPS-27andOEPS-29sightingsys- The systemcomprisesalaserrangefind zmt ±6 ±30 ±60 -30/+15 elevation -60/+15 azimuth ROSOBORONEXPORT OEPS-27 OEPS-29 er/illu- ily aircraft. ly aircraft. target designationsystem,andacomputer. finder, alaserrangefinder, ahelmet-mounted enemy ECM. down modes,bydayandnight,underintensive gets atallaltitudes,bothinthelookupandlook- attack aircraft. copter. Line-of-sight anglerange,deg: Daytime controldevicefield-of-view,deg: Basic specifications Night controldevicefield-of-view: Electro-Optical SightingSystems The OEPS-29isdesignedfortheMiG-29fam- The OEPS-27isdesignedfortheSu-27fami- The systemcomprisesathermaldirection The OEPS-27canacquire andtrackairtar- The Shkval-MisdesignedfortheSu-39 The Shkval-VisdesignedfortheKa-50heli- lvto -85/+15 3x4 elevation wide zmt ±35 7.3x5.5 18.2x13.7 0.7x0.9 azimuth narrow wide narrow OEPS-27, OEPS-29 Sighting System SHKVAL

95 SIGHTING EQUIPMENT AVIONICS GOES-342 Sighting System

designate surface targets, as well as to perform laser rangefinding and targeting when deliver- ing missiles, rockets, and gunfire by day and night, in any season and in all weather conditions. The system is intended for installation on combat and transport helicopters. The GOES-342 integral system is built on the baseline gyrostabilised platform. The stabilised

AVIONICS optical module unit comprises an IR channel (8- 12 µm), daytime/low-level light TV channel, laser rangefinder (1.54 µm), IR locator or laser beam-riding missile guidance channel, stabilisation and control system, and interfacing units.

Basic specifications Viewing angles, deg: azimuth ± 230 elevation -115/+25 SIGHTING EQUIPMENT TV/IR channel fields of view, deg: wide 18 x 13.5/18 x 12 narrow 0.9 x 0.6/4 x 3 The GOES-342 sighting system is designed to provide round-the-clock visual information for Max rangefinding error, m 5 the helicopter crew on the MFD; to acquire and Stabilisation accuracy, µrad 50

GOES-520 Sighting System

nel on the multifunction displays by day and night, in all seasons and weather conditions. The system can be optionally supplied with a combination of channels such as imaging infrared and television, a laser rangefinder, and a missile control channel. The GOES-520 can be installed on helicopters, fixed-wing aircraft, and unmanned air vehicles.

Basic specifications Viewing angles, deg: The GOES-520 round-the-clock gyrosta- azimuth ± 180 bilised optoelectronic sighting system is designed to acquire and designate ground elevation +35/-85 objects and obstacles using their video images Dimensions (diameter x height), mm 350 x 500 generated by thermal imaging or the TV chan- Weight, kg 45 Operational temperature range, OC± 50

96 ROSOBORONEXPORT ing complexes. optical surveillanceandsurveillance/sight- designed tooperateaspartoftheelectro- Image ProcessingSystem OKHOTNIK ie hnesTV,infrared 1to2 Weight anddimensions: System interfaces: operating informationchannels Number ofsimultaneously Video channels Basic specifications The Okhotnikimageprocessing systemis Composition: oe upyfrom115/200-V, power supply volume, nu/uptsga fullvideo(1.0V,625lines) weight, kg input/output signal beam control system. BLIK multi-channellaser- subsystem automatic targettracking system BUK video-improving sub- L ROSOBORONEXPORT VIDEO INFORMATION ANDLASERSYSTEMS for black-and-whiteTVloadresistance75ohms IN ELECTRO-OPTICALCOMPLEXES from 27-VDChelicopterelectricalsystem 400-Hz AChelicopterelectricalsystem; as perGOST7845-92 4 to6 5 to7

97 VIDEO INFORMATION AND LASER SYSTEMS AVIONICS BUK Video-Improving Subsystem

The Buk video-improving subsystem greatly enhances quality of TV pictures and infrared images of target environment, including abnormal conditions of surveillance: low and irregular outdoor lighting, adverse weather conditions (haze, fog, dust, rain, snow, etc) and artificial tained: the weight of the subsystem does not causes (smoke, expositions, flashes). exceed 2.2 kg. The system increases distances of acquisition and identification of pin-point targets under

AVIONICS Functions: abnormal conditions of surveillance by 1.3 to smooth electronic zooming from 1 to 4 1.7 times. All data are processed in real time times and adequate quality of images is provided. overlay of graphics The Buk system can reduce time needed for integration of information coming from the acquisition and identification of targets and different-spectrum sensors extend the time limits of their actions. electronic stabilization of field of view. Equipment can be manufactured self-con-

Automatic Target Tracking Subsystem

The system locks on and automatically tracks tracking of the target in case of the 5-sec- detected by operator targets and transmits their ond (maximum) interruption of the optical current coordinates and control signals to the contact, automatic detection of tracking drives of the platform with the image position loss, automatic target relock-on caused by detectors to ensure high-precision tracking of optical contact interruption the target. sub-pixel accuracy of coordinates meas- Features: urement. manual and semiautomatic lock-on of The automatic target tracking system fea- targets tures extra functions to integrate information handling maneuvering targets of various coming from video channels of different spec-

VIDEO INFORMATION AND LASER SYSTEMS VIDEO INFORMATION RCS against inhomogeneous backgrounds trums and to ensure automatic acquisition of control along two axes in a closed system targets. BLIK Multi-Channel Laser-Beam Control System

The Blik multi-channel control system provides high-precision guidance of guided weapons by creating in space the information field in the form of the coded light raster, which center coincides with the optical line of sight of the target. The coded raster allows the guided missile to determine its position relative to the center of the information field and to move towards it.

Basic specifications Number of control channels 2, max Control range, m 10,000, max Coordinate discrimination error, m 0.1, max Transmitting module weight, kg 1.2

98 ROSOBORONEXPORT fighting; identifies typesandnumberofair- continuing airspace surveillance;supportsdog- attack ofairandground/surface targets,while electronic azimuthandelevationscanning. additional mechanicalazimuthdeflection, and “sea” and“micro-plan” modes,andiscapable attacks. automatic flight control duringmultipletarget tem alsoprovides missilelaunchesandsemi- search, andHUDtargetsearch. Theradarsys- vertical, wide-angle,andcruciformfixed-beam target illuminationfrequency, track-while-scan, provides discrete targettrackingwithalternable targets bytheirspeed,measures theirrange, nels. tion oftheair-to-airandair-to-surfacechan- ing missiles.Itcanprovide combinedopera- and semi-activeradar-homingheat-seek- oe osmto CD,kA3.6/0.5 4 8 Power consumptionAC/DC,kVA Volume, dm Weight, kg Number ofsimultaneouslyattackedtargets Number ofsimultaneouslytrackedtargets =5m Air targetdetectionrange(RCS Deviation angle,deg: Frequency band Basic specifications The Bars radarfeatures aphasedarraywith The Osaradarisdesignedtoguideactive The radarprovides detection,trackingand In theair-to-surfacemodeOsahas In theair-to-airmodeOsaradardetects elevation azimuth 3 ROSOBORONEXPORT 2 )85 27, R-73E,andKh-31Amissiles. ment. target indicationandcoordinates measure- and "freezing" modes,movingground/surface borne targets;provides mappingwithzooming range finding. while-scan, movingtargetindicationand variable rangeresolution, two-targettrack- of real-beam mapping,covertdetectionwith rce agt notmorethan15 4 X Number ofsimultaneouslyattackedtargets tracked targets Number ofsimultaneously Target detectionrange,km: Detection sector,deg: Frequency band Basic specifications The Bars provides guidance ofRVV-AE,R- zmt ±70 60-140 40-150 air-to-surface mode air-to-air mode elevation ± azimuth 45 Airborne Radar Airborne Radar BARS OSA ± 60 ± 60 120 150 X

99 AIRBORNE RADARS AVIONICS ZHUK Family Airborne Radars

Zhuk-ME Zhuk-MFE Zhuk-MSE Zhuk-MSFE

identification of target types and classes AVIONICS The Zhuk is a multifunction coherent radar identification of clustered target and deter- designed for multi-role aircraft (MiG-29 and Su- mination of its composition 27 fighters). detection of dangerous weather phenomena. As part of the avionics suite, the Zhuk airborne radar ensures:

In the air-to-air mode: In the air-to-surface mode: lookup/lookdown detection of air targets ground mapping at a resolution of up and measurement of the angular coordi- to 3 x 3 m (with zooming and “freezing” AIRBORNE RADARS nates, range and speed modes) tracking of single and clustered targets simultaneous tracking of several ground tracking of a clustered air target and attack (surface) targets of several most dangerous single targets detection and tracking of moving ground lock-on and tracking of visual target for (surface) targets dogfight measurement of slant visual range to detection and engagement of helicopters, ground (surface) targets including hovering ones information support of low-altitude flight.

Basic specifications Zhuk-ME Zhuk-MFE Zhuk-MSE Zhuk-MSFE Air-to-air mode Air target detection range (RCS = 5 m2), km: forward/rear hemisphere 110 to 120/ 100 to 110/ 180 to 190/ 170 to 180/ 45 to 50 45 to 50 65 to 70 55 to 60 Scanning sector, deg: azimuth ±85 ±70 ±85 ±70 slant +56 to -40 ±70 +56 to -40 ±70 Number of simultaneously tracked/attacked air targets to 10/4 to 20/4 to 10/4 to 30/6 Air-to-surface mode Ground (surface) target detection range, km: group of tanks /railway bridge 25/120 25/120 30/130 30/130 motor boat/destroyer 150/300 150/300 150/300 150/300 Number of simultaneously tracked ground (surface) targets to 2 to 2 to 2 to 4 Antenna type SA PA SA PA Antenna diameter, mm 624 700 960 980 Weight, kg 220 285 255 305

100 ROSOBORONEXPORT tions, theKopyoairborneradarensures: designed forcombataircraft. In theair-to-airmode: Air-to-air mode egt g1085 SA 500 100 2 SA 500 2 Weight, kg Antenna diameter,mm Antenna type tracked ground(surface)targets: Number ofsimultaneously Ground (surface)targetdetectionrange,km: Air-to-surface mode Scanning sector,deg: Air target,RCS=5m Detection range: Basic specifications ubro iutnosytakdatce agt / 10/2 8/2 Number ofsimultaneouslytracked/attackedtargets Kopyo-21I The Kopyoisamultimodecoherent radar Under normalandadverse weathercondi- zmt 4 ±60 ±40 azimuth lvto 4 +60to-40 80/150 25/100 100/200 ±40 20/80 motor boat/destroyer group oftanks/railwaybridge elevation lookdown: lookup: including hoveringones detection andengagementofhelicopters, veillance most dangerous oftheminairspace sur- al airtargetsanddiscriminationofthe simultaneous while-scantrackingofsever- tracking ofsingleairtarget lookup/lookdown owr/erhmshr 72 80/40 80/40 57/25 57/30 forward/rear hemisphere forward /rearhemisphere ROSOBORONEXPORT 2 , km detection, lock-onand KOPYO-21I/KOPYO-M In the air-to-surface mode: In theair-to-surface Kopyo-M detection ofdangerous weatherphenomena. nation oftheirnumber identification oftargettypesanddetermi- information supportincombat ground (surface)targets. measurement ofslantvisualrangeto (surface) targets detection andtrackingofmovingground targets simultaneous trackingofseveralground ing” modes ground mappingwithzoomingand“freez- oy-1 Kopyo-М Kopyo-21I nfe AirborneRadars Unified

101 AIRBORNE RADARS AVIONICS KOPYO-25 Airborne Radar AVIONICS AVIONICS

The Kopyo-25 is a multimode radar designed generation of the aircraft control signals for the Su-25 family aircraft (installed in sus- when attacking ground (surface) targets pended under-wing unit). generation of mission tasks for guided mis- Under normal and adverse weather condi- siles of the air-to-surface class AIRBORNE RADARS tions, the Kopyo-25 airborne radar ensures: measurement of slant visual range to ground (surface) targets In the air-to-surface mode: information support of low-altitude flight.

