AAAATMANIRBHARTTMANIRBHARTAA BYBY HALHAL ONEONE STOPSTOP SOLUTIONSOLUTION FORFOR ALLALL AEROSPAEROSPACEACE NEEDSNEEDS OVERHAUL/UPGRADE
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To achieve self reliance in design, development, manufacture, upgrade To become a and maintenance of aerospace equipment, diversifying significant into related areas and managing the business in a climate of growing global player in professional competence to achieve world class performance the aerospace standards for global competitiveness and growth in exports. industry.
3 CONTENT
9 TEJAS-LCA 32 AFCC 10 HTT-40 11 DHRUV 12 LCH 13 LUH 14 RUDRA 15 JAGUAR UPGRADE
AIRCRAFT FLIGHT CONTROL PLATFORMS PAGE 6 PAGE 17 SYSTEM PAGE 33
ABOUT HAL PAGE 9 Communication, PAGE 31 Navigation & RECORDING Identification SYSTEM systems
6 THE COMPANY 18 DACS 34 SSDVRS 7 PRODUCTION CENTRES 19 ACS 235 35 CVFDR 8 DESIGN COMPLEX 20 SoftNet Radio 36 SSFDR 21 SCDLU 37 CPMM 22 VACS 38 SSFDR/CVR 23 MNS 24 VOR/ILS 25 ADVANCED TACAN 26 RAM 2700A 27 IFFT-2460ALH1 28 IFFI-3400A 29 CIT 30 AIS
4 CONTENT
42 Mission Computer for Mirage 2000 68 TRANSFORMER RECTIFIER UNIT (TRU) 43 Jaguar Darin III 69 AC POWER MANAGEMENT & DISTRIBUTION Mission Computer S YSTEM 44 Mission Computer (MC) 70 ALTERNATOR CONTROL & PROTECTION UNIT for Hawk- i 71 DC POWER MANAGEMENT & DISTRIBUTION 45 Display & Mission Computer SYSTEM for IADS - LCH 46 Engine and Flight Display Unit (EFDU) 47 LCA MK1A Mission Computer 48 LCA MK1A SMFD 49 LCA MK1A Digital Map Generator
MISSION, COMBAT AIRCRAFT ELECTRICAL AND DISPLAY SYSTEM PAGE 39 SYSTEM PAGE 51 PAGE 73
R&D CENTRE MISSILE PAGE 41 AIRCRAFT PAGE 67 CAPABILITIES ELECTRONICS UTILITY & SYSTEM TEST FACILITIES
40 RPF 52 DIGITAL LOX INDICATOR/ 74 AEROSPACE SYSTEMS AND TRANSMITTER EQUIPMENT RESEARCH & DESIGN CENTRE 53 ENVIRONMENTAL CONTROL (ASERDC) -KORWA SYSTEM 76 STRATEGIC ELECTRONICS 54 FUEL CONTENT GAUGING RESEARCH & PROBE DESIGN CENTRE 55 HYDRAULIC POWER PACK (HYDERABAD) 56 ACTUATORS 78 TEST FACILITY AT SLRDC 57 HYDRAULIC PUMP 80 MISSION AND COMBAT SYSTEM R&D 58 WHEELS & BRAKES CENTRE (MCSRDC) 59 BHEEM-EU 83 AEROSPACE SYSTEMS & 60 SECU EQUIPMENT R&D 61 TGECU CENTRE, LUCKNOW, INDIA 62 CWS 85 FACILITIES AVAILABLE AT ASERDC, LUCKNOW 63 ATS 87 CONTACT 64 SSWCS 65 ADU
5 Hindustan Aeronautics Limited (HAL) is a premier activities in the areas of Design, Development, aerospace company under the Ministry of Defence, Manufacture and Overhaul of advanced fighters, trainers, Government of India, with its Corporate Office at helicopters, transport aircraft & associated aero engines, Bengaluru. The company has 20 production divisions and accessories, avionics and airborne systems. It has also 10 Research & Design Centres spread across the country. diversified into manufacture of structures for space HAL had its origin in 1940 as a private limited company vehicles like Polar/ Geostationary Satellite Launch founded by a far-sighted industrialist Seth Walchand Vehicles, Indian Remote Sensing and other Satellites, Hirachand to manufacture aircraft. Over the past Eighty Industrial & Marine Gas Turbines as well as Commercial years, HAL has spread its wings to cover various services at the HAL Airports at Bengaluru and Nasik. ORGANISATION
BANGALORE DESIGN MIG COMPLEX COMPLEX COMPLEX
Aircraft Division Aircraft R&D Centre (ARDC), Bengaluru Aircraft Mfg. Division, Nasik Mission & Combat LCA Tejas Division Aircraft Overhaul Division, System R&D Centre (MCSRDC), Bengaluru Engine Division Nasik Aero Engine R&D Centre (AERDC), Bengaluru Overhaul Division Sukhoi Engine Division, Rotary Wing R&D Centre (RWRDC), Koraput Foundry & Forge Division Bengaluru Aerospace Division Aircraft Upgrade Research & Design Engine Division, Koraput Industrial & Marine Centre (AURDC), Nasik Gas Turbine Division Aerospace Systems and Eqpt R&D Centre ( ASERDC) Korwa Airport Service Centre Aerospace System and Eqpt R&D Centre ( ASERDC) Lucknow Strategic Electronics R&D Centre (SLRDC), Hyderabad Central Materials & Process Laboratory, Bengaluru Transport Aircraft R&D Centre, Kanpur
HELICOPTER ACCESSORIES COMPLEX COMPLEX
Transport Aircraft Division, Helicopter Division Kanpur Accessories Division, Barrackpore Division Lucknow Helicopter MRO Division Avionics Division, Hyderabad and Branch factory Aerospace Composites at Kasaragod Division Avionics Division, Korwa
6 AIRCRAFT DIVISION, BENGALURU • Manufacture of Structural Work Packages for Export
LCA TEJAS DIVISION, BENGALURU • Manufacture of Light Combat Aircraft (LCA) - Tejas
• Manufacture and Overhaul of Adour Mk 871, Shakti, Artouste IIIB & Garrett TPE 331-5 engines ENGINE DIVISION, BENGALURU • Overhaul of Adour Mk 804/811, Dart, Gnome, Orpheus and TM332-2B2 engines
AIRCRAFT OVERHAUL DIVISION, BENGALURU • Overhaul and Upgrade of Jaguar, Mirage-2000, Kiran & Hawk
FOUNDRY & FORGE DIVISION, BENGALURU • Manufacture of Castings, Forgings, Rolled Rings
• Structural packages for Launch vehicles (PSLV, GSLV), Satellites (INSAT, IRS), AEROSPACE DIVISION, BENGALURU Integration of Booster Rockets and Cryogenic Engines
• Manufacture & Overhaul of LM 2500 Industrial & Marine Gas Turbine IMGT, DIVISION, BENGALURU • Repair and Overhaul of SGT A20 AV (Industrial Avon)/ SGT A05 (Industrial 501K) Engines
AIRCRAFT MFG. DIVISION, NASIK • Manufacture of Su-30 MKI Aircraft
AIRCRAFT OVERHAUL DIVISION, NASIK • Overhaul of MiG-21 Series, Su-30MKI Aircraft
SUKHOI ENGINE DIVISION, KORAPUT • Manufacture & Overhaul of AL-31 FP engine for Su-30 MKI
• Manufacture of RD33 engine ENGINE DIVISION, KORAPUT • Overhaul of R11, R25, R29B and RD33 engines
TRANSPORT AIRCRAFT DIVISION, KANPUR • Manufacture of Do-228 Aircraft in both Civil & Military Version
ACCESSORIES DIVISION, LUCKNOW • Manufacture & Overhaul of Mechanical, Electrical, Hydraulic and Fuel System
• Manufacture & ROH of Communication Systems, Primary Airborne Radar and Ground Radar AVIONICS DIVISION, HYDERABAD Systems, Secondary Surveillance Radar Systems, Mission, Display and Radar Computers
• Manufacture & ROH of Navigation and Attack Systems, Cockpit Displays AVIONICS DIVISION, KORWA Flight Data Recorders, Sensor package for Brahmos and Prithvi Missiles
• Manufacture of Advanced Light Helicopter (ALH Dhruv), HELICOPTER DIVISION, BENGALURU Light Combat Helicopter (LCH), Cheetal and Chetak
BARRACKPORE DIVISION, BARRACKPORE Overhaul & Servicing of Chetak, Cheetah, Lancer & Cheetal Helicopters
HELICOPTER MRO DIVISION, BENGALURU • Maintenance, Repair & Overhaul facility for Helicopter
• Manufacture of composite parts and assemblies. AEROSPACE COMPOSITES DIVISION, BENGALURU • Rubberised fuel tank for Helicopters (ALH)
7 DESIGN COMPLEX
R&D DIVISION MAJOR ACTIVITIES
CENTRAL MATERIAL & PROCESS • Development of Materials, Castings, Forgings and New Processes LABORATORY, BENGALURU • NADCAP certified facilities for checking of material properties & N DT facilities
AIRCRAFT UPGRADE R&D CENTRE (AURDC), NASIK • Aircraft / System Upgrade work on Russian Aircraft (like MiG Series & Su-30)
AEROSPACE SYSTEMS & EQPT R&D CENTRE, • Design & Development of ECS, Hydraulic, Wheels & Brakes, Fuel, AC/DC (ASERDC) LUCKNOW Electrical System, Electrical Rotating Machine and Fuel gauging system.
AEROSPACE SYSTEM & EQPT R&D CENTRE, • Design & Development of Avionics & Navigational System (ASERDC) KORWA
TRANSPORT AIRCRAFT R&D CENTRE (TARDC), KANPUR • Development & Modification / Upgrades of Transport Aircraft
• Design & Development of Communication, Navigation, Identification, Radar, STRATEGIC ELECTRONICS R&D CENTRE Computers & Utility Management Systems. (V/UHF Radio, RAM, VOR, TACAN, (SLRDC), HYDERABAD IFF, Transponder & Interrogator, CIT, Air Data Computer)
AIRCRAFT R&D CENTRE (ARDC), • Design & Development of Fixed Wing Aircraft (LCA, IJT, UAV, HTT-40), Facility for BENGALURU Ground & Flight Testing, Wind Tunnel Testing, Unique Iron Bird Test Facility
AERO ENGINE R&D CENTRE (AERDC), BENGALURU • Development & Upgrade of Aero Engines & Test Bed design
• Design & Development of Mission Avionics Hardware, Mission Software, MISSION & COMBAT SYSTEM R&D CENTRE Algorithms for Navigation & Weapon Guidance. Integrated Avionics suite (MCSRDC), BENGALURU Aircraft Upgrade, Weapon & Sensor, Integration and Flight Simulators
ROTARY WING R&D CENTRE (RWRDC), BENGALURU •Design & Development of Rotary Wing Platforms (ALH, ALH-WSI, LCH, LUH)
CURRENT MAJOR PROGRAMMES
DESIGN & DEVELOPMENT UPGRADE PROGRAMMES OVERHAUL PROGRAMMES PRODUCTION
• LCA • 'TEJAS' Light Combat FIGHTER • Su-30 MKI Aircraft (LCA) Single • Su-30MKI • Mirage 2000 I /TI • Hawk Mk132 Seater, Trainer and Naval • Do-228 Variants. • Jaguar Darin III • Jaguar • 'Dhruv'ALH • Light Combat Helicopter - • Hawk-i • Mirage-2000 T /TH • LCH (LCH) TRANSPORT • Chetak / Cheetal • Light Utility Helicopter - • Kiran HJT-16 • Do-228 Glass Cockpit (LUH) • Do-228 • Basic Turboprop Trainer • An-32 HTT - 40 • Unmanned Aerial Vehicle • HS-748 (UAV) • ALH Dhruv • Do - 228 Civil Variant • HTFE-25 Turbo Fan Engine • Chetak / Cheetah / Lancer • HTSE-1200 Turbo Shaft • MiG-21 series Engine
8 TEJAS Light Combat Aircraft (LCA)
The Light Combat Aircraft (LCA), named as 'Tejas', is light weight, multirole, supersonic combat aircraft. It has been designed and developed by Aeronautical Development Agency (ADA) and HAL to meet the stringent requirements of the Indian Air Force as its frontline, multi-mission, tactical aircraft for the coming decades. Composite material has been used extensively for the fuselage and the wings. The Aircraft is also fitted with state of the art Indigenous Avionics equipment like TACAN, VOR-ILS, Mission Computer, Digital Video Recording System, Brake Control Hydraulic Engine and Electrical Monitoring System, Open Architecture Computer, Audio Management Unit, Radio Altimeter, Centralised Warning System, Identification Friend or Foe including Primary Radar. The aircraft is powered by single GE 404 IN20 turbofan engine. Tejas has four variants namely Air Force (Fighter & Trainer) and Naval (Fighter & Trainer). Series Production of the aircraft for meeting the IAF's requirement is under progress. Tejas Mark 1A is an advanced version which will have mid-air refueling probe, AESA Radar and Electronic Warfare (EW) sensor suite to enhance aircraft endurance and capability. To increase combat operations, it is enabled with BVR & ASRAAM missiles.
FEATURES ROLES SPECIFICATIONS
• Tail-less compound delta • Supersonic fighter for air • MTOW : 9900 Kg • Quadruplex Digital Fly By Wire combat • Payload : 3500 Kg • Open Architecture Avionics with • Offensive air support. • Speed : 1.6 Mach Glass Cockpit • Reconnaissance • Service Ceiling : 15 Km • Advanced Composites • Ground attack and maritime Structure operations
9 HTT-40 Hindustan Turbo Trainer-40
The Hindustan Turbo Trainer (HTT) - 40 is an ab-initio trainer aircraft designed to meet primary training requirements. This fully aerobatic tandem seat turbo trainer will have an air-conditioned cockpit, modern avionics and zero-zero ejection seats. Built around a proven turbo prop engine, this aircraft is designed to have good low speed handling qualities for better training effectiveness. This aircraft will be certified to FAR-23 Standard.
Glass Cockpit
SALIENT FEATURES OF HTT-40: ROLES: • Sturdy structure with a combination of light alloys and composites • Basic Training • Instrument flying • Single piece canopy giving both pilots good all-round vision • Aerobatics • Close formation • Glass Cockpit • Maximum speed 450 km/h • Navigation • Night Flying • Maximum load factor +6/-3 g • Glide ratio of 11.5:1
10 DHRUV Advanced Light Helicopter (ALH) -Mk III
Dhruv, designed and developed by HAL, is a multi-role, multi- mission, new generation helicopter in the 5.5 tonne weight class built to meet FAR standards. It is designed to meet the requirements of both civil and military operators. Dhruv is powered by two Shakti engines with sufficient power margins for single engine performance and CAT 'A' take-off and landing capability. Use of two engines provides increased safety and allows continued flight till safe landing. Composites have been used extensively in the construction of the ALH. It also features a hingeless main rotor, bearingless tail rotor and anti resonance isolation system. The Helicopter is fitted with indigenous Avionics viz Radio Communication System, Radio Altimeter and Identification Friend or Foe (IFF), Air Data Unit and Solid State Digital Video recording System. GLASS COCKPIT Dhruv is ideally suited for VIP transport, search and rescue, offshore operation, disaster relief, EMS and police roles. The ALH is in operation in Nepal, Mauritius and Maldives. HAL has a dedicated Maintenance, Repair and Overhaul (MRO) facility at Bengaluru.