ground mapping at a resolution of up to In the air-to-air mode: 6 х 6 m (with zooming and “freezing” modes and aircraft targeting) lookup/lookdown detection of air targets simultaneous tracking of several ground continuous tracking of single targets targets lock-on and simultaneous tracking of sev- sea-surface surveillance eral air targets within the scanning sector detection and tracking of moving ground detection of helicopters, including hovering (surface) targets ones determination of air target coordinates and generation of mission tasks for air-to-air guided missiles, as well as signals and Basic specifications commands for fire control system Air-to-surface mode information support for attacking aircraft Detection range, km: and using guided heat-seeking missiles 2 sea targets (RCS=300 m ) 75 identification of target types and determi- columns of armored vehicles 25 to 30 nation of their number in the tracking Number of simultaneously tracked mode ground (surface) targets: 2 detection of dangerous weather phenomena. Air-to-air mode Lookdown air target detection range (RCS=5 m2), km forward hemisphere/ rear hemisphere 70/35 Number of simultaneously tracked/ attacked targets 10/2 Antenna type SA Antenna diameter, mm 500 Weight, kg 90

102 ROSOBORONEXPORT tions, theArbalet-Dairborneradarensures: designed forhelicopters. Arbalet airborneradarensures: unintended interference andjamming,the tions andinthepresence ofnaturalclutter, in theKaandLfrequency bands. pulse radaroperating two-band coherent helicopters. Itisa designed forcombat Airborne Radar ARBALET-D In theair-to-airmode: mode: In theair-to-surface Airborne Radar ARBALET The Arbalet-Disadecimetric-waveradar the Arbaletis Under normalandadverse weathercondi- Under normalandadverse weathercondi- ground mapping employment ofguidedmissilesandguns antiaircraft andantimissiledefense. employment ofguidedmissilesandguns to repel aguidedmissileattack information supportforthehelicoptercrew including guidedmissiles of thetargetsapproaching thehelicopter, detection andmeasurement ofparameters moving ground (surface)targetindication coordinates face) targetsandmeasurement oftheir detection andidentification ofground (sur- and measurement oftheircoordinates detection andidentification ofairtargets AIRBORNE RADARSFORCOMBAT ANDSPECIALHELICOPTERS ROSOBORONEXPORT a apn ag,k 32 120 Target detectionrange,km Air-to-air mode Azimuth scanningsector,deg Max mappingrange,km Target detectionrange,km Air-to-surface mode Basic specifications egt g30 10 1 Weight, kg tracked targets Number ofsimultaneously on approachingtarget,s Time todetectandlock Closing speedmeasuringrange,m/s Max targetdetectionrange,km: Basic specifications 140 Weight, kg 0.5 Detection range,km Low-altitude flight mode Scanning sector(detectionsector),deg Missile detectiontime,s Scanning sector(detectionsector),deg: In themeteomode: In thelow-altitudeflightmode: missile 3 zmt 360 -45to+15 10 elevation azimuth attack aircraft isl 5 15 12 25 missile attack aircraft tank bridge oe ie 0.4 ±30 1.5 slopes (morethan10deg) power lines elevation azimuth 360 tion probability. to increase theapproaching targetdetec- tronic andotherairbornewarningsystems recorder ground servicesandtotheon-board enemy’s attacktothehelicoptercrew and transmission ofinformationonthe danger level. na anddeterminationoftheirzones tude contourmatching detection ofground obstaclesandlow-alti- detection ofdangerous weatherphenome- information supportforoptical,optoelec- 25 to1,000

103 AIRBORNE RADARS AVIONICS KOPYO-A Airborne Radar

The Kopyo-A is a coherent multimode radar, which provides sea (earth) surface surveillance during execution by helicopters and aircraft of combat missions and search-and-rescue operations.

Under normal and adverse weather conditions at different states of sea and ground sur-

AVIONICS AVIONICS face, the Kopyo-A airborne radar ensures:

all-aspect maritime border surveillance and monitoring in a circular zone of 0° to 360° with a scanning radius of up to 250 km search and detection of surface objects, Basic specifications including of small-size (boats, motor boats, Air-to-surface mode vehicles, etc.) ones Surface target detection range, km: detection of coastline and ground mapping

AIRBORNE RADARS destroyer/motor boat 250/130 at high resolution within the preset angular periscope 30 sector Number of simultaneously tracked identification and tracking of surface tar- surface targets 10, max gets and precise measurement of their Air-to-air mode coordinates in the circular scanning zone Target detection range, RCS = 5m2, km 70 search and detection of air targets Mapping mode detection of dangerous weather phenomena Mapping range, km 250, max and determination of their coordinates Range and azimuth resolution, m x m: solution of navigation tasks by coordinates at mapping range of up to 40 km 20 x 20 of detected radio-contrast terrain features at mapping range of up to 10 km 5 x 5 information support for employment of Meteo mode guided missiles. Detection range of weather phenomena/ dangerous turbulent areas, km 0.1 to 260 0.1 to 200 Weight, kg 100

104 ROSOBORONEXPORT radar ensures: designed forhelicopters. and multifunctionradar limeter-wave multimode search-and-rescue operations. ters, airpatrolling and of aircraft andhelicop- and navigationsupport ed formeteorological coherent radardesign- In the air-to-surface mode: In theair-to-surface Airborne Radar GUKOL-7 Airborne Radar GUKOL-3 Scanning sector,deg: Maximum range,km: Basic specifications egt g23,max Weight, kg Detection range,km: The Gukol-7isamil- The Gukol-3isa The Gukol-7airborne The Gukol-3airborneradarensures: zmt ±40 18 azimuth mapping oe ie0.8,max 30,max +10to-30 weather phenomena power line obstacle 5, elevation RCS ≥10m target detectionrange, max detection ofweatherphenomenaturbulent ground mappingwithzoomingand“freezing” modes files ofweatherphenomena generation ofhorizontalandverticalpro- helicopter flights zones, whichare dangerous toaircraft/ (also atlowaltitudesandinsurfaceclutter) mination oftheirzonesanddangerlevels of dangerous weatherphenomena,deter- airspace surveillance,includingdetection 2 ROSOBORONEXPORT WEATHER ANDFLIGHTCONTROLAIRBORNERADARS at least10 In themeteomode: In thelow-altitudeflightmode: Scanning sector,deg: Detection range,km: Basic specifications egt g14 305 Weight, kg Antenna diameter,mm nen ye SA Antenna type zmt ±60 300 azimuth weather phenomena lvto ±30 200 50 elevation surface targets high turbulentareas signals. ters andgenerationofcollisionwarning detection ofapproaching aircraft/helicop- level phenomena andevaluationoftheirdanger detection andidentification ofweather crew aboutpossiblecollisionwiththem. coordinates andwarningofthehelicopter and structures), determinationoftheir transmission linepoles,high-risebuildings artificial obstacles(smoke-stacks,power detection ofdangerous ground naturaland 10 km,respectively. ter atmaximumranges-1kmand cles aheadoftheaircraft/helicop- detection ofground andairobsta- safety objects toensure navigational ground mappingtodetectsurface helicopter. sites andapproach/landing of detection ofhelicopterlanding coordinates tures andmeasurement oftheir and radio-contrastterrainfea- identification ofsurfacetargets copter mining thepositionofheli- of theircoordinates whendeter- rain features andmeasurement detection ofradio-contrastter-

105 AIRBORNE RADARS AVIONICS GUKOL-10 Airborne Radar

acquisition of radar-contrast surface targets and determination of their coordinates for navigation purposes acquisition of unorganized landing grounds, runways and landing on them moving surface target indication.

In the low-altitude flight mode: AVIONICS AVIONICS

detection of natural and man-made ground obstacles (stacks, power transmission lines, high-rise buildings and structures) The Gukol-10 weather/navigation radar is a that might endanger flights multifunctional two-band (centimeter and mil- determination of coordinates and obstacle limeter bands) coherent radar designed for all- edges and warning of the crew about pos- weather and round-the-clock weather/naviga- sible collision with them. tion support of aircraft and helicopter flights,

AIRBORNE RADARS including information support of flights at low In the meteo mode: altitudes. detection of weather phenomena, determi- Glukol-10 airborne radar ensures: nation of their location, boundaries and danger level In the air-to-surface mode: detection of turbulent zones in weather ground mapping in the mode of real beam phenomena, dangerous for aircraft flights in the millimeter band and usage of syn- generation of horizontal and vertical pro- thetic aperture in the centimeter band files of weather phenomena.

Basic specifications In the air-to-air mode: Max range, km: mapping 200 detection of air targets and determination Max detection range, km: of their coordinates to provide safety of ground obstacles 5 flights and prevention of collision with weather phenomena 300 them. air targets (RCS=10 m2) 30 Scanning zone, deg: azimuth 180 elevation 90 Weight, kg 45

106 ROSOBORONEXPORT air/ground-to-air missileandprovide: include: imtr m20–20350 330 200 400 – – 200 600 Diameter, mm Length (w/oradome),mm Reaction time Basic specifications egt(/ aoe,mx g 4581 13 10 8 14.5 Weight (w/oradome),max,kg Lock-on rangeoftarget Active radarseekers are designed forair-to The 9B-1103Mfamilyofactiveradarseekers after apreliminary tlat m 01 540 1.0 25 1.0 13 1.0 20 1.5 2-min activation,max,s at least,km with 5-sq.mRCS, gets usingpre-launch targetdesignation search, lock-onandtrackingofmovingtar- (diameter 350mm). 9B-1103М0150 activeradarseekers (diameter 200mm) 9B-1103М0150 activeradarseekers seekers (diameter150mm) upgraded 9B-1103M0150activeradar active radarseekers 9B-1103M multifunctionalpulseDoppler 9B-1103M ROSOBORONEXPORT diameter 150mm 9B-1103M 9B-1103М 9B-1103М-150 9B-1103М-200 9B-1103М-350 9B-1103М-1509B-1103М-200 9B-1103М diameter 200mm Operating modes: inertial guidanceusingradioupdates fire-and-forget puter. enter anewprogram intotheairbornecom- line totheweaponcontrol system. transmitted viaadigitalcommunications reception anddecodingofupdatesignals and missile-to-targetclosingspeed angular coordinates, targetangularspeed systems from airborneradars orantiaircraft generation ofmissilesteeringcommands reprogramming modewhentheusercan 9B-1103M 9B-1103M Active RadarSeekers diameter 350mm 9B-1103M Family

107 ACTIVE RADAR SEEKERS AVIONICS RVV-AE Air-to-Air Missile Active Radar Seekers

The multifunction Doppler-monopulse active radar seeker of the RVV-AR air-to-air missile provides:

search, lock-on and tracking of moving targets using target designation from the missile’s inertial control system angular coordinates, target angular

AVIONICS AVIONICS speed and missile-to-target closing speed reception and decoding of update signals generation of missile steering commands transmitted to the weapon’s control system.

Operating modes: fire-and-forget inertial guidance using radio updates and active terminal guidance. ACTIVE RADAR SEEKERS

Basic specifications Active radar seeker ensures RVV-AE missile launch from of MiG-29 aircraft in FHS at range, km 80, max Reaction time after a preliminary 2-min activation, s 1, max Length (w/o radome), mm 604 Weight (w/o radome), kg 16, max Diameter, mm 200

108 ROSOBORONEXPORT enhancement. in group missions,andcombatefficiency craft control automationcombatinteroperation other frequency bands,datatransferequip- tions systemsoperatinginHF, VHF, UHF, and automatic control ofaircraft combatoperations. nels invariousfrequency bands,andensure face andair-to-surfacecommunicationschan- reliable digitaldatatransferviasurface-to-sur- The K-DlAEandK-DlUEsystemsprovide air- Aircraft communicationssystemsprovide The systemscanbefitted onanyaircraft. The systemscomprisesatellitecommunica- Standard CommunicationsSets K-DIAE/K-DIUE ROSOBORONEXPORT receivers connectedtoasingleantenna. ous operationofseveraltransmitters and ation, andmultiplexers provide forsimultane- equipment. systems, switching,datacoding,andECCM ment, special-purposecomputers, intercom 8MTV, Mi-24,Mi-171,andMi-172helicopters. and theKa-27M,Ka-31,Ka-50-2,Ka-60,Mi- MiG-29, MiG-31,Su-39,andYak-130 aircraft, nation field. ations, andformingofintegratedtargetdesig- support, self-sustainedtask-force aircraft oper- compatibility injointoperations,navigation tion ofcockpitinstrumentation,provides asset Lightning-proof antennasensure stableoper- The AT-E terminalisdesigned for theMiG-21, The AT-E terminalensures full-scaleintegra- COMMUNICATIONS SYSTEMS Transfer Terminal Airborne Data AT-E

109 COMMUNICATIONS SYSTEMS AVIONICS Airborne Communications System for AWACS Aircraft

The airborne communications system for AWACS aircraft incorporates communications equipment operating in the VHF, UHF and HF frequency bands, a satellite communications unit,

AVIONICS AVIONICS voice communications and switching equipment, data transfer and message recording equipment, a comput- erised automation system, and data encryption equipment. The system is mounted on the A-50E aircraft.