SARANG DISPLAY TEAM ALH - ARMY UTILITY SKID VARIANT
11 LCH Light Combat Helicopter
The LCH is a dedicated attack helicopter developed by HAL. It is fitted with select weapon systems with in-built stealth characteristics. The helicopter features a narrow fuselage and tandem seating for the pilot and co-pilot. The machine is designed for low detection (reduced visual, aural, radar and infra-red signatures) and is fitted with crash worthy landing gear for better survivability. The Helicopter is fitted with indigenous Avionics viz Radio Communication System, Radio Altimeter and Identification Friend or Foe (IFF). Features: • Powered by twin Shakti turboshaft engines • Helmet mounted targeting systems, electronic warfare systems and advanced weapons systems • Glass cockpit with multifunction displays, target acquisition and designation system with laser range-finder and laser designator • Data link for network-centric operations facilitating transfer of mission data to other airborne platforms and ground stations • 20 mm Turret gun, 68/70 mm rocket pods, Air to Surface and Air to Air Missiles
Shakti (Ardiden 1H1) Engine
12 LUH Light Utility Helicopter
Salient features of LUH are: • Composite Airframe with crash worthy Light Utility Helicopter (LUH) is a new generation utility features helicopter in the three tonne weight class designed by HAL to • Main &Tail Rotor blades made out of meet the requirements of both military and civil operators. LUH composite materials for damage tolerance capability is powered by a single turbo shaft engine with adequate power • The hinge less Rotor system ensures high margins to accomplish high altitude missions in the Himalayas agility and maneuverablity of the helicopter with ease. Light Utility Helicopter is designed and developed by • State of the art Avionics suite with smart HAL as a fully indigenous product with features suitable for MFDs and indigenously developed operations in diverse operating conditions. application software • Spacious cabin ensuring enough room for troop transport up to 6 troops or 2 stretchers with a medical attendant or large volume internal cargo
Roles: • Pilot Training • Reconnaissance and surveillance • Casualty Evacuation • Utility • Civil Aviation Ardiden 1 U Engine with FADEC
13 WEAPON SYSTEM INTEGRATION RUDRA Advanced Light Helicopter (ALH)-Mk IV
Advanced Light Helicopter Mk IV is the armed version of ALH The ALH Mk IV is a sophisticated weaponised designed to meet the requirements of Indian Army and Air platform designed to carry external stores up to 900 Force with the following Weapons and Mission Sensors : kg. ALH Mk IV is equipped with Integrated a. Turret Gun System with Ballistic Computer System (BCS) Architecture Display System (IADS) with Multi- Function Displays. The Helicopter is designed for b. Rocket System with fixed sight system self defense mode as well as attack mode. Three c. Air to Air Missile System sighting systems are available for aiming at the d. Anti Tank Guided Missile (ATGM) System target which include Electro Optic pod, Fixed sight e. Electronic Warfare (EW) System consisting of RWR, LWR, and Helmet Mounted Sight. The sensors also include MWR Electronic Warfare suite along with Flare and Chaff f. Flare and Chaff Dispenser System (FCD) dispenser. The helicopter can be fitted with 4 rocket pods or two air to air missiles or four air to ground g. Electro Optical System (EO) consisting of FLIR / CCD missiles apart from 20mm nose mounted Turret Camera, LRF/LD Gun. The mission sensors and the weapon h. Helmet Pointing System (HPS) electronics are integrated to the cockpit display I. Solid State Data & Video Recorder (SSDVR) system (IADS) through MIL 1553.
14 UPGRADE
Weapon/ Technology Sensor Development Integration
Avionics Upgrade/ Flight Avionics Suite Simulators
JAGUAR DARIN-III AIRCRAFT UPGRADE Upgrade of Jaguar DARIN I and maritime aircraft to DARIN III with near glass cockpit configuration, multimode radar, indigenous mission computer, digital Engine and Flight Instrument System & latest weapons.
JAGUAR DARIN-II UPGRADE DARIN-II(Display Attack Ranging and Inertial Navigation) upgrade of Jaguar Aircraft significantly enhancing mission and operational capabilities
MISSION MANAGEMENT SYSTEM (MMS) FOR MID LIFE UPGRADE OF DO-228 • Integrated Sensor Management • Enhanced Situational Awareness • RADAR and EO/IR video display • Mission Planning with Debrief functions • Single & Twin Operator Console Configuration
HAWK MK-132 AIRCRAFT UPGRADE (HAWK- I) • Indigenous Mission Computer • Integration of A.I based Voice Activated Command System • Secured voice communication & data link operation • Embedded Virtual Training System (EVTS) • Integration of Weapons & EW Systems (RWR & CMDS) • Digital Map Generation (DMG) with Ground Proximity Warning (GPW)
15
Communication, Navigation & Identification systems
17 DIGITAL AUDIO CONTROL SYSTEM (DACS 2300A SERIES)
DACS 2300A SERIES – KEY FEATURES DIGITAL AUDIO CONTROL SYSTEM • Lightweight, compact & solid-state design
In modern aircraft, the Pilot is engrossed in a wide range of • DSP based Adaptive Noise Cancellation (ANC) & Voice operated communication signals viz., Transceiver audios, Receiver audios, switch (VOS) algorithms Warning audios and Intercommunication audios. Digital Audio • Extensive Self-test and Built In Test Control System (DACS) eases the Pilot’s burden by efficiently minimizing the controls, interfacing all the signals in a logical • Automatic change over to standby Power Supply path in case of manner and provides the following functions: failure in Normal power supply path • Intercommunication between Flight Crew and Ground Crew. • Reliable dual redundant functional channels for safe operation • Interface and control of mike and headset audio signals of various transceivers. • In-situ adjustment of Mike and Audios through USB interface • Interface of warning signals. • Front panel VOS adjustment • Interface to the Cockpit Voice Recorder and Voice Data Recorder. • NVG compatible panel illumination Digital Audio Control System (DACS) implements audio signal conditioning in digital domain using digital signal processing techniques and provides better signal quality by using efficient DACS 2300A CONFIGURATIONS: Adaptive Noise Cancellation (ANC) algorithm. The Digital Audio Control System design is derived from the extensive • DACS-Single LRU version: experience from analog Audio Management Unit configurations DACS Qty:1 no for Fighter aircrafts 146mm (W) X 67mm (H) X developed for and being used in LCA, IJT, ALH, MiG21 BIS Upgrade 180mm (D) Wt: 1.5 Kg max and MiG27 Upgrade aircrafts. • DACS -Split LRU version : Solid-state modular design and rugged construction provides long (A) Remote Junction Box (RJB) Qty:1 No Dimensions: 227mm (W) life, high reliability and excellent maintainability for both new and X 113mm (H) X 153mm (D) Wt: 2.2 Kg max retrofit applications on fixed wing and rotary wing platforms. The (B) Audio Control Panel (ACP) Qty: 2 no’s to 4 no’s depending up DACS is a compact, lightweight and low cost system. on the platform Dimensions: 146mm (W) X 67mm (H) X 122mm (D) Wt: 0.75 Kg max SPECIFICATIONS
Parameter Specifications SYSTEM SPECS ELECTRICAL SPECS SNR > 40 dB Power Supply 28 V DC Distortion < 5% Power Consumption 45 W Max Frequency response <+3 dB from 300Hz to Current Rating 1.5 A Max at 28 V DC 3500Hz INTERFACE SPECS Cross talk > 50 dB Digital I/O MIL STD 1553B, ARINC 429, Self test POST, IBIT and CBIT. ETHERNET & USB. QUALIFICATION & COMPLIANCE Audio Input a) 2.5 V to 5.5 V rms from avionics on board Power Supply Standard MIL STD 704E b) 4mV rms from Microphone Environmental MIL STD 810F Audio Output a) Headset output : 150mW EMI/EMC MIL STD 461C/E across 150 Ω / 600 Ω Reliability (MTBF) >3000 Hours MIL b) Recording output: 2 to HDBK 217 15mW across 600 Ω and > Software Compliance DO-178B 4.5V across 10K Ω PLATFORMS LCA, LCH, LUH and HTT40 Discrete Input 5V and 28V
18 ADVANCED COMMUNICATIONS SYSTEM - ACS 235 Designed & Developed by SLRDC
ADVANCED COMMUNICATION SYSTEM - ACS 235 KEY FEATURES
For critical flight regimes, HAL’s V/UHF Tactical Airborne Transceivers • Multi-mode, multi-band, V/UHF Airborne provides today’s flight crews with dependable, highly accurate air to air Transceiver and air to ground communication. • Direct sequence spread spectrum for LPI ACS-235, lightweight airborne V/UHF Tactical Airborne Transceiver is a • Good co-location for multiple radio highly versatile, solid- state, digital, high frequency radio communication installations system intended for both fixed- and rotary-wing airborne applications. • Emergency guard receiver for 40.5, 121.5, Advanced features include digital signal processing (DSP) technology to 156.8 and 243 MHZ provide new embedded features in an exceptionally lightweight, compact system. Control options for the system provide MIL-STD-1553B. • FH for TRANSEC Extensive built-in test equipment (BITE) is utilized for diagnostic testing • Encryption for COMSEC and monitoring. Built on a strong foundation of quality, ACS-235 provides users with tactical advantages and lower life cycle costs. HAL has over 30 years experience in airborne communication system design and our systems are successfully proven on various aircrafts like SU-30, MIG-29UPG, MIG-29K/KUB, IJT, MIG- 21UPG (BISON), JAGUAR/DARIN-III, ALH, MIG27 etc. Combination of our rich experience with latest digital technology makes HAL ACS 235 Radio the affordable choice for users. SPECIFICATIONS
Frequency Range 30-407 MHZ TRANSMITTER Channel Spacing 8.33 kHz; 12.5 kHz; 25kHz RF Output Power 10W (AM), 32.4W (PEP AM) Modulation Formats AM, FM FSK, OQPSK 15W (FM) Power supply 28V DC Harmonics <-60 dBc Control MIL-STD-1553B Spurious emissions <-80 dBc MAIN RECEIVER ENVIRONMENTAL Sensitivity (10dB Sinad) <107dBm (FM 3kHz Operating Temperature -40°C to + 70 °C modulation) Vibration, Shock MIL-STD-810F <105 dBm (AM 30% Supply variations MIL-STD-704E modulation) EMC MIL-STD 461C IF/Image Rejection ≥ 80 dB Altitude 18Kms GUARD RECEIVER PHYSICAL Frequencies 40.5 MHZ,121.5 MHZ, Size (D x H x W)mm 318 x 195 x 124 (½ ATR Short) 156.8 MHZ, 243 MHZ Weight < 8kg Sensitivity <101 dBm (FM), PLATFORMS Advanced Light Helicopter <101 dBm (AM) (Dhruv), Chetak
19 SoftNET RADIO (SDR-2010) Designed & Developed by SLRDC
SoftNET RADIO SDR-2010 KEY FEATURES
The SDR-2010 is a Software Defined Radio, designed and • Digital AM / FM compatible with Legacy AM/FM radios developed at SLRDC 2-RF channel (V/UHF & L-Band) software 100 / 500 Hops Frequency Hopping Voice waveform configurable Radio. • Dynamic TDMA based MANET implementation with 40 nodes The SDR is capable of hosting different waveforms ranging participation from Legacy AM/FM to Frequency Hopping(FH) Voice and • Dynamic Node Leaving and Node Joining mechanisms Dynamic Time Division Multiple Access (DyTDMA) Networking. • Suitable for Net Centric Operation The SDR has necessary interfaces like RS-232, RS-422, • Built in GPS receiver Ethernet and MIL-STD-1553B for Data and Control. • Efficient Time and Frequency Synchronization schemes The SDR is a 3/4 ATR LRU with an External 1/2 ATR L-Band • Ethernet based user data interface Power Booster. • Modular concept with Replaceable RF heads In the Dynamic TDMA based master-less Mobile Adhoc • Digital Processing Resources available for future growth Networking mode, 40 member participation is possible with potential facilities like fixed / free message forwarding and Image • Free and Fixed messaging facility broadcasting. • Built in Test Facility - POST, IBIT Integrated GUIs for various mode selections and waveform • Pilot selectable modes through MFD loading are available for ease of operation of the SDR. The features currently available are not limited and are expandable in terms of Waveforms as well as RF operating bands.
SPECIFICATIONS
Parameter Specifications Parameter Specifications Dimensions 318 (D) X 193 (H) X 210(W) mm RF SPECIFICATION Weight 13Kg (without Mounting Tray) Frequency 30-88 MHZ (FM) ELECTRICAL SPECIFICATIONS 118-155.975 MHZ (AM) 156-174.975 MHZ (FM) Power Supply 28V DC 225 -399.975 MHz (AM/FM/FH500 Voice) Power Consumption 340 W (max) 960 - 1240 MHz (FH500 Adhoc Networking) INTERFACE COMPLIANCE Control MIL-STD-1553B Environmental MIL-STD-810F Data Ethernet Power Supply MIL-STD-704D Others RS-232, RS-422 EMI /EMC MIL-STD-461E HEALTH MONITORING PLATFORMS Built in Test POST, IBIT Fighters, Trainers, Transport and Ground
20 SECURE COMMUNICATION DATALINK (SCDLU) Designed & Developed by SLRDC
KEY FEATURES
SCDLU is a Software Defined Radio designed and developed by • Digital AM/FM compatible with Legacy AM/FM Radios SLRDC. It is a 2 RF channel (V/UHF & L Band ) software • 100/500 Hops frequency hopping waveform configurable Radio. • Dynamic TDMA based MANET with 40 nodes participation SCDLU is capable of hosting different waveforms ranging from • Dynamic Node Joining and Node Leaving mechanism Legacy AM/FM to Frequency Hopping (FH) Voice and Dynamic • Free/Fixed Text, Image Transfer capability Time Division Multiple (DyTDMA) Networking. • Suitable for Net Centric Operation SCDLU has necessary interfaces like MIL-STD-1553B, Ethernet, • Built-in GPS receiver RS-232, RS-422 for Data and Control. • Efficient Time and Frequency Synchronization schemes SCDLU is designed in ½ ATR with horizontal mounting. Power • Robust Modulation and Forward Error Correction schemes Amplifier for V/UHF and L Band RF channels is built into the Unit. • Ethernet based user Data Interface The unit is cooled by built-in DC fans. • Modular Concept with Replaceable RF heads Integrated GUIs for various mode selections and waveform • Digital Processing Resources Available for future growth potential loading are available for ease of operation of SCDLU. • Built In Test Facility- POST, CBIT, IBIT The features currently available are not limited and are • Pilot selectable modes through MFD expandable in terms of Waveforms as well as RF Operating Bands.