Airborne Communications System equipment, data encryption equipment, auto- for Military Transport Aircraft matic relay device, data transfer equipment, joint control post, and radio multiplexers.

COMMUNICATIONS SYSTEMS COMMUNICATIONS The system includes HF1, HF2, VHF, UHF, and The system is designed to be mounted on the HF radio stations, radio relay stations, intercom An-32, Il-18, Il-76, and Tu-154 aircraft.

BKS-2ME Small-Size Communications System for Frontline Aircraft and Helicopters

The system is designed as part of the upgrade package for the radio communications suite of Su-27SK aircraft and the Ka-27, Mi-8, and Mi-24 helicopters. The system comprises the TsIMSS communications unit, Bozon-2M and Burka-M radio stations, and ATM-2 terminal.

110 ROSOBORONEXPORT voice andautomaticdataexchangecommuni- designed forground control stationstoprovide Functional capabilities: The ground communicationssystemis digital map acquisition, processing anddisplayonthe and correcting errors decryption ofaccepteddataplusdetecting cation channels sion ofdataviaexchangecommuni- anti-noise encryptiontoprovide transmis- cryptographic protection ofdata protection againstfalsified dataentryand system equipment automatic control andmonitoringofthe nication withaircraft of-sight voiceanddataexchangecommu- DMW radiochanneltoprovide beyond-line- cation withaircraft sight voiceanddataexchangecommuni- MW-DW radiochannelstoprovide line-of- ROSOBORONEXPORT are provided. craft. Fixed andmobileversions ofthesystem cation withtheSu-30MKandSu-27SKMair- Ground CommunicationsSystem and-night. operating conditions–continuous,day- ment status accepted informationonthesystemequip- automatic recording oftransmittedand messages including automaticreceipt ofemergency exchange communicationchannels, communication withaircraft viadata two-way dataandstandard command route dataaccording toflight mission flight navigationdatafrom friendlyaircraft coming from ground andaircraft radars i nformation onair(ground, sea)targets,

111 COMMUNICATIONS SYSTEMS AVIONICS K-DLI-03-1 Standard Airborne Data Communications Set

The K-DLI-03-1 standard airborne data com- protection against falsified data entry into munications set is designed to provide voice and voice and digital radio communication digital (data exchange) radio link between the channels, immunity to enemy electronic Su-30MK2 and Su-27MK aircraft and with countermeasures in the DMW, MW and DW ground control stations via the MW-DW and SW bands radio channels. universal interface to cooperate with air- The set provides: craft systems and ACS ground communica- connection of aircraft to the Air Force auto- tion centers

AVIONICS mated control system (ACS) reconfiguration and flexibility of architec- rise of effectiveness in combat of up to ture 25% automation of equipment monitoring cooperation when aircraft operate in inde- installation on any aircraft pendent teams simplicity of maintenance. assistance to pilots due to data transfer automation COMMUNICATIONS SYSTEMS COMMUNICATIONS

KARDAN Telephone Encryption Equipment

The Kardan telephone encryption equipment is designed for all types of aircrafts, including as part of standard communication systems, and ensures encryption of traffic between flight crews and personnel of ground control stations when calls are transmitted via communication channels digitally in synchronous mode. This equipment guarantees security of information by means of a unique cryptographic algorithm.

112 ROSOBORONEXPORT ELECTRONIC WARFARE SYSTEMS OLEN Digital Information Encryption Equipment

cation systems. It is designed to provide encryption of digital communication between flight crews and personnel of ground control stations when information is transmitted digitally in sim- plex mode. This equipment guarantees security of infor- The Olen digital information encryption mation by means of a unique cryptographic equipment can be installed on any aircraft and algorithm and protection against falsified data also can be used as part of standard communi- entry made cryptographically. AVIONICS

L-150 PASTEL Radar Warning System

acquisition, tracking, and illumination modes. The Pastel is capable of prioritising the radars detected, and providing the crew with information on the most dangerous ones. It can also set off a sound alarm when the aircraft is subjected to hostile illumination. The L-150 can be installed inside the aircraft or in an unshaded container.

The L-150 Pastel radar provides detection Basic specifications ELECTRONIC WARFARE SYSTEMS ELECTRONIC WARFARE and direction-finding onto radars illuminating Frequency band, GHz 2-18 the carrier aircraft, as well as radar seekers of Radar signal types quasi-continuous, air-to-air and surface-to-air missiles. continuous, pulse The radar is designed to detect, including Enemy radar location accuracy, deg 3-10 doing so in the track-while-scan mode, and find Radar types stored in the database 128 direction to air defence systems and aircraft by Throughput, MHz 1 emissions of their radars operating in the target Weight (without display), kg 45 SUKHOGRUZ Electro-Optical Countermeasures System

The Sukhogruz man-portable heat-seeking surface-to-air mis- system is design- siles, such as the Chaparral, Red Eye, and ed to protect the Strela MANPADS. aircraft from heat- seeking missiles. It covers a 50- Basic specifications degree cone- Modulation frequencies 8 frequencies in shaped sector in 700-1,700Hz band the rear hemi- Mode switching time, min 5 sphere. Emitted power, VA 6,000 The Sukhogruz Weight, kg: effectively jams transmitter 28 control unit 3.5

ROSOBORONEXPORT 113 ECM EQUIPMENT Helicopter and Aircraft Electro-Optical System

Intended to protect aircraft and helicopters from air-to-surface missile (ASM), surface-to- air missile (SAM) and air defense gun (ADG) systems by detecting threats and providing appropriate countermeasures

Multi-purpose control Control device indicator panel AVIONICS AVIONICS

Laser countermeasures equipment Active jamming radar

ELECTRONIC WARFARE SYSTEMS ELECTRONIC WARFARE Optronic countermeasures equipment Irradiation warning radar

Flare/chaff dispenser UF locator

Provides: detection of launching of air-to-air and surface-to-air missiles by emission of their acquisition and identification of air-to-air engines and surface-to-air missiles fitted with radar radio interference against radars and seekers and determination of their direc- active seekers of air defense weapons tion on ASMs, SAMs and ADGs by emis- infrared jamming of against missiles sions of their radars and active radar seek- equipped with IR seekers ers that employ continuous, quasi-continu- control of chaff/heat flare dispensing ous and pulse types of radiation distribution of the system elements laser illumination warning between the threatened facilities of air defense.

114 ROSOBORONEXPORT also beusedasapartofthesystem. craft/helicopter. Aself-containeddisplaycan ous threats onamultifunctiondisplayoftheair- if necessary. the systemcanbeinstalledinexternalpods craft/helicopter fuselage.Separateelementsof in theformofunitsinstalledinsideair- egt g18(with4optronicunits) morethan6 conical,withtopangleof100 10 0.4to1.1 Weight, kg Time ofresponse,sec Missile launchacquisitionrange,km optronic unit(ОU),deg: D–J Scan-sector: Missile attack warning radar Basic specifications 128andmore Weight, kg 120%fromtheseradars range Range ofoperatingwavelengths,µm Accuracy ofbearingmeasurement,deg Scan-sector, deg: Laser illuminationwarning Basic specifications Weight, kg Number ofradarmodesstoredinmemory Dynamic range,dB Illuminating radaracquisitionrange Accuracy ofdirectionfinding(RMSE),deg: Operating frequencyrange,GHz Scan-sector, deg: Radar warning Basic specifications cuayo ern esrmn,dg 0.5 Accuracy ofbearingmeasurement,deg Incorporates: The optronic systemequipmentisdesigned The systemprovides displayofmostdanger- zmt 360(with4optronicunits) azimuth elevation 3to10(dependingonangleofapproach) elevation azimuth elevation azimuth elevation azimuth flare/chaff dispenser. optronic countermeasures equipment active jammingradar missile attackwarningradar laser illuminationwarningreceiver radar warningreceiver control device receiver ROSOBORONEXPORT receiver means ofthebuilt-intestsystem. aircraft/helicopter viaMILSSTD1553B. ensures datacommunicationwiththesystemsof commands forcountermeasures equipmentand electronic suitedatabase,transmitssteering The system’sserviceabilityischeckedby It provides foron-linereprogramming ofthe 60 (+20/-40) 360 360 0.1 15 30 40 90 90 60

115 ELECTRONIC WARFARE SYSTEMS AVIONICS Basic specifications Active jamming radar Jamming sector, deg: azimuth 120 elevation 60 Operating frequency range G – J Energy potential, W 2,000, max Types of jamming RF noise flickering quasi-continuous range- and speed-distorting amplitude- and phase-modulated Number of simultaneously suppressed radars 2 Weight, kg 51.5 AVIONICS

Basic specifications Optronic countermeasures equipment Jamming sector, deg: azimuth 360 elevation 90 (+30 -60) Beam width, deg 7 Radiation intensity in IR band, kW/sr spectrum band IR 1 3.0 spectrum IR 2 1.2 Types of jamming guided, space pulse-modulated Weight, kg 80

ELECTRONIC WARFARE SYSTEMS ELECTRONIC WARFARE Basic specifications Flare/chaff dispenser Type of cartridges dispensed antiradar infrared Caliber of cartridges dispensed, mm 26; 50 Number of cartridges 128, max Mode of operation automatic Weight, kg 32.7

116 ROSOBORONEXPORT AEROSPACE SYSTEMS

ARMAMENT

ROSOBORONEXPORT 117 R-73E Short-Range Air-to-Air Missile

The R-73E missile is designed to intercept and destroy in close air combat manoeuvrable manned/unmanned air attack and reconnaissance assets by day and night, from all directions, in head-on and tail-on engagements, against the earth background and in aggressive ECM environment. seeker, the missile is capable of engaging not The missile features an all-aspect IR homing only receding, but also approaching and collid-

ARMAMENT system, a proximity fuse and a rod-type war- ing-course air targets. head. The missile can attack targets in any initial The R-73E is one of the world’s first all-aspect position at designation angles of ± 45 degrees short-range missiles. Owing to the sensitive IR flying at speeds of up to 2,500 km/h at altitudes ranging from 0.02 to 20 km. Minimum range of Basic specifications launch is only 300 m when fired in the rear hemi- Max launch range, km 30 sphere. Weight, kg: The R-73E missile is superior to the world’s launch 105 best counterparts in terms of basic characteris- warhead 8.0 tics on which depends its combat effectiveness Target g-number 12

AIR-TO-AIR MISSILES Fighter-type target hit probability 0.6-0.8 in dogfight. Dimensions, m: The missile is designed to arm the length 2.90 MiG-21-93, MiG-29, Su-39, Su-27 and Su-30 diameter 0.17 aircraft. horizontal stabiliser span 0.51 R-33E Long-Range Air-to-Air Missile

The R-33E missile is designed to engage single and multiple targets within all-round attack zone in all weather conditions, with natural interference, enemy ECM, and evasive manoeuvring against the earth background or in free airspace by day and night. It features a normal aerodynamic configuration The R-33E is designed to arm the MiG-31E with upper fins folded to fit suspension under the aircraft. fuselage. In the initial flight stage the missile is guided by the inertial system, and in the terminal stage by the semi-active radar homer. The missile Basic specifications has a solid propellant, single-chamber two-mode Max launch range, km 120 engine and a high-explosive fragmentation war- Weight, kg: head. launch 490 Four missiles are attached to recessed fuse- warhead 47 lage hardpoints. Launch of the four missiles Target g-load 4 ensures simultaneous engagement of up to Fighter-type target hit probability 0.65 four targets flying at different altitudes with dif- Dimensions, m: ferent speeds, as well as of a single target by length 4.15 several missiles. The targets are engaged at diameter 0.38 altitudes ranging from 0.05 to 28 km. horizontal stabiliser span 1.1