SPECIFICATIONS
Parameter Specifications Parameter Specifications Dimensions 368(D) X 174(H) X 260(W) RF Specification (with Mounting Tray) Frequency Weight 12.0 Kg 30-88 MHz (FM) (with Mounting Tray) 118-155.975 MHz (AM) 156-173.975 MHz(FM) ELECTRICAL SPECIFICATIONS 225-399.975 MHz (AM/FM/SecureVoice/ Power Supply 28V DC FH500Voice/FH500 Adhoc Networking) Power Consumption RX 250W(max) 400-512MHz (FM/Custom waveforms) 960-1240 (2 RF heads operational) Tx 700 Watts(max) MHz(FH500 Adhoc Networking) INTERFACE COMPLIANCE Control MIL-STD-1553B Environmental MIL-STD-810F Data Ethernet Power Supply MIL-STD-704D Others RS-232, RS-422 EMI/EMC MIL-STD-461E HEALTH MONITORING PLATFORMS Built in Test POST, CBIT, IBIT Fighters, Trainers, Helicopters, Transport and Ground
21 VOICE ACTIVATED COMMAND SYSTEM (VACS-1000A) Designed & Developed by SLRDC
VOICE ACTIVATED COMMAND SYSTEM VACS-1000A KEY FEATURES
Voice Activated Command System (VACS1000A) • Speaker independent recognizes the pilot voice commands and sends the • Continuous speech recognition respective code to Onboard computer on MIL STD- • Operation in high noise and pressure breathing environments 1553B bus. • Use of state of the art speech recognition and enhancement techniques VACS reduces the pilot workload and allows more • Provision for Aural feedback/Command confirmation focus on the critical tasks pertaining to the targets, • Easy to use Trainer Software to cater for new commands and for landing zone, terrain etc. further improvement Intended for tuning of the radios, selection of modes, • INSITU Programming set up of MFD's, navigational equipment etc. • MIL-STD-1553B Interface • Extensive BIT facility for fault analysis
SPECIFICATIONS
Parameter Specifications Weight 3kg Word Accuracy 98% Self Test PBIT, IBIT and CBIT Power Supply 28V DC Supply as per MIL-STD Compliance 704E Software & Hardware DO178B, DO254 Power Consumption < 30 Watts EMI/EMC MIL-STD-461E Physical Dimensions < 1/4 ATR Environmental MIL-STD-810F PLATFORMS For Rotary Wing and Fixed Wing Aircraft
22 Multimode Navigation System (MNS) Designed & Developed by SLRDC
KEY FEATURES
FUNCTIONS: • NO.OF CHANNELS : VOR : 160 CHANNELS MNS3005A is an integrated navigation system to : LOC/GS: 40 CHANNELS (Pair) support the VOR, ILS, marker and GPS receiver • VOR: Sensitivity:-99dBm Dynamic Range: -93 dBm to -27dBm, functional capability. Bearing accuracy <±3º • VOR receiver for route navigation Audio Output: 1mW to 100mW Adjustable/ 600 ± 20 Ω • ILS receiver for instrument landing • LOC: Sensitivity:-99dBm • Marker receiver for runway approach Dynamic Range: -72 dBm to -33dBm, • GPS l1 c/a receiver for positional data support in DDM Accuracy:<±11% Std Deviation NMEA-0183 format. Audio Output: 1mW to 100mW Adjustable/ 600 ± 20 Ω • GLIDE: Sensitivity:-87dBm Dynamic Range: -76 dBm to -33dBm, DDM Accuracy:<±13% Std Deviation • MKR : Sensitivity:-67dBm(High Sense), -53dBm(Low Sense) Audio Output: 10mW to 100mW Adjustable/ 600 ± 20 Ω
S P E C I F I C AT I O N S
PARAMETERS SPECIFICATIONS Physical • Unit:331 (L) X 60.5 (W) X 102 (H), • Mounting Tray: 372 (L) X 72 (W) X 125 (H) • Weight: Unit: 2.1 Kg (max) • Mounting Tray:0.5Kg Electrical • Power supply: 28V DC • Power consumption: 28 Watt Interfaces • MIL-STD-1553B • ARINC-429 • ETHERNET • RS232 • RS422 • RS485 Standards Compliance • VOR: DO-196 • LOC: DO-195 • GLIDE SLOPE: DO-192 • MARKER: DO-143 • MIL-STD-810G for Environmental tests. • MIL-STD-461E for EMI/EMC tests. • MIL-STD-704F for Power supply conditions PLATFORM Proposed • ALH, DORNIER
23 ANS SERIES-VOR/ILS/ MARKER RECEIVER Designed & Developed by SLRDC
ANS SERIES-VOR/ILS/MARKER RECEIVER KEY FEATURES
For critical flight regimes, HAL’s ANS series VOR-ILS systems provide • Low power, lightweight solid-state design today’s flight crew with dependable, highly accurate bearing and landing • Digital Radial/bearing Out information. This real- time system enhances operational safety during all-weather approaches and Landings. • FM broadcast immunity per ICAO Annex 10 The ANS family of VOR/ILS/MKR systems are recognized as a value • Marker receiver for runway approach added solution on multiple military platforms. The ANS series systems • VOR receiver for route navigation quickly gained acceptance as robust VOR-ILS solution and are installed • ILS receiver for landing on a multitude of platforms including SU-30, MIG-29UPG, MIG-29K/KUB, IJT, LCA (A/F), LCA (NAVY), MIG-21UPG (BISON), JAGUAR/DARIN-III, • DSP technology HAWK-AdT. • No of channels : VOR : 160 channels LOC/GS: 40 channels The ANS 1100A/ANS1101A/ANS2810A/ ANS2820A is a proven design • MIL-STD-1553B / ARINC-429 interface derived from extensive experience in navigation, precision approach and landing systems. • VOR as per RTCA DO-196 Solid-state modular design and rugged construction provide long life, • LOC as per RTCA DO - 195 high reliability and excellent maintainability for both new and retrofit • GS as per RTCA DO - 192 applications on fixed-wing aircrafts. • Marker as per RTCA DO - 143 The receiver combines all VOR/ILS/MKR functions in one compact, Additional Options: lightweight, low cost system. The ANS series meets multiple stringent MIL-STD requirements • ARINC based VOR/ILS controller assuring peak performance under the harshest Military aircraft • ARINC based Interface Unit (IFC) to drive the INPR display environments. With support for both analog and digital interfaces, the ANS is compatible with a variety of aircraft architectures. The ANS 1100A/ANS1101A/ANS2810A/ANS2820A is available to meet FM broadcast Immunity requirements as defined in ICAO Annex 10. Combination of our rich experience with latest digital technology makes HAL VOR/ILS/ Marker Receiver the affordable choice for users.
SPECIFICATIONS
PHYSICAL SPECS Sensitivity: LOC: - 99dBm Dimensions 318mm x 194mm x 57.2mm Glide: - 87dBm (¼ ATR short) VOR: - 99dBm Weight < 3.3 Kg (without mounting tray) MKR:- 67dBm±3dBm ELECTRICAL SPECS (High Sensitivity), Power Supply 28 V DC as per MIL-STD-704D -53dBm ± 3dBm Power Consumption 35 W (Max) (Low Sensitivity) Current Rating 1.2A Max at 28 V DC Accuracy: LOC:- 72dBm to-33dBm INTERFACE Glide: - 76dBm to-33dBm Digital Outputs MIL-STD-1553B, ARINC 429 VOR: - 93dBm to-27d8m Audio Output ILS/VOR : 1 to 100mW Self-test POST, IBIT and CBIT. (adjustable)/600 ± 20Ω QUALIFICATION and COMPLIANCE MARKER: 10 to 100mW EMI/EMC MIL-STD 461 (adjustable)/600 ± 20Ω Environmental MIL-STD 810F SYSTEM PARAMETERS Reliability (MTBF) >5000 Hours as per MIL Frequency Range: LOC : 108.10 to 111.95 MHZ HDBK 217 GLIDE : 329.15 to 335 MHZ PLATFORMS SU-30 MKI, MIG-29UPG, MIG VOR : 108.00 to 117.95 MHZ 29K/KUB, JT, LCA (A/F), LCA MKR : 75 MHZ (NAVY), MIG-21UPG(BISON), Number of channels LOC : 40, GLIDE : 40, VOR : 160 JAGUAR/DARIN-II/DARIN-III, HAWK-AJT
24 ADVANCED TACAN (TACTICAL AIR NAVIGATION) Designed & Developed by SLRDC
ADVANCED TACAN KEY FEATURES (TACTICAL AIR NAVIGATION) • Pilot selectable channel type (252 channels: 126X and 126Y) and ADVANCED TACAN (Tactical Air Navigation) is a polar coordinate frequency through mission Computer/ Display. type radio air navigation system that provides aircrew with range • High-speed 32-bit DSP processor is used for acquisition of distance and and bearing (azimuth) information on the ARINC429 / MIL 1553B bearing, time to go computation and system operation. Bus for display on the Mission Computer/CDU. Using this • Time to go computation for velocities from 10-1500 knots. information, pilot can fly directly to particular location or use the bearing and distance from a specific beacon to fix his geographic • GaN based 500W transmitter for better efficiency. location. The range in nautical miles indicates the distance of the • Pulse generation through digital for better pulse modulation aircraft from the surface beacon. The bearing indicates the characteristics. direction in degrees with respect to Magnetic North. TACAN can • Log amp based super heterodyne for covering the wide dynamic range of transmit, receive and process time coded pulse pairs or single 90dB. pulses. The design is based on solid-state Transmitter with GaN • Instantaneous dynamic range of 40dB to acquire the signal during flight (Gallium Nitride) based Power Amplifier technology, Log amp maneuvers. based Super heterodyne receiver for wide dynamic range, High • Beacon identification facility in the form of digital audio output whose speed 32 bit DSP, FPGA and ARINC429 / MIL 1553B Bus interface. power can be controlled through 1553. The system has extensive built in test facility for easy testability • ARINC429 / MIL 1553B Bus compatibility for both input and output and flash for recording system parameters during flight for post functions. flight system performance analysis. In-situ feature completes • Lightning protection as per DO-160E level 3 waveform 3. the software loading without disassembly. • Recording of system parameters during flight for post flight analysis. ADVANCED TACAN is backward compatible with existing TACAN • Operating Modes: which is fitted on various aircrafts like SU-30, MIG-29UPG, MIG- 29K/KUB, IJT, JAGUAR DARIN-II / III, LCA, HTT40 and HAWK. a) T/R (with ground beacon and airborne beacon) Combination of our rich experience with latest digital technology b) Receive (with ground or airborne beacons) makes HAL TACAN the affordable choice for users. c) A/A (air to air with another aircraft equipped with same TACAN system) SPECIFICATIONS
Parameter Specifications Audio power output 100mW (± 2 dB) on a 600 Ω Power Output of transmitter 500W (peak) Min load. Power output can be Frequency range Tx: 1025-1150 MHZ controlled through MIL 1553 Bus. Rx: 962-1213 MHZ Suppression interface Bi Directional Receiver Sensitivity and -90dBm to 0dBm for Range. Mechanical dimensions and 280 mm X 75 mm X 194 mm dynamic range weight and weight: 4.0 Kg(Max) -87dBm to 0dBm for Bearing. Power Supply 28V DC: Max: 50Watts. Range Tracking capability 0 to 300Nm. Accuracy : ± 0.1Nm Qualifications & Compliance 0 Bearing ± 1 throughout dynamic range EMI/EMC MIL-STD-461E Distance acquisition time ≤ 2 seconds Environmental MIL-STD-810G Bearing acquisition time ≤ 4 seconds Power Supply MIL-STD-704F Memory time ≤ 15 seconds. Software Compliance DO-178B Level C. Time to go 10-1500 Knots, Settling time:40 Hardware Compliance DO-254 Seconds, Anticipated Platforms LCA, MK1A, HTT-40, LUH, Accuracy: ± 30 Seconds. Su-30 Upgrade, HAWK Upgrade Control and data Output MIL 1553B/ ARINC 429 Advanced HAWK
25 ADVANCED RADIO ALTIMETER - RAM 2700A Designed & Developed by SLRDC
ADVANCED RADIO ALTIMETER - RAM 2700A KEY FEATURES
• DSP-based C-Band FMCW Radio Altimeter For critical flight regimes, HAL’s Radio Altimeters provide today’s flight • Capability to operate in all weather, including heavy crews with dependable, highly accurate altitude information above rain and snow & terrain like Land, water, Grass etc ground-level (AGL) information. This real-time system enhances • Digital & analog outputs operational safety during takeoff, landing, night time operations, and • Variable power output as per range for LPI hazardous flight above rough terrain • Leading edge tracking technique Designed for applications such as helicopter and combat fighter • Extensive BITE facility for checking the unit operations where accuracy is needed down to zero feet, RAM 2700A is the serviceability. “State-of-the art” FMCW Digital Radio altimeter operating in C-Band • High resolution accuracy and measures accurate altitude of the aircraft over the terrain. • Doppler effect immune RAM 2700A, with its MIL-STD-1553 data bus can be easily coupled with • Roll & Pitch limit operation Aircraft display, mission computer and instrumentation. Proven and • No forced air cooling is required precise, this system offers improved situational awareness for a broad • Thermal drift sustainability during flight range of fixed and rotary wing aircraft. HAL has over 30 years experience in Radio Altimeters and our systems are successfully proven on various aircrafts like SU-30, MIG-29UPG, MIG-29K/KUB, IJT, MIG-21UPG (BISON), JAGUAR/DARIN-III, ALH, MIG 27 etc. Combination of our rich experience with latest digital technology makes HAL Advanced Radio Altimeter the affordable choice for users.
SPECIFICATIONS
Dimensions 124W X 160 D X 170 H mm SYSTEM PARAMETERS (without mounting tray) Altitude Range 0 to 20,000ft 135W X 230D X 192H mm Altitude Accuracy 0 to 20,000ft ± ( 2ft + 1% H ) (with mounting tray) Pitch Limit ± 30 ° with S67-2002 Antenna Weight < 3 Kg Roll Limit ± 30° with S67-2002 Antenna (without mounting tray) Tx-Frequency 4200 to 4400 MHZ < 3.7 Kg Frequency 123 ± 2.5 MHZ (with mounting tray) Tx-Power output 10 mW to 1 W Max (Variable) ELECTRICAL SPECS Acquisition time < 800 msec Power Supply 28 V DC as per MIL-STD-704D AID 35 ft(Software Configurable) Radio Silence Less than - 10 dBm Power Consumption 35 W (Max) Self test POST, IBIT & CBIT. Current Rating 1.2 A Max at 28 V DC QUALIFICATION & COMPLIANCE INTERFACE EMI/EMC MIL-STD 461 E Digital Altitude Outputs MIL-STD-1553B,RS 422, Environmental MIL-STD 810F ARINC 429 Reliability MIL-STD-217F Analog Altitude Output As per user requirement: Software compliance DO-178 B & DO-254 compliant Antenna S67-2002 PLATFORMS Jaguar Darin III, LCA, SU-30
26 IDENTIFICATION OF FRIEND OR FOE TRANSPONDER WITH ADS-B Out IFFT-2460ALH1 Designed & Developed by SLRDC
IDENTIFICATION OF FRIEND OR FOE KEY FEATURES TRANSPONDER WITH ADS-B Out IFFT-2460ALH1 • Interrogation/Response Identification system for MKXII, Mode S Level 2 The advance IFF products enable war fighters to identify as per STANAG 4193, RTCA DO-181D and ICAO Annex-10 Standard. friendly forces and make correct decisions in time- • Frequency of Operation 1030 MHz on Receive, 1090 MHZ on Transmit. critical situations. The IFF MKXII(S) Transponder-(IFFT)is • ADS-B out feature as per DO- 260B standard an airborne electronic identification equipment to • TCAS-II Compatible identify friendly aircraft from enemy by assigning unique identifier code to friendly aircraft transponders. The • Acquisition Squitter Transmission for Aircraft Address Acquisition. system supports Mode 1, 2, 3/A, C, IS1 and Civil Mode S • Selectively Addressed Interrogation/Reply. Level 2 features as per STANAG 4193, ICAO Annex-10 • Elementary and Enhanced Surveillance. Standard and ADS-B Out feature as per RTCA DO-260B • SAG Certified Crypto for Indian Secure Mode (IS1) for Interoperability. standard. • Enhanced Surveillance provides Aircraft Vertical Intentions, Track and Turn Indian Secure mode (IS1) is provisioned exclusively for Report, Magnetic Heading and Speed Report. military purposes. In this mode of operation, the • 1553B/ARINC-429 bus compatibility for both I/O functions. interrogation and reply information are encrypted for • Dual channel Digital Receiver for space diversity. transmission & Decrypted for reception of secured • Solid States transmitter with nominal output of peak power. military information. • Pilot selectable operating modes through Mission Computer/ Display. HAL has over 40 years experience in IFF Transponders • BITE facility is available for checking the unit serviceability. and our systems have proven performance in various aircrafts like JAGUAR DARIN-III, DORNIER, ALH MKIII, • Suppression IN/OUT facility for interface. IN-SITU Programmable BOEING P8I, HTT-40, SU-30, MIG-29UPG, MIG 29K/KUB, MIG-21UPG (BISON), MIG 27, etc. Our unique combination of deep experience with a modern digital implementation makes HAL Transponders the only affordable choice for users.
SPECIFICATIONS
Parameter Specifications Transmitter Frequency 1090 ± 0.5MHz Dimensions 90W X 380D X 195 H mm Transmitter Power output 57 ± 2 dBm (peak) Weight 7 Kg Max Dynamic Range MTL to -22dBm ELECTRICAL SPECS Cooling Conduction Self test POST, IBIT & CBIT. Power Supply 28 V DC as per MIL-STD-704D QUALIFICATION & COMPLIANCE Power Consumption 125 W (Max) EMI/EMC MIL-STD-461 E Boot up Time <60 sec Environmental MIL-STD 810F INTERFACE M IL-STD-1553B Reliability MIL-STD-217F ARINC 429 (Optional) Software compliance DO-178 B & DO-254 SYSTEM PARAMETERS compliant Receiver Frequency 1030 ± 0.5MHz PLATFORMS Rotary & Fixed wing Sensitivity -73dBm to -79dBm Aircraft
27 IDENTIFICATION OF FRIEND OR FOE INTERROGATOR (IFFI-3400A) Designed & Developed by SLRDC
IDENTIFICATION OF FRIEND OR KEY FEATURES FOE INTERROGATOR IFFI-3400A • Interrogation/Response Identification system for Airborne IFF interrogator (IFFI 3400A) is a state-of-the art MK- MKXII as per STANAG 4193 and ICAO Annex-10 Standard. XII interrogator radar with advance leading edge technology. • Frequency of Operation 1090 MHz on Receive, 1030 Airborne IFFI 3400A is equipped with latest high speed digital MHZ on Transmit. processing implemented in FPGAs & multicore processor which • 1553B bus compatibility for both I/O functions. can perform accurate identification of targets in hostile • Handles up to 100 targets environments. IFFI3400A can be used as a standalone system • Processing range upto 250Km with independent E-Scan System or can be coupled to primary • Dual channel Digital Receiver for Monopulse radar to share the same antenna platform. operation. The IFFI- 3400A incorporates all advanced features required in • Pilot selectable operating modes through Mission today's global military air traffic control environment, designed Computer/ Display. and developed for airborne application. • BITE facility is available for checking the unit serviceability. • Interfaces : RS422, MIL-STD 1553B, Ethernet. • Suppression IN/OUT facility for interface.
SPECIFICATIONS
Parameter Specifications Transmitter Frequency 1030 ± 0.1MHz Dimensions 157W X 380D X 194H mm Transmitter Power output 62 dBm (peak) (Typ.) Weight 10 Kg Dynamic Range 60dB ELECTRICAL SPECS Cooling Conduction Power Supply 28 V DC as per MIL-STD-704D Self test POST, IBIT & CBIT. Power Consumption 125 W (Max) QUALIFICATION & COMPLIANCE INTERFACE EMI/EMC MIL-STD-461 C/ E Interrogator interfaces MIL-STD-1553B, RS 422 & Environmental MIL-STD 810F Ethernet Reliability MIL-STD-217F SYSTEM PARAMETERS Software compliance DO-178 B & DO-254 Receiver Frequency 1090 ± 0.5MHz compliant Sensitivity -80dBm (Typ.) PLATFORMS Rotary & Fixed wing Aircraft
28 COMBINED INTERROGATOR AND TRANSPONDER (CIT) Designed & Developed by SLRDC
COMBINED INTERROGATOR AND TRANSPONDER (CIT) KEY FEATURES
Combined Interrogator and Transponder (CIT) - is a IFF MK XII • Total in-house design and development of dual channel high system designed and developed for Airborne application to power transmitters with RF pulse power greater than 1KWatt. identify friend or foe (IFF). These systems are essential in the • Dual Channel Receiver for Transponder for Diversity application. battlefield to positively identify enemies and friends. CIT is a • High-Speed Multi-core Processors, FPGA with high Processing state of the art system to cater for both military and civil aircraft Power for Reply processing & acquisition of target data. requirements. CIT can Interrogate the designated target and at • Software Compliant to DO254 and DO178 the same time it can respond to the interrogations received from • Compliant to STANAG 4193 & ICAO annexure-10 Standard. other Interrogators to provide its identity. The main Functional • Compatibility to E-SCAN & M-SCAN antennas. Modes for the Interrogator are Search, Sector search and • TCAS compatibility through ARINC 429 interface. Challenge. Integration of CIT in attack, reconnaissance and • Ruggedization, Conduction Cooling, High shock and vibration surveillance aircrafts will improve the tactical situations resistant. awareness. • Option to integrate with existing RADAR or install as independent system with Antenna Control Unit and E Scan Antennas
SPECIFICATIONS
Parameter Specifications Minimum decoding level -76dBm System CIT 4100A CIT 4400A Mode-S squitter YES Interrogator COMPLIANCE Modes of Operation Mode 1, 2, 3/A, C & Mode 4(IS1) System design STANAG 4193 and ICAO Annex 10 Transmitter Frequency 1030± 0.2 MHZ 1030± 0.1 MHZ Software compliance DO-178 B & DO-254 Transmit Power 1.2KW (Typical) 2KW (Typical) ENVIRONMENTAL MIL-STD 810G , MIL-STD 461 E Minimum decoding level >-79 dBm >-83dBm PHYSICAL SPECS Target Processing Range 200Km 400Km Dimensions 385DX 190WX193H mm CIT : 385DX190W No of Targets Per Sector 32 X193H mm Transponder: ACU: 260DX264WX Modes of Operation Mode 1,2,3/A, C& Mode 4(IS1), 128H mm Mode-S (Level-2) Weight <12 Kg CIT: <12Kg Transmitter Frequency 1090± 0.5 MHZ ACU : <6 Kg Transmit Power 350W (Typical) ELECTRICAL SPECS Power Supply 28 V DC as per MIL-STD-704E INTERFACES MIL-STD-1553B, RS 422 , ARINC 429, Ethernet PLATFORMS Fixed wing military aircrafts
29 AUTOMATIC IDENTIFICATION SYSTEM (AIS) Designed & Developed by SLRDC
KEY FEATURES
Automatic Identification System Receiver Unit • Three Separate identical RF receivers to receive & process two AIS and one (AIS) is an Integrated Automatic Identification DSC RF signal. System (AIS) & Digital Selective Calling (DSC) • AIS receiver unit comply with Class A receiver specification as per “ITU-R receiver which operates in VHF Maritime Band M.1371-5“document. 156.025MHz to 162.025MHz. • AIS receiver unit support the RS-422 serial bus interface. AIS Receiver Unit receives static and dynamic • AIS receiver unit receive the Aircraft positional data from Mission information from AIS Transponder/Base Station, Computer/GPS receiver. decodes and communicates the ship's information • AIS receiver unit data exchange as per IEC 61162 / NMEA0183 protocol. in NMEA (National Marine Electronic Association) • Channel Management as per AIS Message 22 or DSC command. format to Mission Computer and Surveillance • AIS receiver unit has LED lamp to indicate the AIS unit health status on Radar through RS-422 serial interface. front panel. • AIS receiver unit has a comprehensive built in testing (BIT) capability.
S P E C I F I C AT I O N S
PARAMETERS SPECIFICATIONS Physical • Dimensions (L X W X H): 178 X 134 X 89 (mm) • Weight: 2 Kg (max) • Mil D38999 connectors for interface Electrical • Power supply: 28V DC • Power consumption: 28 Watt Interfaces • RS422 (3 Channels) • RS232 (1 Channel) • ARINC-429(2 Rx and 1 Tx) • In-situ Programming facility. Standards Compliance • ITU-R M.1371-5 for AIS & DSC Rx. • MIL-STD-810G for Environmental tests. • MIL-STD-461E for EMI/EMC tests. • MIL-STD-704F for Power supply conditions PLATFORMS • ALH, DORNIER
30 FLIGHT CONTROL SYSTEM
31 AUTOMATIC FLIGHT CONTROL COMPUTER (AFCC) Designed & Developed by SLRDC
KEY FEATURES
• PowerPC,32-Bit Processor • Real-Time Operating System • Dual-Redundant System with Inter-Processor Communication. • Handling 189 Nos. of Input / Outputs Signals • IO Interface card • 18-Layer Flex-Rigid Mother Board AUTOMATIC FLIGHT CONTROL • Metal-Core PCB’s for better Thermal management COMPUTER (AFCC) • State-of-the-art Surface Mount Devices, Hybrids & BGA packages. Automatic Flight Control Computer (AFCC) drives Series and trim actuators in pitch, roll, yaw and collective axes TECHNOLOGY for Light Combat Helicopter (LCH).The AFCC is a real- time airborne computer with two processing channels • COTS, Modular design approach with inter-processor synchronization and data • Short circuit protection. communication. • Lightning protection (level 4 with Waveform 4) as per AFCC receives data from various Sensors, two Pilot Control Units (PCU), control sticks and Cockpit. It DO-RTCA 160D performs control law computation and generates • Series and Trim Actuator Drive circuit and Safety Logic actuator control command signals to series actuators • Ruggedization, Conduction Cooling, High shock and (Electro hydraulic actuators) and Parallel (trim) vibration resistant. actuators.
SPECIFICATIONS
Parameter Specifications No of inputs 189 Dimensions 394(W x 154(D) x 197(H)mm Output Current for series actuator Weight 7.45Kg Pulse width modulation for ELECTRICAL SPECS trim actuator Power Supply 28V Axis control Pitch, Roll, Yaw and Power Consumption 180W Collective INTERFACE COMPLIANCE Communication interface RS232(2Nos)/422 (3Nos), EMI/EMC MIL-STD-461F Ethernet (2 Nos), ARINC-429 Power supply standard MIL-STD-704F (10Tx & 20 Rx) and 1553B (2Nos) Environmental MIL-STD-810G SYSTEM PARAMETERS Reliability 3000Hrs Cooling Conduction cooling Software & Hardware RTCA DO-178B & 254 Self test PBIT, IBIT & CBIT PLATFORMS LCH
32 RECORDING SYSTEM
33 SOLID STATE DATA & VIDEO RECORDING SYSTEM (SSDVRS) Designed & Developed by SLRDC
SOLID STATE DATA & KEY FEATURES VIDEO RECORDING SYSTEM (SSDVRS) • Simultaneously records all the video inputs, audio inputs and data channels. Solid State Data and Video Recording System (SSDVRS) is an airborne equipment for Light Combat Helicopter • Capable of continuous recording for 4 hours of all the channels. (LCH). The system has six video input channels, two • Video, Audio and Data are time synchronized. audio input channels, two MIL STD 1553B bus channels • Both the audio inputs are mixed together and combined with the video and and two RS422 channels. All channels will be recorded stored in the removable memory module. simultaneously for 4 hrs continuously. System has one • Capable of playing back recorded video data on one of the on-board MFDs video output with dual redundancy for in flight replay of (MFD is selected by pilot) selected video channel. • Records hardware event markers, which are discrete inputs to the system. • Records software event markers received on Mission 1553B bus. Ground Replay Station provides facility to download the • Event information is stored as a separate file. recorded video and audio data along with event • Recorded video, audio and data shall be downloaded from Removable markers from the Removable Memory Module (RMM) Memory Module (RMM) for requirement of post analysis in Ground Replay for replay and analysis in a time synchronized manner Station (GRS). during post flight debrief. • In case of an emergency, it is possible to erase the complete stored data HAL has over 60 years experience in Various avionics upon a discrete command from pilot systems and our systems have hard won, proven • The various controls present in the system are Start, Stop, Rewind, Forward, performance in various aircrafts like SU-30, MIG- Play, Pause, Jump to event, Jump to time, Play frame by frame and Erase. 29UPG, MIG-29K/KUB, IJT, MIG-21UPG (BISON), These controls are available through MIL 1553B bus. JAGUAR/DARIN-III, ALH, MIG 27 etc. • Individual channel selection for Record / Erase / Playback.