118 ROSOBORONEXPORT ignation anglewithin±50degrees forthesemi- increased powerengine. tion. inertial navigationguidancewithradiocorrec- includes asemi-activeradarhomingheadand destabilisers. pivoting wingconfigurations, withtandem evasive manoeuvring. ground, inspiteofsevere ECM, counterfire and directions, againsttheearthandseaback- night, inadverse weatherconditions,from all to intercept anddestroy airtargets bydayand a anhrne m6 256 80 0.6-0.8 65 0.6-0.8 62.5 0.6-0.8 0.6-0.8 60 Dimensions, m: Fighter-type targethitprobability Target g-load Weight, kg: Max launchrange,km Basic specifications The R-27air-to-airguidedmissileisdesigned The R-27missilelocksonatargetatanydes- The R-27ER1andR-27-ET1missileshavean The R-27T1isfitted withanIRseeker. The R-27R1missileguidancesystem The missile’sdesigncombinescanard and imtr02 .602 0.26 4.49 39 0.23 0.97 3.80 39 0.26 4.775 0.97 0.23 4.08 39 0.97 0.97 39 343 245 horizontal stabiliserspan diameter length 350 warhead launch 253 ROSOBORONEXPORT Medium-Range Air-to-AirMissileFamily -71R2E1R2T R-27ET1 R-27T1 R-27ER1 R-27R1 ness oftheweaponsystem. anti-jamming capabilityandcombateffective- homing headsofvarioustypesincrease integral 27 andSu-30aircraft. launch is500m. can reach 10km.Minimumtail-onrangeof elevation (depression) inthecarrierlevelflight ranging from 0.02to27km.Maximumtarget ing atspeedsofupto3,500km/haltitudes sile launch.Themissilecanengagetargetsfly- seeker. active radarhomerand±55degrees fortheIR The R-27isdesignedtoarmtheMiG-29,Su- 8888 The carrierg-loadcanattain5gatmis- The R-27missileswith R-27

119 AIR-TO-AIR MISSILES ARMAMENT RVV-AE Medium-Range Air-to-Air Missile

The RVV-AE missile is designed to engage fighters, attack aircraft, bombers, helicopters and military transport aircraft by day and night, in all weather conditions, from all directions, against the earth and sea background with enemy ECM and evasive manoeuvres. The RVV-AE missile has an active radar homing head and inertial guidance system with radio

ARMAMENT correction, which allows in-flight target acquisition and re-targeting. The active radar homer improves autonomy of the carrier and ensures effective implementation of the "fire-and-forget" The RVV-AE missile family features a modular principle. design with a rod-type warhead. The RVV-AE can engage targets flying at Basic specifications speeds of up to 3,600 km/h at altitudes ranging Max launch range, km: from 0.02 to 25 km. Minimum range of launch against fighter-type targets 50 in the rear hemisphere is 300 m. Maximum tar- against bomber-type targets 80 get elevation (depression) at the missile carrier Weight, kg:

AIR-TO-AIR MISSILES level flight can attain 10 km. The RVV-AE launch launch 175 does not impose limitations on the carrier’s g- warhead 22.5 load. Target g-load 9 Fighter-type target hit probability 0.6-0.7 Dimensions, m: length 3.60 diameter 0.20 horizontal stabiliser span 0.70

120 ROSOBORONEXPORT rudbsd i-andsea-bornecarriers. ground-based, air- Igla-S, IglaandIgla-1missilesfrom different mated remote singleorsalvolaunchingofthe isl air,m 72 1,625 provided notmorethan13 Missile calibre,mm Missile length,mm ‘Fire-and-forget’ principle Into-action time 10to3,500 upto6,000 Airspeed oftargetsengaged,m/s Altitude oftargetsengaged,m Target engagementrange,m Basic specifications yeo aha HE,impact-delayaction, Type ofwarhead yeo pia ekr two-spectrum, Type ofopticalseeker egto isl/aha,k 11.7/2.5 Weight ofmissile/warhead,kg The Strelets setisdesignedtoprovide auto- It incorporates: edo upto400 head-on nprutupto320 in pursuit kit ofconnectors. links withfire control systemsplatforms for combatoperationandprovides comms that receives commands,selectsmodule communication andcontrol equipment launch ations, includinglock-onbytheseekerand ply sources andtoensure pre-launch oper- two Igla-typemissilesandfourpowersup- universal launchmoduledesignedtocarry ROSOBORONEXPORT jamming-proof proximity Control EquipmentandLaunchModuleSet ronment (heatflares). a targetintheelectronic countermeasures envi- near-miss. only incaseofadirect hit,butalsoincaseof head, whichallowdestructionofthetargetnot due totheproximity fuzeandupgradedwar- 6.0 kmwithaheatprobability of0.8to0.9. cles head-onandinpursuit atrangesofupto cruise missiletypesandremotely pilotedvehi- as welllow-altitudeandstealthtargetsofthe to destroy dayandnightaircraft andhelicopters with apassivetwo-bandIRseekerisdesigned fo O't isl anh,s6.6 20,max 72 Weight ofcontrolequipment,kg Weight withfullyarmedmodule,kg (from 'On'tomissilelaunch),s Reaction time upto4/8 Number oflaunchmodules/missiles Basic specifications The heatseekerprovides reliable selectionof High effectiveness ofthemissile isprovided The Igla-Sair-to-airguidedmissileequipped for Igla-Type GuidedMissiles STRELETS Guided Missile IGLA-S

121 AIR-TO-AIR MISSILES ARMAMENT Kh-22E Supersonic Long-Range Air-to-Surface Missile

phase the missile assumes radar homing. The missile features an active radar seeker and an HE shaped-charge warhead. The Kh-22E is part of the weapons suite of The Kh-22E supersonic air-to-surface missile the Tu-22M3E bomber. is designed to engage radar-contrast mobile and stationary targets at a long range. Basic specifications ARMAMENT The combined guidance system includes an Max range, km up to 290 autonomous flight control subsystem and a homing subsystem. The former stabilises yaw En-route speed, Mach number 2.2-3.4 and roll angles during the first 25 seconds of Launch weight, kg 5,820 the flight, evenly increasing the pitch angle as Warhead weight, kg 900 the homing head keeps tracking the target. In Dimensions, m: the vertical plane the autonomous flight control length 11.65 system ensures climb to the cruising altitude, diameter 1.81 subsequent level flight, and dive. At the diving wing span 3.00 Kh-29 Short-Range Air-to-Surface Missile Family

AIR-TO-SURFACE MISSILES AIR-TO-SURFACE The Kh-29 family is designed to engage sea- surface and ground targets: reinforced concrete shelters, bridges, buildings, warehouses, concrete runways, warships and amphibious landing craft. The Kh-29T missile features a passive TV homing system. The vertical plane control system operates in two modes, namely autonomous control and homing. The autonomous control mode is activated at the initial stage of The Kh-29T arms the Su-27UB, Su-30MK, the flight, and the homing mode takes over at Su-35, Su-39, MiG-27K, and MiG-29M aircraft. the terminal stage. The Kh-29TE extended The Kh-29L missile features semi-active range version is developed. laser guidance providing for the proportional approach method. If the carrier is equipped with the Prozhektor target Basic specifications illumination station, the missile hom- Kh-29L Kh-29T Kh-29TE ing is used in both planes. If the carrier Launch range, km: is fitted with the Klyon and Kaira illumi- maximum 8-10 10-12 30 nation stations, then the vertical plane minimum 3 control system realises three-stage Launch altitudes, km 0.2-5 0.2-5 0.2-10 guidance to increase the missile Launch speeds, km/h approach angle to the target. Launch weight, kg 660 685 690 The Kh-29L is in the inventory of the Warhead weight, kg 320 320 320 Su-25, Su-27UB, Su-30MK, Su-39, Dimensions, m: MiG-27K, and MiG-29M aircraft. length 3.900 3.900 3.875 diameter 0.38 0.38 0.38 empennage span 1.10 1.10 1.10

122 ROSOBORONEXPORT trols themissile flight tothetargetarea. nal sources. Theinertialguidancesystemcon- missile bothfrom thecarrierfacilitiesandexter- seeker. Target designationdatacanbefedtothe storage. head. Itiscontainerisedfortransportationand sile hasanHEshaped-chargeincendiarywar- ters, vessels,andcoast-basedcarriers. Themis- booster enablesitsemploymentfrom helicop- turbojet engine.Thedetachablesolidpropellant with X-shapedcontrol surfaces.Itispowered bya craft. types, includingships,coastalsystems,andair- sels. Themissilecanbemountedoncarriers ofall of upto5,000-tdisplacement,andtransportves- sile boats,torpedogunboats,surfaceships Su-35, MiG-29SMT, andMiG-29Kaircraft. Kh-31P missilearmstheSu-30MK,Su-32, radars (dependingontheseekertype).The emitting radars ofSAMsystemsandacquisition and MiG-29Kaircraft. Su-32, Su-35,MiG-29M,MiG-27M,MiG-29SMT, mode isselectedbythecrew. the targetafter missilelaunch.Theengagement internal guidancemodetheseekerlocksonto the missileisstillathardpoint, andinthe bined modetheseekerlocksontotargetwhile seeker hastwoengagementmodes:inthecom- seeker andanHEshaped-chargewarhead.The surface shipsofuptodestroyer class. figuration withX-shapedcontrol surfaces. Missile Family Supersonic Air-to-Surface Kh-31 The Kh-35Emissileisdesignedtoengagemis- The Kh-31missilefeatures astandard con- The Kh-35Ehasanactivejamming-proof radar The Kh-35Efeatures anormalconfiguration The Kh-31Pmissileisdesignedtoengage The Kh-31AisintheinventoryofSu-30MK, The missileisequippedwithanactiveradar The Kh-31Amissileisdesignedtoengage ROSOBORONEXPORT Ka-28 helicopters. 29SMT, Su-30,Su-35aircraft, andtheKa-27 tics astheKh-35E,armsMiG-21,MiG- assets. plicates itsinterception byship-basedSAM tude flight (3-5maboveseasurface),whichcom- increased attheexpenseofextremely low-alti- air targethasbeendeveloped. aha egt g145 * -helibornevariant 520(610*) 0.8 Dimensions, m: 0.32≤M≤0.9 Warhead weight,kg Launch weight,kg En-route speed,Machnumber Launch speeds,km/h Launch range,km: Basic specifications aha egt g9 87 600 94 610 600-700 0.1-15 Warhead weight,kg 600-700 Launch weight,kg 600-1,250 0.1-10 En-route speed,m/s 600-1,250 Launch speeds,km/h Launch altitudes,km Launch range,km: Basic specifications Dimensions, m: The Kh-35Umissilewiththesamecharacteris- The combateffectiveness of themissileis On thebasisofKh-31missileMA-31 i . 15 upto110 7.5 25-50 min max imtr0.42 1.33 3.85(4.40*) 5 130 empennage span diameter length minimum maximum 0.36 4.70 0.914 0.36 4.70 0.914 empennage span diameter length Anti-Ship Missile h3AKh-31P Kh-31A Kh-35E

123 AIR-TO-SURFACE MISSILES ARMAMENT Kh-59ME Medium-Range Air-to-Surface Missile missile approaches the target area, its TV homing head turns on to broadcast the target image to the carrier aircraft at a range of up to 140 km. Two warhead types are available: shaped-charge fragmentation and cluster ones. The missile arms the Su-30MK aircraft. ARMAMENT The Kh-59ME missile is designed to engage Basic specifications pinpoint surface targets with the coordinates Max launch range, km 115 preset before launch, in fair weather at daytime. Flight speed, Mach number 0.72-88 The missile features a tailless configuration Cruising altitude, km 0.05-1.0 with X-shaped control surfaces. The power Launch weight, kg 930 plant comprises a turbofan engine and a boost- Dimensions, m: er. The missile is stored and transported in a length 5.7 sealed container. diameter 0.38 At the initial flight stage the missile is con- empennage span 1.30 trolled by its inertial guidance system. As the AIR-TO-SURFACE MISSILES AIR-TO-SURFACE KORNET-E Antitank Missile System