SPECIFICATIONS
Parameter Specifications DVI Outputs 2 Nos. Dimensions 148 W X 164L X 120 H mm Audio Output 1 No Weight 4.7 Kg Recording Duration 4 hours ELECTRICAL SPECS Memory Size 128GB (Expandable up to 256 GB) Power Supply 28 V DC as per MIL-STD-704D Compression H.264 Power Consumption 60 W (Max) Discretes Hardware : 8 INTERFACE Software : 32 SSDVRS interface to MIL-STD-1553B Cooling Conduction Mission computer Self test PBIT, CBIT & IBIT. SYSTEM PARAMETERS Ground Replay Station Data down loading and debrief DVI Inputs 4 Nos. QUALIFICATION & COMPLIANCE EMI/EMC MIL-STD-461 F Composite Videos (PAL) 2 Nos. Environmental MIL-STD 810G Audio inputs 2 Nos. Reliability MIL-STD-217F MIL-STD-1553 B 2 Nos. Software compliance DO-178 B Compliant RS 422 2 Nos. PLATFORMS Rotary & Fixed wing Aircraft
34 COCKPIT VOICE AND FLIGHT DATA RECORDER - CVFDR
Designed & Developed by ASERDC HAL KORWA
KEY FEATURES
Flight Data Recorder is a critical equipment to record • Digital recorder of flight parameters received from flight parameters & voice, to ascertain the health of the Arinc429 and Arinc 717 channels, audio. various systems and to perform the aircraft post- • Recording in crash protected solid state memory. incident/ accident analysis for investigating/ establishing • High MTBF & Improved Data Security the cause of incident/ accident by reconstructing the • Equipped with Under Water Locator Beacon cause of the events. ASERDC & Avionics Division HAL • High Data Rate of Retrieval & Channel wise Audio Data Korwa has evolved into a Centre of Excellence for design Download development, manufacturing and repair of SSFDRs and • Modular design benefits with high degree of adaptability associated Ground data retrieval systems for most of the • Software Design and development as per DO-178B aircraft used by Indian defense services • Qualification as per MIL-STD-810F/ MIL-STD-461E • Sortie based & Complete Memory Data Retrieval
SPECIFICATIONS
Power 28 V DC, 40 watts, max Environmental in compliance with Temperature Operating: -40 to +71 deg C MIL STD 704D Storage : -55 to +85 deg C Physical SIZE WEIGHT Altitude 7 Km DRU 260mmx 120mmx 3.5Kg Qualification MIL STD 810F 128mm EMI/EMC MIL STD 461 E CU 144mm x 81mmx 70mm 0.37Kg PMM 384 MB compliance to Main Connector TSO C124a D38999 Series III with EMI filtering and Lightning protection Impact shock 3400g, 6.5 ms half sine Recording Time 25 hrs of data, Fire Protection 1100 deg C, 60 min, 2 hrs of Audio (4 channels) 260 deg C 10hrs Parameters ULB 90 days operation with Analog , Discrete, Frequency received from Arinc 429 and Arinc 6 years battery life 717 channels. Ground Replay Handheld Rugged Laptop based GRE Equipment for download and playback
35 SOLID STATE FLIGHT DATA RECORDER - SSFDR Designed & Developed by ASERDC HAL KORWA
KEY FEATURES
Flight Data Recorder is a critical equipment to record flight • 3 LRU system with data acquisition of flight parameters, audio and parameters & voice, to ascertain the health of the various recording in crash protected solid state memory. • High MTBF & Improved Data Security systems and to perform the aircraft post-incident/ accident • Equipped with Under Water Locator Beacon analysis for investigating/ establishing the cause of • High Data Rate of Retrieval & Channel wise Audio Data Download incident/ accident by reconstructing the cause of the events. • Sortie based & Complete Memory Data Retrieval ASERDC & Avionics Division HAL Korwa has evolved into a • On board 10GB storage in DAU for HUMS purpose Centre of Excellence for design development, • Multiprocessor system based on PowerPC and ADSP processor. manufacturing and repair of SSFDRs and associated Ground • FPGA/ CPLD technologies adopted data retrieval systems for most of the aircraft used by Indian • Modular design benefits with high degree of adaptability defence services • Software Design and development as per DO-2167A • Qualification as per MIL-STD-810F/ MIL-STD-461E • Online flight parameter monitoring for DAU Calibration • High Speed Ethernet based Data Downloading
SPECIFICATIONS
Power 28 V DC, 60 watts, max in compliance Environmental MIL STD 704D Temperature Operating: -40 to +65 deg C Physical SIZE Weight Storage : -55 to +85 deg C DAU 360mmx 180mmx 150mm 8 Kg Altitude 80000 ft RU 306mmx 124mm x 125mm 6 Kg Qualification MIL STD 810F CIU 178mmx 100mm x 70mm 1 Kg EMI/EMC MIL STD 461 C Main Connector PMM 384 MB compliance to TSO D38999 Series III for Signal, DK621 for 1553 C124a Recording Time Impact shock 3400g, 6.5 ms half sine DAU 10 hrs of data, Fire Protection 1100 deg C, 60 min, 10 hrs of Audio (2 channels) 260 deg C 10hrs RU 25 hrs of data, ULB 90 days operation with 2 hrs of Audio (2 Channels) 6 years battery life Parameters Ground Replay Handheld Rugged Laptop Analog , Discrete, Frequency, Arinc 429, MIL 1553 Bus parameters Equipment based GRE for download and (> 7000 parameters) playback
36 CRASH PROTECTED MEMORY MODULE (CPMM) Designed & Developed by ASERDC HAL KORWA
KEY FEATURES
Flight Data Recorder is a critical equipment to record flight • Titanium Alloy based Metallic Housing. parameters & audio, to ascertain the health of the various • Incorporates thermal barrier for fire and heat resistance systems and to perform the aircraft post-incident/ accident • Mechanical Housing Supports mounting of Under Water locator Beacon. analysis. Crash Protected Memory Module is part of SSFDR • 384 MB storage capacity Crash Protected Memory to record critical and complies to crash survivable conditions as per TSO Flight parameters and cockpit voice. C124a. • High MTBF & Improved Data Security ASERDC & Avionics Division HAL Korwa has evolved into a • Flex rigid PCB interface for easy connectivity with host electronics. Centre of Excellence for design development, • Modular design benefits with high degree of adaptability manufacturing and repair of CPMM of SSFDRs and data • Interfaces with FDR using Glue logic and compact flash interface retrieval in event of crash for most of the aircraft used by • Qualification of Module as per TSO C124a for crash survivability. Indian defence services • Qualified with FDR as per Mil STD 810D, MIL STD-461C for environmental and EMI/EMC .
SPECIFICATIONS
COMPLIANCE ED112 Environmental TSOC 124a Crash Survivable Temperature Operating: -40 to +65 deg C Conditions Storage : -55 to +85 deg C Physical Qualification MIL STD 810D Size Length 146 mm x Dia 92 mm EMI/EMC MIL STD 461C Weight 2.5 kg Memory 384 MB Penetration 230 Kg from 3m Height Impact shock 3400g, 6.5 ms half sine Resistance (Pin Dia – 6.35 mm) Fire Protection 1100 deg C, 60 min, Static Crush 22.25 KN in all six axes 260 deg C 10hrs Deep Sea Pressure ` 60 MPa (at 6000m Depth) ULB support 90 days operation Immersion in Fluids Salt water, Kerosene, aircraft with 6 years battery life fluid etc.
37 SOLID STATE FLIGHT DATA RECORDER/ COCKPIT VOICE RECORDER -SSFDR/CVR Designed & Developed by ASERDC HAL KORWA
KEY FEATURES
Flight Data Recorder is a critical equipment to record • Integrated data acquisition of flight parameters, audio and recording in flight parameters & voice, to ascertain the health of crash protected solid state memory. the various systems and to perform the aircraft post- • High MTBF & Improved Data Security incident/ accident analysis for investigating/ • Equipped with Under Water Locator Beacon establishing the cause of incident/ accident by • High Data Rate of Retrieval & Channel wise Audio Data Download reconstructing the cause of the events. ASERDC & • Sortie based & Complete Memory Data Retrieval Avionics Division HAL Korwa has evolved into a Centre • Dual ARM processor based system Design. of Excellence for design development, manufacturing • FPGA/ CPLD technologies adopted and repair of SSFDRs and associated Ground data • Modular design benefits with high degree of adaptability retrieval systems for most of the aircraft used by • Software Design and development as per DO-178B Indian defense services • Qualification as per MIL-STD-810F/ MIL-STD-461E • In Built FMS function in addition to FDR/CVR functions
SPECIFICATIONS
Power Environmental Requirements 12-28 V DC, 40 watts, max Temperature Operating: -40 to +71 deg C in compliance with Storage : -55 to +85 deg C MIL STD 704D Altitude 7 Km Physical Qualification MIL STD 810F Size 264 mmx 128 mm x 130 mm EMI/EMC MIL STD 461 E Weight 3.5 kg PMM 384 MB compliance to ED112 Main Connector Impact shock 3400g, 6.5 ms half sine D38999 Series III with EMI filtering and Lightning protection Recording Fire Protection 1100 deg C, 60 min, Time 25 hrs of data, 260 deg C 10hrs 2 hrs of Audio (4 channels) ULB 90 days operation with Parameters 6 years battery life Analog , Discrete, Frequency, Resistive, Thermocouple and digital Ground Replay Handheld Rugged Laptop based GRE parameters on Arinc429 bus. Equipment for download and playback
38 MISSILE ELECTRONICS
39 RADIO PROXIMITY FUZE (RPF) Designed & Developed by SLRDC
KEY FEATURES
Radio Proximity Fuze (RPF) is a short range • MMIC (monolithic microwave integrated circuit) based Ku-band continuous wave Radar. It is one of the subsystems Transmitter & Receiver design in the missile system. The purpose of RPF is to • Ku-band Hybrid Radio Frequency multilayer PCB design detect the target within a specified Range & • Real time signal processing (Matched filter, Fast Fourier Transform, velocity and communicate the Range & Velocity Constant False Alarm Rate thresholding) using high density miniaturized information to missile On Board Computer and digital signal processing board. Telemetry. It gives detonation command to • Extensive BITE facility warhead at an optimum instance of time, to cause • Digital Radio Frequency Memory (DRFM) based target simulator for real target kill. time target simulation.
S P E C I F I C AT I O N S
PARAMETERS SPECIFICATIONS Physical • Dimensions (L X W X H) : 250 X 170 X 55 ( mm) • Weight: 2.5Kg (max) Electrical • Power supply: 28V DC • Power consumption: 50 Watt System Parameters • Frequency of operation : Ku-band • Detection range : 3 to 150mts • Range resolution : 1.5mts • Detection velocity : 100 to 4000 m/s • Velocity resolution : 10 m/s • Transmitter RF power output: 33 dBm (2W) CW • Receiver Sensitivity : -104 dBm Interfaces • RS-422 • In-situ Programming facility. Standards Compliance. • MIL-STD-810G for Environmental tests. • MIL-STD-461E for EMI/EMC tests. • MIL-STD-704F for Power supply conditions • DO-254, Level-B PLATFORMS • AKASH, ASTRA, AAD, AKASH-1S and AD1 missiles
40 MISSION, COMBAT AND DISPLAY SYSTEM
41 Mission Computer for Mirage 2000 Designed & Developed by MCSRDC
KEY FEATURES
Mirage Mission Computer designed & developed • Generates graphic output for display on MFDs by MCSRDC-HAL performs management of LRUs • Weapon Aiming Computations, Sensor Management & System Mode of Indian Specific Systems, Weapons and Sensors Management used in Final Operation Clearance (FOC) • Provides acquisition and storage of fault list for maintenance configuration. • Receives sensor data, MMI and Mission data from IOC computer via Ethernet interface • Video switching and Graphics overlay capabilities
S P E C I F I C AT I O N S
PARAMETERS SPECIFICATIONS Dimension (LxWxH) 320±2 X 124±2 X 200±2 (mm) Weight 10.5 ± 0.5 Kgs Operating Voltage 115/200 V, 400 Hz, 3Ø AC or 16 to 31.5VDC Power Consumption 200 Watts a) ½ ATR chassis design b) Two PowerPC based processor modules & c) Graphics generation with GPU Technology Used d) VME64x hybrid backplane. e) 08 Nos of 32-Bit General Purpose Timers f) OS Support: Greenhill’s INTEGRITY g) Conduction Cooled Chassis Discrete Inputs / Output 08 No’s / 24 No’s Analog Input / Outputs 02 No’s each Video Input / Outputs 06 No’s / 04 Nos. MIL-STD-1553 02 Channels Ethernet 03 Channel RS-422 / RS-232 02 Channel / 04 Channel
42 Jaguar Darin III Mission Computer Designed & Developed by MCSRDC
KEY FEATURES
The Jaguar DARIN-III Mission computer (JD3MC) • Generates independent graphic output for display on SMFDs. designed & developed by MCSRDC-HAL has the • Stroke symbol generation for Head-up display capability to perform the full range of Mission • Navigation and guidance computation, Weapon Aiming Computations, functions. Sensor Management & System Mode Management • Four MIL 1553B bus control • Video buffering, Video format conversion and Video Switching, Symbology generation for HUD, Display Management for single/Dual HUD& UFCP Interface with the various sensor
S P E C I F I C AT I O N S
PARAMETERS SPECIFICATIONS Dimension 356.5x190.5x193.5 mm (3/4 ATR) Weight 15.5 Kg(max) Operational Voltage 115V AC,400Hz & 28V DC Power Consumption 200 Watts(max) Technology Used a) Power PC based architecture; inter-processor communication is based on switched serial fabric using industry PCIe communication protocol b) Modular Design c) Module Re-Configurability d) VPX Standard(VITA-46) Backplane e) Conduction Cooled Chassis f) OS Support: VxWorks Analog Input / Outputs 11 No’s / 08 Nos. Synchro Input / Outputs 06 No’s/ 01 No. Discrete Inputs / Outputs 122 No’s / 39 No’s MIL-STD-1553B 04 Channel RS-422 / RS-232 06 Channel / 02 Channel Ethernet 2 No’s Video Input / Output 2 No’s (1 Composite and 1 RGB) / 4 No’s (1 RGB, 2 Composite video , 1Y/C)
43 Mission Computer (MC) for Hawk- i Designed & Developed by MCSRDC
KEY FEATURES
The HAWK-i Mission Computer is the main • Three Power PC based processor modules operating at 1 GHz max controller for the upgraded avionics of HAWK • Generates graphics, symbology and drives the MFDs for display . Graphic Mk132 A/c and is indigenously designed & generation with GPU at 600 MHz max developed by MCSRDC-HAL. • cPCI Flexi-rigid hybrid backplane with routing for approx. 250 I/O lines • Data/symbols overlays on to the external videos and displays it on MFDs/HUD • Inbuilt Digital Map generator (2D and 3D maps) • MIL1553B, ARINC429 Data Bus Module • Microcontroller based I/O module for discrete I/Os, analog I/Os and serial interfaces RS422/485 , RS232 • Navigation processing and weapon computations • Embedded Virtual Training for training purpose
SPECIFICATIONS
PARAMETER SPECIFICATION Dimension 320 X 280 X 200 (mm) Weight 12.5 Kg DC Voltage 16 V DC to 31.5 V DC Power Consumption 180 Watts a) Processor: MPC7448 b) Graphics: E4960 c) Operating Frequency: 1.066 GHz (max) Technology Used d) Memory: SDRAM: 1 GB with ECC (minimum) Program FLASH:128 MB (minimum) NvSRAM:128 KB (minimum) NAND FLASH: 1GB (minimum) e) 08 Nos of 32-Bit General Purpose Timers f) OS Support: Greenhill’s INTEGRITY Features • Dual Redundant Architectur • Conduction Cooled Chassis with fan Analog Input /output 15 No’s / 13 No’s Stroke Output 02 No’s Discrete Inputs / output 74 No’s / 40 No’s ARINC-429 , MIL-STD-1553 06 Channel , 02 Channel RS-232/RS-422 10 Channel Video Input / output 2 No’s (1Composite and 1Y/C) / 6 Nos.
44 Display & Mission Computer for IADS - LCH Designed & Developed by MCSRDC
KEY FEATURES
Designed & developed by MCSRDC-HAL, DMC is • Generates 4 independent graphic output for display on MFDs. the main controller of indigenous Integrated • Overlays text/data on external videos Avionics Display Suite (IADS) for Light Combat • Inbuilt Digital Map generator providing 2D Maps such as Aeronautical Helicopter (LCH). It is an integrated multi-role Charts, Satellite Maps in different resolutions, Terrain Shaded Map, Sun real-time airborne central computer acquiring Angle Shading using DTED and GPWS features & 3D perspective view data from various onboard Avionics systems, maps. processing and providing necessary data/ • Navigation and guidance computation, Weapon Aiming Computations, command to the other onboard systems/ sub- Sensor Management & System Mode Management systems. • Data exchange via MIL1553B, ARINC429, ARINC717 data bus interfaces
S P E C I F I C AT I O N S
PARAMETERS SPECIFICATIONS Dimension 320 X 280 X 200 (mm) Weight 11Kgs DC Voltage 12VDC to 31.5VDC Power Consumption 180 Watts Technology Used a) Two Power PC based processor modules b) cPCI flexi-rigid hybrid backplane c) I/O module for discrete I/Os and serial interfaces d) 08 Nos of 32-Bit General Purpose Timers e) OS Support: Greenhill’s INTEGRITY f) Conduction Cooled Chassis Discrete Inputs / Output 127 No’s / 53 No’s ARINC-429 16 Channel ARINC-717 01 Channel MIL-STD-1553 02 Channel RS-232 / RS-422 07 Channel / 16 Channel Audio Output 01 No Video Input / Output 07 No’s Ethernet 05 No’s
45 Engine and Flight Display Unit (EFDU) Designed & Developed by MCSRDC
KEY FEATURES
The Engine and Flight display Unit (EFDU) is indigenously • Flight critical system replacing conventional engine, fuel, hydraulic & designed & developed by MCSRDC-HAL. It replaces existing standby flight instruments. conventional Stand-by Flight, Engine and Fuel instruments. • Two Signal processing modules • Integrated 4” X 5” AMLCD display • Processes data from Aircraft sensors and presented on the AMLCD as symbols/alpha numeric readouts • Generates display video for recording. • Data communication via ARINC-429 and MIL STD 1553 channel. • Human Machine Interface management through multi-function buttons, Knobs and brightness control switch.
SPECIFICATIONS
PARAMETERS SPECIFICATIONS Dimension 216 X 146 X 210 (mm) Weight 5.5 Kg DC Voltage 16 V DC to 31.5 V DC Power Consumption 45 Watts • Low Power ARM Cortex-M3 based FPGA Technology Used • Chrome-ART accelerator for Video Graphics Generation • LED based display • Conduction Cooled Chassis Analog Input 22 No’s Analog Output 03 No’s Discrete Inputs 20 No’s Discrete Output 03 No’s ARINC-429 01 Channel MIL-STD-1553 02 Channels RS-232 04 Channels Video Output Differential S Video (Y/C) o/p for recording of display video 46 LCA MK1A Mission Computer Designed & Developed by MCSRDC
KEY FEATURES
The LCA MK1A Mission Computer is the main controller for the • Latest Multicore processor and Hybrid VPX Backplane. upgraded avionics of LCA MK1A for which the hardware is • Capability of handling Analog and Digital (ARINC-818) video switching. indigenously designed & developed by MCSRDC-HAL. • Stroke symbol generation for Head-up display • Temperature Monitoring feature for all Modules. • Provision for Thermal Shut-down • Operational Hour Logging feature • Future Upgradability: 2 Spare VPX Slots, Ethernet, CAN Bus, ARINC 429/ 717.
SPECIFICATIONS
PARAMETERS SPECIFICATIONS Dimension ½ ATR Supporting 3 U Modules Weight < 11 Kg DC Voltage 16 V DC to 31.5 V DC Power Consumption < 120 Watts a Latest Multicore processor (NXP QorIQ T1042) Technology Used and Hybrid VPX Backplane b) OS Support: Vx-Works 7 c) Forced air cooling at 0.3Kg/min with inlet temperature of 10°C MIL-1553B 5 Channels Stroke Output 01 No Discrete Inputs / output 28 No’s / 34 No’s ARINC-818 Input/ Output 4 No’s / 8 No’s Analog Video Input/ Output 09 No’s (5 RGB, 4 Comp) / 09 No’s (7 RGB, 2 Comp) RS-232/RS-422 07/08 Channel Compliance MIL-STD-704D, 461E, 810F Connectors MIL-D38999 Connectors (Octonet Contact for ARINC-818 Video)
47 LCA MK1A SMFD Designed & Developed by MCSRDC
KEY FEATURES
The LCA MK1A Smart-Multifunctional Display (SMFD) is • Latest Multicore processor Based Design (NXP QorIQ T2080). indigenously designed & developed by MCSRDC-HAL for LCA • Ruggedized AMLCD 5” X 5” Display head with resolution of 600 X 600 MK1A upgrade. RGB pixels or better • Capability to accept Analog (RGsB) and Digital (ARINC-818) video inputs. • Display of internally generated graphic symbology information overlaid on external input video. • Option Selection Switches (Bezel Keys) for selection of various display parameters and pages • Provision for Thermal Shut-down SPECIFICATIONS
PARAMETERS SPECIFICATIONS Dimension 160 (W) X 190 (H) X 283 (D) Supporting 3 U size Backend electronics Modules. Weight 6.5 Kg DC Voltage 16 V DC to 31.5 V DC Power Consumption <100 Watts a) Latest Multicore processor Based Design (NXP QorIQ T2080) with Technology Used AMD based graphic processor. d) OS Support: Vx-Works 7 e) Conduction cooled MIL-1553B 01 No Ethernet 03 No Discrete Inputs / output 10 No’s / 02 No’s Digital Video(ARINC-818) Input 02 No’s Analog Video(RGsB) Input/ Output 02 No’s / 01 No. RS-422/RS-232 04/01 No. Compliance MIL-STD-704D, 461E, 810F Connectors MIL-D38999 Connectors (Octonet Contact for ARINC-818 Video)
48 LCA MK1A Digital Map Generator Designed & Developed by MCSRDC
KEY FEATURES
• Latest Multicore processor Based Design with NXP QorIQ T2081 and Extensive Graphics Processing with AMD E8860 The Digital Map Generator (DMG) is indigenously designed & developed by MCSRDC-HAL for LCA MK1A program. It aids the • Capability of Generating Analog (RGV) video for display on SMFD. pilot in aircraft navigation, flight planning & tactical operations • Video Capture and Overlay Provision. by rendering 2D & 3D maps and drawing overlays over the map. • Generation of 2D Maps with Aeronautical Charts and Satellite Maps in different resolutions (1:50K,1:100K,1:250K,1:500K,1:1M,1:2M, 1:5M and 1:10M) • Generation of Terrain Shaded Map, Sun Angle Shading using DTED and Enhanced GPWS features. • Enhanced situation awareness with 3D perspective view maps & Vector maps . • Overlay of Mission Data, Tactical Data, threat Inter-visibility Plots, etc. • Supply of two independent channels for 2D and 3D map display. • Provision of generation of ARINC-818 Digital Video SPECIFICATIONS
PARAMETERS SPECIFICATIONS Dimension < ½ ATR , Supporting 6 U Modules Weight < 7 Kg Operating Voltage 16 V DC to 31.5 V DC (Adaptability to operate on 115V AC,400Hz,3-phase aircraft supply) Power Consumption < 80 Watts a) Processor: NXP QorIQ T2081 b) Graphics Processor: AMD E8860 Technology Used c) Mass Memory : 64GB d) OS Support: Vx Works 7 e) Graphics Library: Open GL f) Various Map Formats with storage optimization schemes and faster rendering. MIL-1553B 01 No. Analog Video(RGsB) Output 04 No’s Discrete Inputs / output 03 No’s / 01 No. RS-232(Debug Port) 01 No. Ethernet (Program/ Data base 02 No’s loading and debug) Compliance MIL-STD-704D, 461E, 810F Cooling Forced air cooling at 0.2Kg/min with inlet air temperature of 10°C Connectors MIL-D38999 Connectors
49
AIRCRAFT UTILITY SYSTEM
51 DIGITAL LOX INDICATOR/ TRANSMITTER Designed & Developed by ASERDC, Lucknow
DIGITAL LOX INDICATOR/ TRANSMITTER KEY FEATURES
Digital Liquid Oxygen Indicator/ Transmitter is Avionics Instrument • Capacitance Measurement through AC Source designed as per MIL-G-19327B to measure the available quantity of of fixed strength & frequency liquid oxygen in the LOX Converter to ground crew and in addition it • Configurable to be used with 10 Ltr & 15 Ltr LOX Converter transmits variable frequency square wave for indication of Liquid Oxygen content to pilot in cockpit on Multifunctional Display. • Health Monitoring through PBIT & CBIT • Fault Logging for easy maintenance LOX Converter designed to provide variable capacitance output atits • In-System Programming measuring terminals. Capacitance value is proportional to available quantity of Liquid oxygen. • Use of latest technology i.e. Micro-controller based Instrument & dot matrix LED Display Digital Liquid Oxygen Indicator/ Transmitter measures the variable capacitance of LOX Converter using a unique “AC Excitation Technology”. In this capacitance of LOX Converter is measured by applying AC signal (of fixed amplitude and frequency) at one end of capacitor and current flowing through the capacitor is measured at other end. The change in current is directly proportional to change in capacitance.
TECHNICAL SPECIFICATIONS
Dimensions 68.0 X 68.0 X172.0 mm Accuracy ± 56 Hz Weight 650 gm (Max) (LOX Transmitter) QUALIFICATION AND COMPLIANCE Operating Voltage Range16 to 31.5VDC EMI/EMC MIL-STD-461C & MIL-STD-461E Nominal Input Current 300mA Max at 28 VDC I/P Power Environmental MIL-STD-810F, MIL-STD-810G & Protection Required Reverse Polarity JSS-55555 LOX Indication 0.0 to 6.0 Ltr with least count Power Supply MIL-STD-704D of 0.1Ltr on 2 Digit LED display Software compliance RTCA-DO-178C, Criticality Accuracy (LOX Indicator)± 0.4 Ltrs Level-B PLATFORMS Fixed wing
52 ENVIRONMENTAL CONTROL SYSTEM Designed & Developed by ASERDC, Lucknow
ENVIRONMENTAL CONTROL SYSTEM (ECS) KEY FEATURES
Environmental Control System (ECS) maintains a comfortable environment in • Air cycle based ECS system cabin by controlling the temperature, pressure and humidity of the cabin air within • Temperature Modulation an acceptable limit. The comfortable environment in cabin shall be maintained in • Over pressure and over all external environmental conditions like low temperature, low pressure and low temperature safety humidity condition at flight altitude as well as high temperature and high humidity conditions encountered at low altitudes. Temperature modulation is available on pilot control panel to regulate the Hot/Cold temperature requirement in the cockpit as per comfort of pilot and crew members. Environmental Control System in general comprises of: a) Bleed Air Management LRUs: Shut Off Valve, Non-Return Valve, Pressure Reducing & Shut Off Valve, Heat Exchangers b) Environmental Control Unit (Cooling Pack): Cold Air Unit , Heat Exchanger , Relief Valves ,Temperature Control Valve, Temperature Controller and Sensor. c) Safety Devices: Over Pressure and Over Temperature safety Switches d) Auxiliary System LRUs: Avionics Flow Control Valve, Shut off Valve for Fuel Tank Pressurisation, Seal Inflation and Deflation Valve, Cabin Pressure control System Valves. TECHNICAL SPECIFICATIONS
Cooling /Heating Load 20 KW Flow Rate Bleed Air 35 Kg/min Bleed Air Temperature 250- 600 deg C Pressure bleed air inlet 25 bar Temperature Cockpit 10 - 30 deg C QUALIFICATION & COMPLIANCE Design regulation MIL-E-38453A, SAE ARP 1796 SAE ARP 292, MIL-E-18927E(AS) Design & Qualification SAE ARP 986C, MIL-STD-810 MIL-STD-461, MIL-STD-704 PLATFORMS Fixed & Rotary wing
53 FUEL CONTENT GAUGING PROBE Designed & Developed by ASERDC, Lucknow
FUEL CONTENT GAUGING PROBE KEY FEATURES
Fuel Content Gauging Probe designed for following three functions: • Both Active and Passive Probes Technology available 1. Gauging: Three Tube Capacitance based fuel gauging which provides Square Technology available for use in Fuel Wave output having Time Period variation from 100 micro second to 200 micro immersed application also second approx. linearly with respect to fuel height from empty to full. The • Height Vs Time Period Relationship can be capacitance measurement is accomplished using DC/AC Excitation Technique customized and further conversion into frequency/ Time Period. Robust design of Three • Logic "High Level" warning Indication Tubes Fuel Content Gauging Probe makes it immune to EMI/ EMC noise and conforming to MIL-STD-461E. 2. Temperature Compensation: Probe output is compensated against real time Dielectric Constant variation due to temperature variation of fuel using appropriate sensors and algorithm. 3. Level Warning Indication: Capacitance based independent Level Warning and it is built independently without any connection to Gauging circuitry. The output of level warning (High/ Low Level) indication is used for external warning indication
TECHNICAL SPECIFICATIONS
Dimensions Flange Dia: 85 mm Length: 150-1100mm Weight 650 gms to 1250 gms Input Power Supply 28 VDC Accuracy ± 1% at Room Temperature (23 ±20C) ± 2% from -400C to +710C Length: 150-1100mm Output Variable Frequency/Time Period integral trimmer Operating Temperature -400C to +710C Storage Temperature -540C to +850C Fuel used ATF Jet A1 QUALIFICATION & COMPLIANCE MIL-STD-810G, RTCA-DO-160D & MILSTD-461E PLATFORMS Fixed & Rotary wing
54 HYDRAULIC POWER PACK Designed & Developed by ASERDC, Lucknow
HYDRAULIC POWER PACK (HPP) KEY FEATURES
• Integrated hydraulic power pack with The hydraulic power pack is source of hydraulic power for following services in the variable delivery axial piston pump having aircraft: constant power characteristic and built in (i) Landing gear extension & retraction. mixed impeller at inlet (ii) Wheel Brakes. • Self cooled 3.4 kW/ 28V DC motor with inbuilt RFI filter as drive to hydraulic (iii) Nose Wheel Steering. pump. The complete hydraulic power pack is housed in main landing gear fairing. The • Provision for providing oil level indicator Hydraulic power pack is divided into following two parts: and filter clog indicator with electrical (i) Hydraulic Supply Unit output (ii) Pump-Motor Unit • Built in High Pressure Relief Valve Pump–Motor unit consists of a variable delivery hydraulic pump driven by a DC electric motor.