Helicopters can use guided missiles being the versatile versions of the Kornet-E antitank system. Missiles can destroy reactive-armored targets, fortifications and firing positions. There are missile derivatives that have both a tandem shaped-charge warhead and a thermobaric high-explosive and incendiary warhead. The missile control system is semiautomatic against laser beam and countermeasures- immune. Missiles require no maintenance work in service and in storage for 10 years and need no The 9М133-1 missile with a tandem shaped- inspections before suspension aboard helicop- charge warhead destroys all modern and future ter. tanks as well as fortifications and field installations. Basic specifications The 9М133F-1 missile with a thermobaric Range of fire, m 100 to 5,500 warhead features a destructive effect compara- 9М133-1 missile armour ble to that of a 155 mm high-explosive frag- penetration, mm 1,000 to 1,200 mentation projectile and can destroy strong for- Calibre, mm 152 tifications, soft-skin materiel and other small Length, mm 1,200 targets. Weight of missile in container, kg 29 Temperature range, OC ±50

124 ROSOBORONEXPORT ROSOBORONEXPORT ating. active seekerstartsoper- target –lasersemi- tial andatthefinal-leg to sile totargetarea) –iner- target (positioningofmis- tial- andmedium-legto tions: atthemissileini- performs combinedfunc- missile control system tainer stage.Theguided head aspartofthesus- (HE) fragmentationwar- powerful high-explosive away boosterstageanda is equippedwithafall- bi-caliber guidedmissile ular guidedmissile.The Hermes supersonic mod- ment ofthesystemis air targets.Thebasicele- and engagelow-speed lations andfortifications, materiel, engineerinstal- day andnightarmored is designedtodestroy semi-active laserseeker weapon systemwitha The Hermesguided a ag ffr,k 15 Control system: Max rangeoffire,km Basic specifications ihmsielae,m 3,500,max with missileloaded,mm 1,000 Missile stagediameter,mm 500 Weight, kg: Average airspeedfor15km,m/s Max airspeed,m/s aha HE-fragmentation Length oflaunchtube Warhead It incorporates: ose 170 atleast28 booster warhead utie 130 110,max sustainer GM launchtube target-seeking inertial final-leg totarget initial- andmedium-legtotarget tion equipment. and documentationdatacommunica- hardware, consolesandcontrols, displays fire control systemthatincludescomputer with theoptronic system two-channel targetauto-trackerinterfaced with atwo-channellasertargetdesignator stabilized, day-and-nightoptronic system Guided Weapon System HERMES-A

125 AIR-TO-SURFACE MISSILES ARMAMENT SHTURM Antitank Guided Missile

The Shturm anti-tank guided missile is designed to destroy small-size mobile and stationary armoured ground targets and low-speed air targets. The missile features the canard configuration. It mounts one pair of folding control surfaces and four folding bow-shaped wings. The missile is transported and stored in a sealed

ARMAMENT launch tube. A single-channel semi-automatic radio command guidance system ensures alignment- technique guidance. In flight the missile spins Basic specifications around its longitudinal axis. The electronic equipment is jamming-proof and allows for Max launch range, km 5 simultaneous attack by a group of 10 helicop- Flight speed, m/s 350-420 ters against close-in targets. The narrow anten- Launch weight, kg 35 na pattern and relatively short cycle of radiation Warhead weight, kg 5.4 hamper enemy electronic countermeasures. Armour penetration, mm 560 The missile warhead can be of a shaped- Tank hit probability 0.65-0.9 charge fragmentation or fuel-air explosive type. Launch tube dimensions, m: The Shturm ATGM arms the Mi-24V, Mi-25 length 1.98 and Mi-35 helicopters. AIR-TO-SURFACE MISSILES AIR-TO-SURFACE height 0.37 width 0.33

ATAKA Antitank Guided Missile

The Ataka anti-tank guided missile is designed to engage small-size armoured ground targets, low-speed air targets, and weapon emplacements. It features the canard configuration. The missile has one pair of folding control surfaces and four folding bow-shaped wings. The sealed launch tube is used for transportation and storage of the missile. The missile is guided by radio commands. During the missile flight, the operator holds the stationary marker on the multi-role display aligned on the target, and adjusts the line-of- Basic specifications sight with the help of controls on the guidance Max launch range, km 6 panel until the missile hits the target. Flight speed, m/s 400 The missile has several warhead versions, Launch weight, kg 42.5 including the shaped-charge, HE/fragmenta- Warhead weight, kg 7.4 tion and fuel-air explosive ones. Armour penetration, mm 800 with ERA protection The missile arms the Mi-24V, Mi-24P and Mi- Tank hit probability 0.65-0.9 28 helicopters.

126 ROSOBORONEXPORT KAB-500 Guided Bomb Family

The bomb arms the Su-24M, Su-35, MiG-29M and Su-30MK aircraft. The KAB-500-OD bomb with a fuel-air explosive warhead is designed to engage personnel and ground targets in terrain accidents.

The KAB-500Kr guided bomb is designed to Basic specifications destroy a wide range of ground and sea-surface KAB-500Kr (-OD) ARMAMENT targets, including strongly protected and weak- Calibre, kg 500 contrast ones, using the fire-and-forget princi- Bomb weight, kg 520 (370) ple. Warhead weight, kg 380 (250) The KAB-500Kr can be used both singly and Dropping altitudes, km 0.5-5 in salvo, from level flight, dives and pitch-ups, Dropping speeds, km/h 550-1,100 by day and night (provided that the target is illu- Target hit accuracy (CEP), m up to 7 minated), against one or several spaced targets Dimensions, m: length 3.05 in a single attack. hull diameter 0.35 GUIDED BOMBS

KAB-1500Kr Guided Bomb with a TV Seeker

craft (fighter-bomber, attack aircraft). Bombing is accomplished by flying at altitudes of 1 to 8 km and at speeds of 550 to 1,100 km/h.

Basic specifications Weight, kg 1,525 Length, mm 4,630 Body diameter, mm 580 Fin assembly span, mm: folded 850 unfolded 1,300 Warhead weight, kg 1,170 Explosives, kg: high-explosive 440 piercing 210 The KAB-1500Кr guided bomb is designed fuel-air explosive 650 to destroy ground and sea-surface targets of Target hit accuracy (CEP), m 4 to 7 reinforced concrete shelter type, defence Guidance system TV-correlation industry facilities, warehouses and port termi- Fuze impact, with three nals. types of delay The КAB-1500Кr guided bomb is used as Conditions of practical part of the weapon’s systems of front-line air- application SWC

ROSOBORONEXPORT 127 KAB-1500 Guided Bomb Family

The KAB-1500L-F guided bomb is designed to destroy ground targets such as reinforced concrete shelters, warehouses, and defence industry facilities, as well as sea-surface targets. It has a feathered semi-active laser homing It is fitted with a TV homing head, and an HE head, and an HE warhead. warhead. The KAB-1500Kr bomb is also designed to These bombs are used by the Su-24M,

ARMAMENT destroy strong ground and sea-surface targets. Su-30MK, and Su-32 aircraft.

Basic specifications KAB-1500L-F KAB-1500Kr Calibre, kg 1,500 1,500 Bomb weight, kg 1,525 1,525 Warhead weight, kg 1,170 1,170 Dropping altitudes, km 1-8 1-8 GUIDED BOMBS Dropping speeds, km/h 550-1,100 550-1,100 Target hit accuracy (CEP), m up to 10 up to 7 Dimensions, m: length 4.58 4.63 hull diameter 0.58 0.58

UMGT-1ME Self-Homing Torpedo

The UMGT-1ME torpedo is designed to destroy submerged and surfaced submarines. A hydroacoustic active/passive homing system guides the torpedo onto a manoeuvring target irrespective of the target’s noise level. The homing system controls the torpedo’s course, depth, and roll parameters, provides its manoeuvring in two planes, and guides the torpedo to the proximity fuse activation area or directly onto the target. The torpedo's modular design facili-

Basic specifications tates its maintenance. A practice ver- Torpedo weight, kg not more than 725 sion is available for training purpos- Explosive charge weight, kg 60 es. Dimensions, m: The UMGT-1ME torpedo is length 3.845 designed for arming ASW aircraft and diameter 0.400 helicopters with internal suspension Parachute container diameter, m 0.500 (in weapon bays). Service life, yrs up to 10

128 ROSOBORONEXPORT APR-3E Air-Launched ASW Missile

The APR-3E Airborne ASW missiles, in contrast to conven- ASW missile is tional torpedoes, have maximum operating speed designed to des- in the target acquisition and detection modes, troy submarines accelerated approach to the target with destruc- moving at a speed of 80 km/h at a depth of up to tion before the target can apply countermeasures. 600 m. Underwater space is scanned by the hydroa- Basic specifications Weight, kg 550 coustic homing system during the missile’s gravi- Warhead weight 100 ty-induced descent on a spiral trajectory with the (TNT equivalent), kg ARMAMENT missile engine shut. Depth range, m up to 800 The APR-3E missile is powered by a turbo water- Speed, km/h up to 120 jet solid-propellant motor. Hit probability 0.80-0.85 The missile can arm the IL-38 aircraft and the Dimensions, m: Mi-14 and Ka-28 helicopters. length 3.60 calibre 0.35

The S3V guid- S3V ed bomb is ASW Guided Bomb designed to des- The S3V bomb arms the Mi-14 and Ka-28 troy submarines helicopters. operating in the following modes: surfaced, at periscope depth, submerged to the maximum Basic specifications depth of 600 m, or lying on the sea bottom. Bomb weight, kg 94 The S3V bomb equipped with a shaped- Explosive charge weight, kg 19 charge HE warhead features excellent cost-effi- Submerging speed, m/s 16.2 ciency. Its hit probability exceeds by 1.2 to 1.5 Glide angle, deg up to 60 AIR-TO-SUBMARINE GUIDED WEAPONS times that of standard ASW air bombs at mod- Trajectory correction system erate depths, and by 4 to 8 times at great diagram sector, deg 120 depths of up to 600 m. In storage the bomb Dimensions, m: does not require any special maintenance or length 1,300 testing. calibre 211

The MDM-3 MDM-3 airborne bot- Airborne Bottom Mine tom mine is designed to mine dropping and enhanced shock resistance. engage sub- The mines are carried by the aircraft in the marines and displacement surface ships of all same way as bombs. classes. The mine features three-channel proximity Basic specifications fuse with acoustic, electromagnetic and hydro- Mine weight, kg 525 dynamic channels. The multichannel design Explosive charge weight, kg 300 protects the mine from modern mine sweepers, Operational depth, m 15-35 and provides jamming-proof capability within Aircraft speed, km/h 1,000 one-year service life. Dimensions, m: The mine’s design ensures high-accuracy length 1,580 diameter 450

ROSOBORONEXPORT 129 FAB-500 M62 High-Explosive Bomb

Basic specifications Bomb weight, kg 500 Drop altitude range, km 0.57-12 Drop speed range, km/h 500-1,900 The FAB-500 M62 HE bomb is designed to Dimensions, m: destroy defence industry facilities, light length 2.47 armoured vehicles, railway junctions, fortifica- diameter 0.4 tions and personnel. ARMAMENT

OFAB HE Fragmentation Incendiary

AIR BOMBS Bombs

The OFAB HE fragmentation incendiary bombs are designed to destroy light armoured materiel, fuel stocks and other targets by a combined HE, fragmentation, and thermal effect.

Basic specifications OFAB-500U OFAB-250-270 OFAB-100-120 Bomb weight, kg 515 268 123 Drop altitudes, km 0.05-8 0.5-12 0.5-15 Drop speed range, km/h 500-1,350 500-1,500 500-1,500 Dimensions, m: length 2.30 1.465 1.065 diameter 0.40 0.325 0.273

OFZAB HE Fragmentation Incendiary Bomb

The OFZAB HE fragmentation incendiary materiel, fuel stocks and other targets by a bomb is designed to destroy light armoured combined HE, fragmentation and thermal effect.

Basic specifications Bomb weight, kg 500 Drop altitudes, km 0.9-12 Drop speed range, km/h 550-1,850 Dimensions, m: length 2.385 diameter 0.45

130 ROSOBORONEXPORT obwih,k 50 525 0.2-12 477 0.03-5 500-1,500 600-1,200 Dimensions, m: Drop speedrange,km/h 0.2-1 520 Drop altitudes,km Bomb weight,kg 500-1,100 Basic specifications Dimensions, m: Drop speedrange,km/h Drop altitudes,km Bomb weight,kg Basic specifications diameter 0.35 length 2.20 diameter 0.50 length 2.28 0.50 2.38 ROSOBORONEXPORT used toclearminefields. tected materielandpersonnel. Theycanalsobe designed todestroy industrialfacilities,unpro- bomb delivery. train pilots(aircrews) inround-the-clock and reinforced concrete shelters. command posts,communicationscentres designed todestroy underground dumps, ODAB-500PM ODAB-500PMV inltp light/smoke 50 upto35 0.2-25 upto16 Dimensions, m: 500-2,500 Smoke signalvisualtime,sec Light signalvisualtime,sec Signal type Drop speedrange,km/h Drop altitudes,km Bomb weight,kg Basic specifications The ODABfuel-airexplosivebombsare The P-50Tpracticebombisdesignedto The BetAB-500concrete-piercing bombis diameter 0.203 length 1.044 Fuel-Air ExplosiveBombs Concrete-Piercing Bomb BetAB-500 Practice Bomb ODAB P-50T

131 AIR BOMBS ARMAMENT M6/M6T Airborne Small-Size Target

The M6/M6T airborne small-size target is designed to simulate an aerial target for heat- seeking and radar-guided weapon systems. The airborne target can be used to evaluate combat effectiveness of different air defence systems and air-to-air guided missiles, as well as to support training of air defence and air force personnel.

ARMAMENT Composition target body parachute system IR-emitting source radar reflector

This decoy is airdropped from carrier-aircraft. The air target is simulated during the M6/M6T descent on the parachute thanks to reflections of radars' electromagnetic energy and AIRBORNE TARGETS heat/light generation for heat-seeking missiles.

The M6/M6T small-size target can be detected and tracked in flight visually and with radars and cine-theodolites.

Basic specifications Tracking range by cine-theodolite (of the burning plume), km up to 35 Aircraft bombing airspeed, km/h 750 - 1200 Airdropping altitude, km 2.5 - 17 Plume luminous power at ground, candelas x 106 more than 2 Outer diameter, mm 280 Length, mm 1,065 Flight weight, kg 98

132 ROSOBORONEXPORT forced concrete. to sixmetres ofsoilanduptoonemetre ofrein- charges. Thetandemwarheadcanpenetrateup design permitsinstallationofvarious-purpose tation maincharge.Thewarhead’smodular the percussor-penetrator andtheHEfragmen- ifications oftheS-8rockets. tures of±60 The rockets are operationalatambienttempera- m, andflight speedsbetween450and610km/h. Their launchrangesliebetween1,200and4,500 kg. 1.54-1.70m length,andweigh11.1to15.2 thick reinforced concrete plate. cations. Thewarheadpenetratesa800mm- head isdesignedtoengagepersonnel infortifi- thick armourplate. mentation warhead,penetratinga400mm- armoured targetswithashaped-chargefrag- B8 RocketPods okt ubr 5 160 Dimensions, m: Empty podweight,kg Rockets number Basic specifications The S-13Trocket hasatandemwarheadwith The B8rocket podcanbeuseedwithallmod- The S-8KOMrocket isdesignedtodestroy The B8M-1rocket podisdesignedfor The tworockets have80mmdiameter, The S-8BMrocket withapenetratingwar- diameter 0.41 length 3.55 o C. ROSOBORONEXPORT B13L rocket from diggingintoground. fragments. Thenosepenetratorprevents the producing upto45025-30gdiamond-shaped 13 rockets ofall modifications. ing onlightaircraft. mounting onhelicopters. employment bytacticalaircraft. okt ubr 0 0 7 40 20 123 20 160 Dimensions, m: Empty podweight,kg Rockets number Basic specifications S-13-OF hasanHEfragmentationwarhead The B-13Lrocket podensures launchingofS- B-13L RocketPod The B8V7rocket podisdesignedformount- The B8V20-Arocket podisdesignedfor imtr05 .20.336 0.52 1.70 diameter 0.52 length 2.76 1.70 Aircraft RocketFamily Aircraft RocketFamily B8M-1 B8V20-A B8V7 S-13 S-8

133 AIR ROCKETS ARMAMENT S-24B Aircraft Rocket The S-24B rocket is designed to destroy a wide range of targets. The rocket is armed with an HE fragmentation warhead. The proximity fuse detonates 30 m above the target. The rocket produces up to

ARMAMENT 4,000 fragments with a kill radius of 300-400 m. Against hardened targets, the S-24B rocket is equipped with an impact fuse. AIR ROCKETS

S-25-OFM Aircraft Rocket

The S-25-OFM rocket is designed to destroy a wide range of targets. The rocket has an HE fragmentation warhead.

Basic specifications S-24B S-25-OFM Calibre, mm 240 340/266 Range, km up to 4 Weight, kg: rocket 232 367 warhead 150 Rocket length, m 2.13 3.57

134 ROSOBORONEXPORT external store. feed chutesare alsosecured to theframeof store. mount attachedtotheframesofexternal opening ofhelicopterslidingdoorandona m. Itcanbeinstalledbothonasupportinthe low-speed airtargetsatrangesofupto2,000 power, unarmored andsoft-skin vehiclesand installed aboard helicopters toengageman- aircraft. MiG-29,Su-27,Su-30,Su-32andSu-35 the gun pod. Mi-24VP andMi-35Mhelicopters. the MiG-21-93,Tu-22M3 andTu-142 aircraft, egt g 05 39 1 30 980 50 1 - 30 860 50 1,500-1,800 2 23 715 3,000-3,400 Weight, kg Number ofbarrels Rate offire,rds/min Muzzle velocity,m/s Calibre, mm Basic specifications The Kord machinegunofairborneversion is The 30mmGSh-301 cannon isinstalledon The 23mmGSh-23Lcannonisinstalledon Cartridge boxes(two,300rounds each)and It canalsobemountedintheUPK-23-250 ROSOBORONEXPORT Aircraft Cannon Aircraft Cannon GSh-301 GSh-23L S-3 S-0 2A42 GSh-23L GSh-301 provided). the mount(disintegratinglinkbeltcanalsobe that isstored inthecartridgeboxessecured on 44 witharmor-incendiary-tracingbullet. cartridges witharmor-piercing bulletandBZT- counter forremote fire control. trigger, achargerandanammunitionround 50, Ka-52andMi-28helicopters. evc ie ht 10,000 820to860 650to750 20mm,max 250,max Weight, kg: Service life,shots Armour penetrationat100m Accuracy offire(R80)at100m,mm Muzzle velocity,m/s Rate offire,rds/min Basic specifications Cartridges are insertedintoametallinkbelt The machinegunusestheB-3212.7-mm The machinegunisequippedwithanelectric The 30mm2A42gunisinstalledontheKa- ahn u 27 52 machine gunonmount machine gun 12.7 mmMachineGun Antitank Gun KORD 2A42

135 GUNS ARMAMENT GSh-30 30 mm Airborne Double-Barrel Gun

The GSh-30 airborne double-barrel gun is designed for the Su-25 and Su-39 attack aircraft and helicopters, both in static and mobile versions of gun mounts.

Basic specifications Cartridge type GSh-6-30 Range of aimed fire, m 2,000 Rate of fire, rounds/ min: ARMAMENT high 2,000 to 2,600 low 300 to 400 Muzzle velocity, m/s 940 Unit of fire, pcs 250 GUNS

UPK-23-250 Versatile Gun Pod

The UPK-23-250 gun pod houses the 23 mm GSh-23 aircraft cannon, 250-round ammunition load and a feeding system.

Basic specifications Weight, kg: gun pod loaded 218 cannon with ammunition 145 Range of laying angles, deg: UPK-23-250 elevation 0 traverse 0

136 ROSOBORONEXPORT AEROSPACE SYSTEMS

AIRFIELD EQUIPMENT

ROSOBORONEXPORT 137 PAR-10 Non-Directional Radio Beacon AIRFIELD EQUIPMENT

The PAR-10 medium-wave automated ground The PAR-10 radio beacon can be mounted on control approach system is designed to provide the ZiL-131 or GAZ-3308 wheeled chassis or on RADAR/SUPPORT EQUIPMENT long- and short-range approach and landing sup- the K-type car body of the 782B trailer. port to aircraft fitted with automatic direction find- There are 22 stationary versions of the ers, as well as mark permanent terrain points. PAR-10S radio beacon available.

PRMG-5 Landing Beacon System

The UHF ground instrument landing system is designed to enable round-the-clock final approach at field and permanent aerodromes, in the manual, semi-automatic, and automatic control modes. The PRMG-5 features high mobility, small dimensions and weight, and versatile primary power supply. A four- man crew can deploy/dismantle the system in two hours.

138 ROSOBORONEXPORT RSBN-4N Radio Navigation Ground Beacon

The RSBN-4N round-the-clock, all-weather short-range radio navigation beacon is designed to provide continuous navigation support for military and civil aircraft, and guide them to any point within the beacon's range. The RSBN-4N also supports air traffic control. AIRFIELD EQUIPMENT RADAR/SUPPORT EQUIPMENT UPG-300/UPG-300 NGZh-4 Versatile Mobile Hydraulic Systems

either with or without hydraulic tank pressuri- sation. The systems comprise three separate main hydraulic systems, which can simultaneously provide pressure to three separate aircraft systems or can be combined to provide hydraulic pressure to one or two aircraft systems. The hydraulic systems The UPG-300/UPG-300 NGZh-4 mobile use the AMG-10/7-50s- hydraulic systems are housed in a special car 3/NGZh-4 hydraulic fluids pressurised to 5-21 body mounted on the ZiL-131N cross-country MPa. The flow rate for each of the three hydraulic chassis. They are designed to check and adjust systems is 20-70 l/min. aircraft hydraulic systems in field conditions,

ROSOBORONEXPORT 139 A2111-0000 Oil/Hydraulic Fluid Refiller

The A2111-0000 system is designed to refill hydraulic oil systems and cooling systems of fixed- and rotary-wing aircraft. The refilling car body accomodates three fluid tanks and a pneumatic system to create surplus pressure in the

AIRFIELD EQUIPMENT tanks. The refiller can be cus- tom-fitted with various combinations of fluid tanks. The tanks are easily demountable, and can be used independent- ly from the refiller.

The refiller uses the AMG-10 and 7-50s-3 antifreeze coolant pressurized to 0.2-0.55 MPa. hydraulic fluids, mineral and synthetic oils, and Both open and closed refilling is possible.

SUPPORT EQUIPMENT ZSZh-66M Oil/Hydraulic Fluid Refiller

The ZSZh-66M (A2104M-0000) oil/ hydraulic and special fluids. The refiller’s heated car body fluid refiller is mounted on the GAZ-66 cross- houses four storage tanks. Fluids are fed from the country chassis, and is designed to refill various tanks through flexible hoses tipped with dis- systems with hydraulic fluids, oils, oil mixtures, charge nozzles. The filled fluid volume is metered.

140 ROSOBORONEXPORT AEROSPACE SYSTEMS

INTEGRATED GROUND MONITORING EQUIPMENT

ROSOBORONEXPORT 141 TOPAZ-M Flight Information Processing System

The Topaz-M system processes flight infor- The Topaz-M system is manufactured in sev- mation registered by airborne recorders for on- eral commercial and laboratory versions for line, special and full-scale monitoring of air- static or mobile applications: craft/helicopter flights in order to: static laboratory version record violations of flight performance lim- static version with a video information itations processor analyze and predict the systems’ status ship-borne static version (for aircraft/heli- INTEGRATED GROUND INTEGRATED MONITORING EQUIPMENT (aircraft/helicopter) copter carriers and shore-based aero- reveal failures and deviations in operation dromes) of aircraft/helicopters and locate their ship-borne mobile version causes mobile protected version (manufactured so reveal the flight crew’s violations of flight as to increase its protection for the severe regimes and the flight mission environment applications) reveal the flying personnel, engineers and mobile laboratory version. technicians’ violations of aircraft/helicopter operating conditions The system includes a stationary or portable find the causes of aircraft/helicopter inci- computer, a re-recorder for rewriting data from dents the airborne recorder, an information player, a develop algorithms to analyze the status board for integration with the player, and soft- and operation of the aircraft/helicopter ware for the Windows 98SE, Windows XP oper- systems. ating system.

The Topaz-M system processes, analyzes and The Topaz-M system can provide objective stores information of airborne recorders of gen- monitoring of flights of various military and

INFORMATION PROCESSING SYSTEMS INFORMATION eral and special applications, airborne auto- transport aircraft and helicopters. mated monitoring systems, airborne video recorders and airborne cockpit voice recorders.