TECHNICAL SPECIFICATIONS
Overall Size 585×250×360 mm Rated Input Voltage 28 VDC Weight 16 kg (Max) Total life 12000 Hrs System Fluid MIL-H-5606E Port Connection Details Pressure Port: As per 33656 System pressure High: 207+3.5 bar, Low: 2 bar Return port: As per 33656-4 Maximum Flow 10.75+/-0.75 lpm at 110 bar QUALIFICATION AND COMPLIANCE 5.75+/-0.75 lpm at 195 bar EMI/EMC MIL-STD-461C Reservoir Volume 3225+/-2% CC Environmental MIL-STD-810F Temperature Range Ambient: - 54°C to + 72°C Fluid: - 54°C to + 100°C PLATFORMS Fixed wing
55 HYDRAULIC ACTUATORS Designed & Developed by ASERDC, Lucknow
HYDRAULIC ACTUATORS KEY FEATURES
Actuators are available up to a hydraulic operating pressure of 4000 psi for • Double acting actuators with Internal following applications: Locking in Extension/Retraction ŸTo operate Air Brakes of an Aircraft. • Shuttle Valve for emergency pneumatic ŸTo open and close Doors of Main and Nose Landing Gear. operation of Door Jack ŸTo operate the Rudder Yaw Damper. • Inbuilt LVDT for Continuous Position Sensing. ŸFor Thrust Vector Control and Aerodynamic Control of Missile • Micro switch indication for extended ŸVarious similar other applications. position of the actuator. Advanced aerospace grade material with suitable heat treatment & surface • Inbuilt EHSV and Potentiometer for protection are selected so that the Actuator can operate between -54oC to actuator's Closed Loop Operation. 135oC. The Actuator can sustain the environmental requirements conforming to MIL-STD-810 and RTCA/DO-160. The working media for these actuators is mineral oil conforming to MIL-H-5606 or equivalent.
TECHNICAL SPECIFICATIONS
Stroke achieved Up to 300 mm Environmental MIL-STD-810, RTCA/DO-160 Load Up to 5000 kgf EMI/EMC JSS 55555, MIL-STD-461 System Pressure Up to 4000 psi PLATFORMS Fixed wing Proof Pressure Up to 6000 psi TBO/ TTL 1000 Hrs to 3000 Hrs QUALIFICATION & COMPLIANCE Design & Qualification MIL-A5503E, MIL-H8775, FAR25, MIL-G5514, ARP 490 & ARP 1383
56 HYDRAULIC PUMP Designed & Developed by ASERDC, Lucknow
HYDRAULIC PUMP KEY FEATURES
• Variable delivery pump with pressure Hydraulic Pump is used as power source in fixed wing, rotary wing and space compensator. launch vehicle. • Special roller & ball bearings conforming to The hydraulic pump is a pressure compensated variable delivery axial piston aerospace grade ABEC 5 – ISO 5. swash plate type hydrostatic pump. The pump has single or dual stroking piston • Nitrile O rings with temperature range -54 to to achieve single or two stage flow vs pressure characteristic as per platform 135oC. requirements. In case of unpressurized reservoir, a mixed flow impeller to • Mounting interface and port size & location as increase the pressure at inlet can be incorporated. The pumps are pressure per Customer specification. compensated i.e a mechanical servo system consisting of spool sleeve, springs, • Direction of rotation as per Customer stroking & spring loaded rate piston and cradle senses the line pressure and Specification. adjusts the pump outlet flow from full to zero flow as per flow vs pressure • Proven for limited dry running and high oil characteristic. These pumps are self lubricated. contamination condition. Advanced aerospace grade material with suitable heat treatment & surface protection are selected so that the pump can operate between -54 deg C to 135 deg C. The pumps can sustain the environmental requirements conforming to MIL 810. The working media for these pumps is mineral oil conforming to MIL-H-5606 or equivalent.
TECHNICAL SPECIFICATIONS
Weight 3.2 Kg (Max) Temperature Range +8oC to +70oC (ambient) Rated Delivery Upto 25 lpm Inlet oil temperature 110oC (max) Displacement 1.4 to 4.1 cc /rev QUALIFICATION & COMPLIANCE Rated Full Flow Pressure 203 bar Hydraulic Pump SAE AS19692 for 207 bar (3000 Max. Discharge Pressure 210 bar (At zero flow) psi) Type II Rated Speed 4000 - 7500 rpm Hydraulic Fluid MIL-H-5606 Rated Inlet Pressure 1 - 6 bar (g) Case Drain Leakage <1.3 lpm PLATFORMS Fixed wing, Rotary wing, Space Rated Endurance 1000 to 2500 Hr Vehicle & Missile
57 WHEELS & BRAKES Designed & Developed by ASERDC, Lucknow
WHEELS & BRAKES KEY FEATURES
Wheels & Brakes used for taxiing, take-off, landing, stopping and parking of • Metallo-ceramic and Carbon-Carbon type aircraft/helicopter. Brakes using both Metallo-ceramic type and Caron-Carbon Brake technology available. brake pads are available. High metallurgical quality close die forgings followed by • Dynamic Landing Loads: Upto 40 Tons. shot peening are used for reliable product. Capability exists for design and • Kinetic Energy/ Brake: Up to 45 MJ certification to requirements of MIL-W-5013, TSO-C-62d/TSO-C-135. Wheel Strength Test Facility, Wheel Fatigue Roll Test Facility and Brake Test dynamometer facility available.
TECHNICAL SPECIFICATIONS
WHEELS Normal Operating Pressure 55 bar Tyre Size 5" to 20" Max Brake Operating Pressure 220 bar Dynamic Landing Loads Upto 40 Tons Proof Pressure 330 bar Tyre Pressure 360 psi Brake Application Speed 297 Kmph Maximum Static Load 16 Tons Overhaul Life 1000 landings Nominal Loaded Radius 460 mm Total Life 3000 landings Over Pressure 1050 psi QUALIFICATION & COMPLIANCE BRAKE Design & Qualification MIL-W-5013L Kinetic Energy/Brake Upto 45 MJ Environmental MIL-STD-810D Brake Operating Fluid MIL-H-5606E/ DTD-585 PLATFORMS Fixed & Rotary wing
58 Brake control Hydraulic Engine and Electrical Monitoring system – Electronic Unit (BHEEM-EU) Designed & Developed by SLRDC
KEY FEATURES
BHEEM-EU is designed to provide Control of • Real Time Operating System (RTOS) based Embedded control system. Brakes and Nose Wheel steering of LCA Tejas. It • Power Architecture based processor (PPC750) also monitor the health of the aircraft Hydraulics, • Complete Dual Redundant system Undercarriage, Engine and Electrical power • Complies to Mil Standards (461C, 810D & 704D) generation and distribution system of the aircraft. • Software compliance to DO-178 Level-B The same unit is compatible for LCA Airforce, • Interface with 300 Input and Output signals A i r fo rce - t ra i n e r , N a va l , N a va l - Tra i n e r • Extensive Power on Built in test(PBIT), Continuous Built in check(CBIT) configurations with GE F404 IN20 & GE F404 F2J3 • Engine Vibration signal processing engines. • Metal Core & Flex PCB technology • Communicates with mission computer over aircraft Main Mil-1553 bus as ART • ½ ATR size with Mounting tray for easy mounting.
S P E C I F I C AT I O N S
PARAMETERS SPECIFICATIONS Physical • Dimensions (L X W X H) : 318 X 124 X194 ( mm) • Weight: 8Kg (max) • ARINC300 connectors for interface Electrical • Power supply: 28V DC • Power consumption: 75 Watt • BIT (Built in Test). Interfaces • 300 Inputs and Outputs • Mil-1553 bus – Main Bus • In-situ Programming facility. Standards Compliance. • MIL-STD-810D for Environmental tests. • MIL-STD-461C for EMI/EMC tests. • MIL-STD-704D for Power supply conditions • DO-178, Level-B PLATFORMS • LCA TEJAS
59 Starter Electronic Control Unit (SECU) Designed & Developed by SLRDC
KEY FEATURES
The main function of the Starter Electronic Unit • ARM processor based controller (SECU) is to start the Gas Turbine Starter • Redundancy in functionality incorporated Unit(GTSU-110/127), accelerate and control the • System uses SPARTAN 6 FPGA and Controller for DIO processing with engine by controlling the fuel flow with the help of adequate resources for future growth. stepper motor. After attaining the desired speed, • BIT facility GTSU in turn starts the Main Engine of the LCA • Conduction cooled and hard mount system. Aircraft.
S P E C I F I C AT I O N S
PARAMETERS SPECIFICATIONS Physical • Dimensions (L X W X H) : 184 X 140 X87.5 ( mm) • Weight: 1.5Kg (max) • Mil D38999 connectors for interface Electrical • Power supply: 28V DC • Power consumption: 35 Watt • BIT (Built in Test). Interfaces • RS 422 bus - for communication • In-situ Programming facility. Standards Compliance. • MIL-STD-1760 CLASS II. • MIL-STD-810G for Environmental tests. • MIL-STD-461E for EMI/EMC tests. • MIL-STD-704F for Power supply conditions • DO-178, Level-B PLATFORMS • LCA
60 Turbine Generator Engine Control Unit (TGECU) Designed & Developed by SLRDC
KEY FEATURES
The main function of the Turbine Generator Engine • ARM processor based controller Control Unit (TGECU) is to start the Gas Turbine • Redundancy in functionality incorporated Electrical Generator(GTEG-60), accelerate and • System uses SPARTAN 6 FPGA and Controller for DIO processing with control the engine by controlling the fuel flow with adequate resources for future growth. the help of stepper motor. Once started the GTEG- • BIT facility 60 in turn starts the Main Engine ( AI-20D) of the • Conduction cooled and hard mount system. AN-32 Aircraft.
S P E C I F I C AT I O N S
PARAMETERS SPECIFICATIONS Physical • Dimensions (L X W X H) : 184 X 140 X87.5 ( mm) • Weight: 1.5Kg (max) • Mil D38999 connectors for interface Electrical • Power supply: 28V DC • Power consumption: 35 Watt • BIT (Built in Test). Interfaces • USB port • In-situ Programming facility. Standards Compliance. • MIL-STD-810G for Environmental tests. • MIL-STD-461E for EMI/EMC tests. • MIL-STD-704F for Power supply conditions • IEEE 12207 PLATFORMS • AN-32
61 CENTRALIZED WARNING SYSTEM (CWS) Designed & Developed by SLRDC
KEY FEATURES
Centralized Warning System, CWS is used to detect • 30 legends to display Red & Amber Warnings. the warning conditions on various Aircraft systems • Generates audio tones for Red & Amber Warnings and alerts the pilot using Visual, Audio & Voice • Generates voice warnings for AOA Exceedance, Low altitude, Canopy unlock warnings. The CWS system comprises two Display & Under carriage extension. Units and one Electronic Unit. The Display Unit • Test facility to check the health of display unit lamps & external cockpit consists of 30 warning indicators for providing RED lamps. and AMBER warnings. During day time, the • Operates in Day-Night conditions. intensity of lamps is fixed and during night time, • Interfaces with fire warning lamp & generates unmutable red tone. t h e b r i g h t n e s s c a n b e a d j u s t e d u s i n g • Interfaces with master alarm lamp (flasher). potentiometer. The Electronic Unit is used for • Capable to receive ARINC/Discrete signals from FADEC Engine warning control of Display Unit, Flasher and other lamps in Interface for health monitoring. the cockpit and also used to generate the audio & • Audio tone interface to Audio Management unit (AMU). voice warnings.
S P E C I F I C AT I O N S
PARAMETERS SPECIFICATIONS Physical • Dimensions (L X W X H) : 250 X 195 X 85 (mm) for EU : 94 X 84 X 152 (mm) for DU • Weight : 3.5Kg (max) for EU : 0.8Kg (max) for DU • Mil D38999 connectors for interface Electrical • Power supply: 28V DC • Power consumption: ≤ 6 A (with external lamp load) ≤ 1 A (under normal conditions) • Test facility for Lamp check. Interfaces • 30 Discrete signals • ARINC-429 Standards Compliance. • MIL-STD-411C for Aircrew station alerting system • MIL-STD-810D for Environmental tests. • MIL-STD-461B for EMI/EMC tests. • MIL-STD-704D for Power supply conditions PLATFORMS • HJT-36 and HTT-40
62 ARINC TO SYNCHRO UNIT (ATS) Designed & Developed by SLRDC
ARINC TO SYNCHRO UNIT (ATS) KEY FEATURES
In legacy aircraft, many display units are analog which can • Dual Channel Synchro : 11.8Vac, 400 Hz with only receive synchro signals inputs whereas New output current up to 150 generation systems provide the input to displays on ARINC mA. Bearing Range: 0 to 429 or MIL 1553B Bus. ATS unit is an interface between bus 359 ° with ± 3°Accuracy based new systems and legacy synchro based analog displays. • ARINC-429 Bus Interface : 4 Receiver & 2 The ARINC to Synchro (ATS) Unit is a digital to synchro Transmitter converter system that receives angular data (Heading and • Discrete Input / Output : 28V/OPEN or 28V Bearing) on two ARINC-429 inputs and converts it into two signal RET/OPEN Condition. independent ARINC-407 analog synchro output (3-wire) to • Optional Interface : RS-232 Interface, Two interface with on the board Radio Magnetic Indicator (RMI) phase Resolver output, of helicopter.ATS unit has following main functions: Current driven Localizer i) It converts the ARINC-429 data received from two & Glide Slope(GS) ARINC sources into two independent Synchro outputs in deviation signal channel-1 & in channel-2. • Synchro output is configurable for VOR Bearing, ii) Interfaces with the discrete switch to select the Heading, Pitch and Roll. processing of ARINC Channel 1 or Channel 2 inputs or both. iii) Indicates the health status of ARINC 429 input source. • Provision for Insitu Programming. • Extensive BITE facility for checking the unit serviceability
TECHNICAL SPECIFICATIONS
Parameter Specifications Synchro Signal Output 11.8V L-L with current Dimensions 167Lx147Wx78Hmm Load of 150 mA Weight Less than 2Kg Discrete Input/ 28V/OPEN or ELECTRICAL SPECS Output 28V RET/OPEN Power Supply 28V DC as per MIL-STD- Cooling Conduction 704D Self rest POST, IBIT & CBIT. Power Consumption 30W (Max) QUALIFICATION & COMPLIANCE AC Reference Power Supply 26V AC, 400 Hz EMI/EMC MIL-STD-461 E Signal Environmental MIL-STD-810G INTERFACE ARINC-429 Reliability MIL-STD-217F SYSTEM PARAMETERS Software compliance DO-178 B compliant Transmitter 2-Channel PLATFORMS Chetak/Cheetah Helicopter Receiver 4-Channel Legacy Fixed & Rotary Synchro Outpur Channel 2 Independent Channels Wing Aircraft
63 SOILD STATE WEAPON CONTROL SYSTEM (SSWCS) Designed & Developed by SLRDC
KEY FEATURES
Solid State Weapon Control System (SSWCS) is • Controls 12 hard points designed for the management of weapon stores on • Controls classical weapons and smart weapons complies to Mil-1760. JAGUAR A/c. It shall replace the existing • System identifies 100 types of weapons using push wheel switches. Armament Main Unit(AMU) which was designed to • Redundancy for emergency jettison function. manage the classical weapons like Bombs, Rocket • Switches audio signals from the weapon stations to Communication Pods and Fuel-tanks in normal mode and Control System. emergency mode. The SSWCS also manages • Communicates with mission computer over aircraft Main Bus and smart weapons with Mil-Std-1760 Class II Communicates with smart weapons over the new Armament Bus - interface. Mil 1553 bus as a bus controller. • Built around SBC based control system with adequate resources for future growth. • System uses SPARTN 6 FPGA with inbuilt RAM for DIO processing with adequate resources for future growth. • cPCI based hydride backplane. • Dual processing channels. • Extensive BIT facility for fault analysis • Conduction cooled and hard mount system.