142 ROSOBORONEXPORT sion, aportableversion isalsoprovided, includ- sion onthetypeofmaintenanceservice. during itsentire servicelifeandtakingadeci- and control overthestatusoffrictionunit ing, troubleshooting, prediction ofservicelife, The analysisofthisinformationallowstoleranc- tion surfacesinmachinesandmechanisms. information onthetechnicalstatusoffric- on filters). Thewearparticleelementscontain appropriate preparation ofsamples(deposition ments inoils,greases andworkingfluids after analysis ofthecontentwearparticleele- oe upysse 220V±10%AC automated 434х310170 notmore9.1 notmorethan3 notmorethan5 notmorethan5 fromStoBi notmorethan0.1(0.00001) Power supplysystem System dimensions,mm 20,max System weight,lesscomputer,kg Mode ofoperation measurements takenonstandardsamples,% Hardware basicerror(reproduction)of elements diagnosed,min notmorethan220eV Time toperformanalysisandprovideresultsof Time ofworkingmodetosettle,min Limits ofchemicalelements,g/t Limits ofmetalsinoils,g/t,(%) Energy resolutioninthelineofx-radiations5.9keV Number ofsimultaneouslydeterminedelements Range ofelementsdetermined Basic specifications iet esr n apepr1 lmns notmore than90 Time tomeasureonesampleper15elements,s The ADKPrizmasystemisdesignedforrapid In additiontotheADKPrizmalaboratoryver- The systemincorporates: lower limit upper limit (printer, modem,etc.). set ofperipheraldevices set oftestsamples adapted software of informationtodiagnosticcenters) fax-modem foron-linetransmission allowed forthenetworkboard and IBM-compatible personal computer Prizma roentgen-fluorescence analyzer ROSOBORONEXPORT for Roentgen-FluorescenceAnalysisofOil standard forWindows95,98. Prizma employthetablesofParadox 7.0 follows: that performcertainfunctions. ed systemincorporatingtheprogram modules graphical .Thesoftware isactuallyanintegrat- management elementsnecessaryforwork executable modulecontainingallformsand ters. engines andmechanismsaircraft/helicop- measurements takendirectly nearvehicle ry version, allowrecording andprintingofall weather characteristicsofthesystemlaborato- that, withpreservation ofalltechnicaland ing anotebookcomputerandportableprinter The relational databasesusedintheADK Basic elementsofthesystemsoftware are as The ADKPrizmasoftware includesacommon diagnostic system. logical characteristicsoftheautomated subsystem todefine graduationandmetro- tion processing subsystem toentermeasurement informa- mation subsystem toanalyzemeasurement infor- Automated DiagnosticSystem ADK PRIZMA 500 0.2

143 DIAGNOSTIC SYSTEMS INTEGRATED GROUND MONITORING EQUIPMENT DOZOR On-line Monitoring System

The Dozor on-line monitoring system pro- The system can be used autonomously at vides on-line monitoring of the technical status field (temporary) aerodromes and in the air- of systems and airborne equipment of aircraft craft/helicopter single parking and can also be and helicopters and the dump of flight informa- included into static and mobile flight information from airborne recorders of the Tester, BUR- tion processing systems of the Luch, Mayak-85, 1, BUR-SL and ZBN-Т types to the dump solid- Topaz and Decoder types as the re-rewriting, state storage with simultaneous on-line moni- primary processing and information reproduc- toring (express analysis) of this information in tion equipment of the airborne recorder.

INTEGRATED GROUND INTEGRATED MONITORING EQUIPMENT order to: The system allows entry, conversion and processing of parametric information directly from monitor out-of-tolerance condition of flight the test connectors of the systems and airborne parameters equipment. monitor technical status of the power plant, systems and airborne equipment of the aircraft/helicopter monitor flight crew’s actions in flight monitor the aircraft/helicopter power plant and airframe life. MONITORING SYSTEMS

144 ROSOBORONEXPORT AEROSPACE SYSTEMS

LIFE SUPPORT EQUIPMENT

ROSOBORONEXPORT 145 VKK-15K High-Altitude Pressure Suit

The VKK-15K high-altitude pressure suit is a fighter pilot’s flight gear designed to provide life support and enhance performance of flight personnel. It is used in flight missions over land.

Basic specifications Max pressure, kgf/cm2:

LIFE SUPPORT EQUIPMENT bladder 0.9 capstan 0.5 Max cockpit depressurization altitude, km 20 Operational time at an altitude of over 12 km (rapid cockpit depressurisation), min 3 including time at altitude of 20 km, min 1 Weight, kg not more than 4.65

FLIGHT SUITS Service life, yrs 5

VMSK-4-15 Sea Survival High-Altitude Suit

The VMSK-4-15 suit is designed to provide individual life support to aircraft crews operating over ground and sea at high and low altitudes.

Basic specifications

Max suit ventilation system resistance, kPa (mm H2O) for air consumption of 250±10 litres/min 4.5 (500)

Max differential air pressure inside the water-tight suit, kPa (mm H2O) for air consumption of 350±10 litres/min 0.49 (50) Max margin air leak at a pressure inside the MK-4-15 suit of (2.94±10) kPa

(300±10 mm H2O), litres/min 1.5 Max weight, kg not more than 17 Service life, yrs 5

146 ROSOBORONEXPORT nor discomfortshimphysically. Theairventila- the high-altitudepressure suit. It canbeusedindependentlyortogetherwith protect pilotfrom ambienttemperature effects. sustained byfighter pilots.Thesuitconsistsof increase limitsofhead-to-seataccelerations evc ie r notmorethan10 notmorethan1.85 1.5 Service life,yrs Weight, kg Temperature ofincomingventilatingair, of 250-350litres/min,hrs temperature of±50 Overcooling/overheating preventiontimeatanoutside Suit ventilationsystemresistance: Basic specifications 112.8 88.2(0.9) 8.82(0.09) Service life,yrs Weight, kg when checkingairtightnessatinitialpressureof88.2kPa(0.9kgf/sq.cm),max Permissible pressuredropinsuitsystemwithin1min Safe workingpressureinsuitchamber,kPa(kgf/sq.cm) Suit endurancepressure,kPa(kgf/sq.cm) Basic specifications The VK-3Mairventilationsuitisdesignedto The PPK-3-120anti-Gsuitisdesignedto The suitneitherrestrains pilot’smovements for airconsumptionof350litres/min,kPa(mmH for airconsumptionof250litres/min,kPa(mmH ROSOBORONEXPORT o C andaventilationairconsumption o 10-80 C 2 2 peratures of±50 field andin1-1.5hflight withambientairtem- excessive heatingorcoolingdownbothatair- over thebodysurfaceandprevents itfrom tion systemprovides evenairdistributionall suit. et forarubberbladder. Itisputovertheflight two trouser-legs withawidebeltholdingpock- ) a 3.92(400) O), max ) a 2.45(250) O), max The suitweightisunder1.85kg. o C. Air Ventilation Suit PPK-3-120 Anti-G Suit VK-3M -9.8 (1.15 -0.1 4.5 8 )

147 FLIGHT SUITS LIFE SUPPORT EQUIPMENT ZSh-7V Helicopter Crash Helmet

The ZSh-7V crash helmet is designed to protect pilot’s head from injuries both in the cockpit during flight or emergency escape from the helicopter. The crash helmet protects pilot from blinding sunlight and cockpit noises, provides two-way radio communications, and can be fitted with various helmet-mounted observation devices

LIFE SUPPORT EQUIPMENT (OVN-1 or GEO-ONV-1 night vision goggles) and oxygen mask. The helmet can be used in any aircraft with an airspeed under 400 km/h. Maximum altitude for using the helmet with the oxygen mask is 6,000 metres. HELMETS

148 ROSOBORONEXPORT AEROSPACE SYSTEMS

SPACE SERVICES

ROSOBORONEXPORT 149 KOSMOS-3M Launch Vehicle

The Cosmos-3M lightweight launch vehicle (LV) can lift-off from launch pads currently operational at the Plesetsk Cosmodrome. The launch vehicle can be also launched from the Kapustin Yar Launch Site.

The Cosmos-3M LV has been developed on the basis of the R-14U single-stage medium-range

SPACE SERVICES SPACE ballistic missile. At the present time Cosmos-3M launch vehicles are primarily used to launch low- orbit military and civil-purpose navigation, communications and COSPAS-SARSAT search-and-rescue satellites.

The launch vehicle comprises two rocket stages and the payload fairing. The propellant for either stage's power plant consists of hypergolic propellant components: unsymmetrical dimethyl- LAUNCH SERVICES hydrazine (UDMH) as fuel, and nitrogen tetroxide AK-27I as oxidizer. The second stage engine reaches full thrust twice during the flight for high- orbit injection. In-between these two switches the engine operates in the reduced thrust mode.

Basic specifications LV Type liquid propellant, two-stage Control system autonomous, inertial Launch weight, t 109 Height, m 34.2 Diameter, m 2.4 Payload mass, kg: to a circular orbit at an altitude of 1,000 km up to 950 to a sun-synchronous orbit at an altitude of: 450 km 945 700 km 820 Launch accuracy (for 700 km altitude): altitude, km ± 15 (3s) orbital period, sec. ± 20 (3s) inclination, ang. min. +2/-4 (3s) Reliability 0.974

150 ROSOBORONEXPORT Small spacecraft mass in orbit ROSOBORONEXPORT SHS-1 Payload locationzone SHS-2

First stage Second stage Space head section (SHS) Mechanisms and instruments section canister andlifts off from silolauncher. dizer. hydrazine asfuelandnitrogen tetroxide asoxi- golic pr operate onhigh-boilingcomponentsofhyper- (Ascent Unit2option). one optimizedduringRS-18triallaunches fairing (Ascent Unit1option)oralarger by twodifferent fairings:astandard RS-18 adapter andmatingstagecanbeprotected ing equipmentcompartmentwithapayload ing systemunnecessary. modification oftheground control andtarget- tion of flight-control systemisusedasanuppersec- RS-18 Mechanisms andInstrumentsSectionofthe tics oftheoriginalRS-18ICBM.The has inheritedallpositiveoperatingcharacteris- the BaikonurandSvobodnyCosmodromes. off from silolaunchers currently operationalat orbital injectionandin-flight reliability. Itcanlift of LV offers highpowerperformance,accuracy (NATO designation:SS-19,Stiletto).TheStrela on theRS-18intercontinental ballisticmissile Injection accuracyfor500kmaltitude: lgtrlaiiy 0.97 2.5 29.2 105 Flight reliability liquid-propellant, autonomous,inertial Payload weighttakentoacircularorbit Diameter, m Height, m Launch weight,t Control system LV type Basic specifications The Strela LV isstored intransport-launch All thestagesofStrela launchvehicle The ascentunitthatcontainsthemeasur- The principaldesignconceptoftheStrela LV The Strela lightclasslaunchvehicleisbased at analtitudeof,kg: liue m±3 ±3 inclination, ang.min. altitude, km the Strela ascentunit,thusmakingany ICBM fitted upwiththelaunchvehicle opellant –unsymmetricaldimethyl 50k 750 1,220 1,400 1500 km 800 km 500 km Launch Vehicle STRELA three-stage

151 LAUNCH SERVICES SPACE SERVICES DNEPR-1 Launch Vehicle

The Dnepr light-class launch vehicle is based on the RS-20 ICBM (NATO designation: SS-18, Satan). The Dnepr LV offers high payload lift capability, accuracy of orbital injection and flight reliability. It is launched from silos currently available at Baikonur Cosmodrome. The Dnepr LV operates on high-boiling propellant components: unsymmetrical dimethyl SPACE SERVICES SPACE hydrazine and nitrogen tetroxide. The launch vehicle comprises the first, second, third stages and a space head that accommodates the payload. The space head consists of a cylindrical shell, payload adapter, contamination shield and nose fairing. All the LV elements, except for payload adaptation hardware, are inherited from the original SS-18 ICBM. LAUNCH SERVICES Dnepr LV is steam ejected from its launch canister to a height of approximately 20 meters above the ground where the first stage engine is ignited. Such type of liftoff offers payload acoustic environment similar to ground- launched LVs. One of the Dnepr unique capabilities is that it can maintain launch readiness for an unlimited period of time that is restricted solely by the requirements of the integrated payload.

Basic specifications LV type liquid propellant, three-stage Control system nertial, computer-based Weight at liftoff, t 211 Length, m 34.3 Diameter, m 3.0 Payload lift capability vs. orbit altitude, kg: 300 km 3,500 400 km 3,000 600 km 1,600 Injection accuracy (for 300 km orbit): altitude, km ± 4.0 inclination, ang. min ± 2.4 Flight reliability 0.97

152 ROSOBORONEXPORT ple-injection missions. of eachsatelliteintoitsestimatedorbitincasemulti- gy trajectoriesofspacecraft andfacilitatesdeployment lant rocket engine.Theengineprovides minimum-ener- restartable (uptofive restart operations)liquid-propel- installed inthetailsection. first stageissloweddownbythepowderretro-engines engine ofthefirst stageiscutoff. Inthemeantime, steering enginethatignitesbefore theliquid-fuelrocket under thethrustloaddevelopedbysecondstage’s canister withfiller portsforrefueling. hydrazine asfuelandnitrogen tetroxide asoxidizer. ing propellant components–dissymmetricdimethyl stage according totheconventionalLV pattern. payload andthenosefairingare installedinthethird that canaccommodatea2.26m-diameterpayload.The and thepayloadcompartmentundernosefairing stages, theBreeze-KM upperstageasthethird stage, the BaikonurCosmodromes. launch padscurrently operationalatthePlesetskand orbital injectionandflight reliability. Itcanlift-off from Rockot LV offers highpowerperformance,accuracyof the RS-18ICBM(NATO designation:SS-19,Stiletto).The lgtrlaiiy0.97 2.5 29.5 107 Flight reliability autonomous,inertial liquid-propellant,three-stage Payload liftcapabilityvs.circularorbitaltitude,kg: Diameter, m Length, m Weight atliftoff,t Control system LV type Basic specifications Injection accuracy(for300kmorbit): liue m±3 ±3 1,000 1,500 1,850 inclination, ang.min. altitude, km 1500 km 600 km 200 km The Breeze-KM upperstageisequippedwiththe The first andthesecondstagesare separated The RockotLV isoperatedcompletewiththelaunch All thestagesofRockotLV operateonhigh-boil- The RockotLV comprisesthefirst andthesecond The Rockotlightclasslaunchvehicleisbasedon ROSOBORONEXPORT Launch Vehicle ROCKOT

153 LAUNCH SERVICES SPACE SERVICES START/START-1 Launch Vehicles

The Start and Start-1 lightweight launch vehicles are designed to launch small-size spacecraft of various-purpose into low-Earth orbits from the Plesetsk and Svobodny Cosmodromes. The above space missile systems were created on the basis of technologies developed and tried out in the course of creation and further operation of ground mobile combat systems. The launch vehicles are made up of

SPACE SERVICES SPACE assemblies, systems and units of the RS-12M (SS-25) ICBM of the Topol Missile System. The Start LV features an additional engine between the engines used in the 1st and 2nd stages of the Start-1 LV and, correspondingly, differs by longer length, heavier launch weight and higher load-carrying capacity. The engines are propelled by explosion-proof composite solid propellant providing high specific impulse. The launch vehicles of the Start family are permanently emplased inside launch canisters (LC) made of composite LAUNCH SERVICES materials. During pre-launch operations the LV is kept in the horizontal position. The LC is elevated along with the LV into the vertical position immediately before the launch. The missile is projected out of the canister by pressure of combustion materials of a solid propellant gas generator. The engine of the 1st stage is started after the LV leaves the LC. High accuracy of spacecraft orbital injection is provided by the LV's control system based on an on-board digital computer and high-precision gyro-devices.

Basic specifications Start LV Start-1 LV LV type solid-propellant, solid-propellant, five-stage four-stage Control system autonomous, inertial Launch weight, t 60 47 Length, m 29 22.7 Diameter, m 1.8 1.8 Payload mass injected into polar circular orbits (i = 90 deg.) at an altitude of, kg: 200 km 715 490 400 km 570 370 600 km 450 275 800 km 340 185 1,000 km 240 105 Injection accuracy: altitude, km ± 5.0 inclination, deg. ± 0.5 in orbital period, s ± 2.5

154 ROSOBORONEXPORT nozzles (usedforthree-axis flight control). burn engineandfourgimbaledsteering system consistsofafour-chambersingle- increases safetyofoperation. event ofmalfunction.Thisprocedure transient control andlaunchabortioninthe the ground, whichenablesengineburn tion andlateralassembliesare ignitedon kerosene). unit usingnon-toxicpropellants (oxygenand burnout. second stageengineassemblyafter burnout, andtransverse separationofthe engine assembliesuponthefirst stage with parallelseparationofthelateralrocket Cosmodromes. operational atthePlesetskandBaikonur among medium-classlaunchvehicles. reliability, Soyuz-ULV isaworldleader Progress spaceshipsintolowEarthorbit. pose spacecraft aswellSoyuzand place civilian,research andspecial-pur- lgtrlaiiy0.98 Flight reliability 10.3 Injection accuracy: 43.8 33.9 at analtitudeof,kg: 313 Payload massforcircular200kmorbit LV Span,m with thepayloadfairing without thespacehead autonomous,inertial Lenght, m: Launch liftoffmass,t liquidpropellant,three-stage Control system Type LV Basic specifications The Soyuz-Ulaunchvehicleisintendedto The third stage(Assembly 'I') propulsion Liquid propellant enginesofthecore sec- The Soyuz-ULV isdesignedasasystem It canlift-off from launchpadscurrently In termsofthenumberlaunchesand Each LV assemblyhasitsownpropulsion in inclination82.6 liue mupto10 altitude, km in inclination51 ria eid e upto6 inclination, angularminupto2 orbital period,sec in inclination62.8 ROSOBORONEXPORT ° ° ° 7,200 6,300 6,600 SOYUZ-U Launch Vehicle

155 LAUNCH SERVICES SPACE SERVICES MOLNIYA-M Launch Vehicle

The Molniya-M launch vehicle is intended to place space objects to the Moon, to the planets of the Solar System, as well as to inject Molniya- and Prognoz-type spacecraft into high-elliptical near- Earth orbit. At present pre-launch preparation and launching of the Molniya-M LV can be realized at the Plesetsk Cosmodrome by using technical and launch complexes currently in operation for Souyz-U SPACE SERVICES SPACE LVs. The Molniya-M is designed as a system with parallel separation of the lateral rocket engine assemblies upon the first stage burnout and trans- verse separation of the second stage engine assembly after burnout. Each of the LV assemblies has its own propulsion unit using non-toxic propellants (oxygen and kerosene). Assembly ‘I’, like that in Souyz-U LV, is used as

LAUNCH SERVICES the third stage. Assembly ‘L’ (the upper stage) is fitted up with a cryogenic liquid propellant engine that is ignited in zero gravity after an hour-long earth referenced (intermediate) orbit flight. Compressed gas is used to enable coasting flight control of the upper stage with the nozzle units actuating the required maneuvering. Assembly ‘L’ includes an autonomous inertial control system.

Basic specifications LV type liquid propellant, four-stage Control system autonomous, inertial Weight at liftoff (w/o S/C), t 309 Length, m 43.4 LV span, m 10.3 Payload mass for orbit with 40,000 km-apogee and 63 deg-inclination, kg 2,000 Flight reliability 0.98

Assembly ‘L’ (Upper Stage) specifications Mass in reference orbit, kg 6,900 Fuel in tanks, kg 3,700 Assembly mass with propellant outage during jettison, kg 1,050 Propellants: fuel kerosene oxidizer liquid oxygen Thrust in vacuum, kN 68 Specific impulse, N.s/kg 3,400 Height, m 3.5 Diameter, m 2.35

156 ROSOBORONEXPORT loads (upto3.0-3.2tonnes)intogeostationaryorbit. environment characteristicsoftheLV. improve powerperformanceaswelloperationaland loads. with Proton-K inorder todoublethespaceavailableforpay- hydrazine asfuel,andnitrogen tetroxide asoxidizer. golic propellant components:unsymmetricaldimethyl Breeze-M upperstageasforthstage. separation ofstages. Baikonur Cosmodrome. propulsion unit. tion ofsatelliteswhichare notequippedwithanapogee geostationary orbitpoints,thusmakingpossibletheinser- version oftheProton-K. lgtrlaiiy 0.97 Flight reliability 7.4 700 autonomous,inertial 42.34 liquidpropellant,four-stage Payload capacity,kg: LV Span,m Length (withouttheupperstage),m LV liftoffmass,t Control system Type LV Basic specifications Payload spaceavailable,m Injection accuracy: The Breeze-M upperstageenablestodeliverheavierpay- Upgrading (replacement) ofthecontrol systemenablesto The Proton-M hasalargerpayloadfairingascompared All stagesoftheLV andupperstageare fueledbyhyper- It iscomposedofthree stagesandspaceheadwith The Proton-M isdesignedasatandemLV withtransverse It canlift-off from launchpadscurrently operationalatthe The LV isabletodeliverpayloadsdirectly intodesignated The Proton-M heavy-classlaunchvehicleisanupgraded liue mupto±15 upto±8 upto±1.5 inclination, angularmin orbital period,sec upto5,400 altitude, km upto5,000 upto6,200 Venus departuretrajectorymass Mars departuretrajectorymass Lunar departuretrajectorymass (ha=36000 km,hп=5500i=7-25 transfer orbitmasspayload (h=36000 km,i=0±0,25 geostationary orbitmasspayload (h=350 km,i=51,6 low Earthmasspayload (h=200 km,i=51,6 low Earthmasspayload ROSOBORONEXPORT ° ° 19,700 ) 22,000 ) 3 ° 3,000-3,200 ) ° 4,800-5,500 ) 98-150 PROTON-M Launch Vehicle

157 LAUNCH SERVICES SPACE SERVICES AIR LAUNCH Space Transportation System SPACE SERVICES SPACE LAUNCH SERVICES

The Air Launch space transportation system The system comprises the Antonov An 124-100 is designed to deliver lightweight commercial Ruslan heavy lift transport aircraft, Polyot satellites to a variety of Earth orbits, including launch vehicle using environmental-friendly liq- sun-synchronous, circular, elliptical, geo-trans- uid oxygen and kerosene as propellant, flight fer, and geosynchronous orbits, as well as control centre, and ground launch preparation departure trajectories. system.

Basic specifications Launched satellites weight, t: low orbits up to 3 - 4 geo-transfer orbits up to 1.4 - 1.6 geostationary orbits up to 0.6 - 0.8 departure trajectory to the moon 0.6 Orbit inclination, deg 0 - 115 Payload diameter x length, m 2.9 x 7 Launch from customer's territory from airfields fitted with ground launch preparation systems

158 ROSOBORONEXPORT scope forcollectingvisibleimageryataresolu- interferometric imagingpossiblewithin. aggregate surveyswathwithstereoscopic and flight path,thusproviding fora1,000km-wide radar beamshift totherightandleft ofthe diameter parabolicantennaallowsforquick lution withina10-200kmtargetarea. A6m- vides detailedterrainsurveywith1-20mreso- radarpro- signal wavelengthof9.6cm.The tion with optoelectronic equipment. equipped withasyntheticaperture radar, or ing systemwithdirect datalinktothecustomer. aged ahigh-resolution, all-weatherEarthprob- most specific ones. any customer-defined requirement, includingthe gather different typesofdataandimagestomeet based onsmall-sizespacecraft is The Kondor-EEarthremote sensingsystem The optoelectronic payloadincludesatele- The Kondor-Eversion carriesamultifunc- The 800kgKondor-Espacecraft canbe The Kondor-Edevelopmentconceptenvis- synthetic aperture r ROSOBORONEXPORT drwt probing adar witha designed to Russian Earthremote sensingspacesystems. tion, customers canbuydataobtainedby designed tocarryoutspecific missions.Inaddi- or incustomisedcomponentcombinations to thecustomerasacompleteturnkeysystem, tions, includingmilitary. tion, icereconnaissance, othercrucialapplica- ronmental protection, oceanology, shipnaviga- agement, geology, mineralexploration,envi- ture, forestry, mappingindustry, landuseman- system canbeusedintheinterest ofagricul- remote sensingsystems.Dataobtainedbythe drastically expandtheemploymentarea of centres. central andlocaldatareception andprocessing nent comprisestheflight control centre andthe high resolution andexcellentinterpretability. Images takenwiththeopticalsystemfeature conditions, andfornear-infrared imagery. tion of1mandbetter, underfavourablelighting The Kondor-Espacesystemcanbedelivered The Kondor-E’stechnicalcapabilitiescan The Kondor-Espacesystem’sground compo- Space RemoteSensingSystem KONDOR-E

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