S P E C I F I C AT I O N S
PARAMETERS SPECIFICATIONS Physical • Dimensions (L X W X H) : 450 X 350 X155 ( mm) • Weight: 14.5Kg (max) • Mil D38999 connectors for interface Electrical • Power supply: 28V DC • Power consumption: 54 Watt • BIT (Built in Test). Interfaces • 164 Discrete inputs and 167 discrete outputs • Mil-1553 bus – Main Bus and Armament Bus • ETHERNET (2 Channels) and RS422 (2 Channels) • In-situ Programming facility. Standards Compliance • MIL-STD-1760 CLASS II. • MIL-STD-810G for Environmental tests. • MIL-STD-461E for EMI/EMC tests. • MIL-STD-704F for Power supply conditions • DO-254, Level-B PLATFORMS • Jaguar
64 AIR DATA UNIT AND OUTSIDE AIR TEMPERATURE PROBE Designed & Developed by SLRDC
AIR DATA UNIT AND OUTSIDE KEY FEATURES AIR TEMPERATURE PROBE • Two ARINC 429 digital bus The ADU (Air Data Unit) measures the static and dynamic • RS422/RS485 digital bus for Debugging. pressures using two MEMS based pressure sensors. Computes • 4 Discrete Inputs (Open/Ground) air data parameters: IAS, baro altitude and vertical speed. The • 3 Discrete Output (Open/Ground) ADU uses the OAT (Outside Air Temperature) probe to measure • Power consumption : < 6W the outside air temperature and computes the True Air Speed • Power Supply: 28 V & Micro power cut for 50msec. (TAS) based on the IAS and OAT. The ADU provides a low air speed • Operating temperature range : - 40°C to + 71°C discrete output at a predetermined airspeed for use in the landing • MTBF 5000 hrs gear control system / Voice Warning System (VWS). • Orientation insensitive The ADU has provision for selecting preprogrammed SEC laws by • As per TSO C106 /AS8002 pin programming to enable correction of air data parameters • Software standard: IEEE-12207. based on helicopter configuration. The air data unit • Environment : MIL-STD-810G. communicates these parameters to other Helicopter systems • EMI/EMC Specification : MIL-STD-461E. (like AHRS, IADS, AFCS, HPS and EW etc.) on ARINC 429 digital • Lightning Protection : DO-160D, level 3 with data bus. waveform 2 & 3 The OAT Probe is an aero dynamic Structure with a Temperature • Outside Air Temperature (OAT) probe is an Aero Dynamic Structure sensor mounted in it. It measures the Outside air temperature from -100°C to +300°C with an accuracy of 1.2°C.
ADU2650A TECHNICAL SPECIFICATIONS OAT PROBE (N165630) TECHNICAL SPECIFICATIONS
Dimensions 131 mm x 151mm X 51 mm Dimensions Ø65 x 97 mm x 108 mm (w x l x h) Weight 0.2 kg Weight 0.8 kg Static Pressure (Ps) 240 to 1100 mb Resistance Range 75 ohms to 130 ohms Differential Pressure (Qc) - 10 to 100 mb Configuration 100 Altitude Rate ±6000 ft/min Excitation Current 1mA Mach Number 0 to 0.7 Altitude -1500 to 30000 Feet Altitude 30,000 Feet, Alt rate : Calibrated Air Speed (CAS) 20 to 230 Knots 6000ft/min (max) True Air Speed (TAS) 40 to 240 Knots Operating Temp. Range -450C to +710C Total Air Temperature (TAT) -55 0C to + 75 0C Environmental Specification As per MIL-STD-810G Static Air Temperature (SAT) -55 0C to + 75 0C PLATFORMS ALH, LCH & LUH PLATFORMS ALH, LCH & LUH
65
AIRCRAFT ELECTRICAL SYSTEM
67 TRANSFORMER RECTIFIER UNIT (TRU) Designed & Developed by ASERDC, Lucknow
TRANSFORMER RECTIFIER UNIT KEY FEATURES
Transformer Rectifier Unit (TRU) is the DC Power Source in Electrical Power • Step/Linear Output voltage Regulation. Generation Systems (EPGS) of Aircraft. It receives input power from 3Ø, 200VLL, • 12/18 pulse rectification. 400Hz AC Bus and provides step or linearly regulated 28V DC, 250 Amps power to • Fan Cooled DC power Bus. • High Temperature Indication 12 pulse step and 18 pulse linear rectification technology is available which provides low ripple DC output for airborne applications.
TECHNICAL SPECIFICATIONS
Dimension 220 X 182 X 180 mm (L x W x H) Output Ripple < 3 V Peak to Peak Weight 12.8 Kg (Max) Efficiency > 88% at full load INPUT: Over Load Capacity 150% (375 amps) for 2 minutes Input Power 115 VAC , 3Ø , 400 Hz 200% (500 amps) for 1 Min OUTPUT: 400% (1000 amps) for 1 Second Voltage 28 V ± 0.5V DC Operating Temperature -40 ° C to + 65 ° C Current 250 A (Max) QUALIFICATION & COMPLIANCE Output Power 7.5 KW EMI/EMC MIL-STD-461C Output Ripple < 3 V Peak to Peak Power Supply MIL-STD-704G Efficiency > 88% at full load Environmental MIL-STD-810G THD < 5% at 250 A output PLATFORMS Fixed & Rotary wing
68 AC POWER MANAGEMENT & DISTRIBUTION SYSTEM Designed & Developed by ASERDC, Lucknow
AC POWER MANAGEMENT KEY FEATURES & DISTRIBUTION SYSTEM • Over load protection AC Power Management & Distribution System • Protection on requirement (For Ex. GPU O/ V and U/V, GPU receives input power from power generating sources (Alternator, Inverters etc.) and provides output power Phase Sequence, GPU O/F and U/F etc.) on various Buses (Main Bus, Essential, Non Essential • In-built protection for GPU Over and under voltage, GPU Emergency etc.) as per user functional logic Phase Sequence, GPU Over Frequency and Under requirements of platform. This system complies MIL- Frequency etc,as per platform requirement STD-704 for AC power systems • Self air cooled by natural convection • Grounding & Bonding points
TECHNICAL SPECIFICATIONS
Dimensions 400mm x 250mm x 170 mm(H) Switching power devices Electro-Mechanical Power Weight 12 Kg Approx. Contactor or Power SSPC Voltage 200 VL-L / 115 VL-N Communication Bus RS 422 / RS485 Power Capacity 40 KVA Max QUALIFICATION AND COMPLIANCE Current Capacity 120 Amps Max EMI/EMC MIL-STD-461E Over Load Capacity 150 % for 2 min, 200% for Environmental MIL-STD-810G 5 sec Power Supply MIL-STD-704G Output Load Distribution Short circuit protection PLATFORMS Fixed and Rotary wing Point (Thermal Circuit Breakers or SSPC)
69 ALTERNATOR CONTROL & PROTECTION UNIT Designed & Developed by ASERDC, Lucknow
ALTERNATOR CONTROL KEY FEATURES & PROTECTION UNIT • Regulation of Alternator output voltage through PWM Alternator Control and Protection Unit regulates the technique Alternator output voltage within specified limits under • Alternator Voltage Adjustment range 108 - 118 Vrms various loads and speed conditions. The unit is having built-in protections against over/under voltage, • In-built protections for Alternator i.e. Over and Under voltage, over/under frequency, over current and feeder fault Over and Under Frequency, Over Current and Feeder Fault conditions during which it disconnects the alternator • Remote Reset facility from AC electrical system by de-energising the line • Self cooled contactor and field by operating the protection relay • Grounding & Bonding points inside the unit. This unit is interfaced with 5KVA / 10KVA Alternator.
TECHNICAL SPECIFICATIONS
Dimensions 190 X 128 X 110 mm Under voltage Protection 100 to 94 Vrms (Phase to Weight 1.6 Kg Neutral) Nominal Input Voltage 3-Ph, 115V Phase to Neutral Operating Temperature -45 °C to +71 °C Output at 400Hz Alternator voltage Range control through Pulse Width QUALIFICATION AND COMPLIANCE: Modulated Waveform 28V DC EMI/EMC MIL-STD-461E to coil of Line Contactor Environmental MIL-STD-810F Alternator Voltage 108 Vrms to 118 Vrms with the adjustment range help of integral trimmer Power Supply MIL-STD-704D Field current handling Capacity 3.5 Adc (Max) PLATFORMS Rotary Wing Continuous 5.0 Adc (Max) for 5 Sec Field current 3.5 Adc (Max)
Over voltage Protection 125 to 130 Vrms (Phase to Neutral)
70 DC POWER MANAGEMENT & DISTRIBUTION SYSTEM Designed & Developed by ASERDC, Lucknow
DC POWER MANAGEMENT & DISTRIBUTION KEY FEATURES SYSTEM • Over load protection DC Power Management & Distribution system receives input • In-built protection for GPU Over-voltage, power from power generating sources (Starter Generator, Battery, TRU etc.) and provides output power on various Buses (Main Bus, GPU & Battery Reverse Polarity, Battery Essential, Non Essential Emergency etc.) as per functional logic Discharge Indication etc., as per requirement of platform. This system complies MIL-STD-704 for platform requirement DC power systems. • Self air cooled by natural convection
• Grounding & Bonding points
TECHNICAL SPECIFICATIONS
Dimensions 415mm x 250mm x 150 mm(H) Switching power devices Electro-Mechanical Power Weight 11 Kg Approx. Contactor or Power SSPC Voltage 28 VDC (As per MIL-STD-704) Communication Bus RS 422 / RS485 Power Capacity 12 KW Max QUALIFICATION AND COMPLIANCE Current Capacity 400 Amps Max EMI/EMC MIL-STD-461C 200% for 5 sec Environmental MIL-STD-810G Output Load Short circuit protection (Thermal Power Supply MIL-STD-704G Distribution Point Circuit Breakers or SSPC) PLA TF ORMS Fixed and Rotary wing
71
R&D CENTRE CAPABILITIES & TEST FACILITIES
73 AEROSPACE SYSTEMS AND EQUIPMENT RESEARCH & DESIGN CENTRE (ASERDC) -KORWA
Established on: 1986 DSIR Recognition as 11th R&D Centre of Design Complex-HAL CEMILAC APPROVED
SSCDR for LCA Mk-I I-DMG SSFDR for AN-32 SSFDR for HTT-40/ALH Deployable FDR / MiG27/IJT/DO228 Key Technology Areas
Recorder Systems: Cockpit Displays: Interface Systems: • Flight Data Recorder • Multifunction Displays • Interface Function Unit (IFU) • Cockpit Voice & Flight Data Recorder • Dedicated Small Displays • Interconnection Unit (ICU ) Rear • Deployable Flight Data Recorder i.e. PCU and GPCU • Interconnection Unit (ICU ) Front • Fly By Wire Data Acquisition Unit Mission Support Systems: • Digital Map Generator
PROJECTS COMPLETED
• DARIN Mini Integration Rig for Jaguar • CMFD (5x5 & 6x6) for Su-30MKI through JV M/s SHDS • Automated Harness Checkout System for LCA • Technology Demonstration of Deployable FDR • Accelerometer Electronics package for strategic • SSFDR for MiG-27 defense requirement • NAP Display Board of INS project • Inter Connection Unit for Jaguar trainer and strike • ADC & MUX Hybrid for FDR aircraft • Self-Test Magnet for Autostab • LF Amplifier for MIG-27 • Lower Cover for HUDWAC • Flight Data Recorder for LCA • Thermal Wafer for HUDWAC • FDR tester for LCA • EHT for COMED • SSCDR MK-II for LCA • Power Supply for IFU of COMED • SSFDR MK-I/II for JAGUAR DARIN-I/II/III • Screen for COMVU for Display Head of COMED • Test Equipment and Ground Replay Equipment for • DMG Mounting Tray SSFDR JAGUAR. • Crash Protected Memory Module (CPMM) • Test Equipment and Ground Replay Equipment for • SSFDR for AN-32 SSCDR MK-II for LCA • Interface Functional Unit for Jaguar DARIN-II & • SSFDR for IJT DARIN-III • SSFDR for Su-30MKI • Cockpit Voice & Flight Data Recorder for LUH • SSFDR for Do-228 • Cockpit Voice & Flight Data Recorder for LCH • Test Equipment & Ground Replay Equipment for SSFDR • Solid State Flight Data Recorder /Cockpit Voice Su-30MKI Recorder SSFDR/CVR) for Cheetah/Chetak/Cheetal • PMM with Memory Capacity of 64MB • SSCDR for HTT-40 • SSFDR for ALH(IADS)
74 STRENGTH FACILITIES
• Development of embedded system achieved Hardware Development Tools: leading to successful development of Flight • PCB Design Tool : PADS from Mentor Graphics, Data Recorders for various aircraft and CADSTAR helicopter platforms. • Mechanical design tool : SolidEdge, AutoCAD • Test equipment based on PXI/CPCI buses with • CPLD & FPGA development tool :ALTERA QUARTUS II, open system architecture. XILINX TOOL, ACTEL FPGA TOOL • Ground Replay equipment required for FDR data analysis. Software Development Tools: • Capability to retrieve the data from SSFDR • UML based design tool from Rational Rose after aircraft accident. /Rhapsody/DOORS • ClearCase : Configuration Management tool CAPABILITIES • Integrity RTOS IDE with MULTI IDE Integration Tool: • Embedded System Design and Development Compilers : • Hardware Design and Development • Diab for Motorola microcontroller MPC68XX series • Software Design & Development • Metrowerks Codewarrior for PowerPC • Test Equipment Design and development • Ground Replay Equipment System • DSP compiler for SHARC • Total solution for Avionics System • Keil for ARM • ADSP Solution • Visual C++ editor & compiler for Ground Equipment • Aircraft Signal Simulation In Circuit Emulators : • Analog DAQ Solution • Windriver probe with Vision Click IDE • Multilayer PCB Design • DSP compiler for SHARC • CPLD & FPGA Based Design Software Testing & IV&V tool • Avionics Interface Solutions • IBM Rational RT-RT tool • Device Drivers for Embedded System • LDRA Tool for Static and Dynamic testing as per • Mechanical Design DO178B • Navigation systems • Software Independent Verification and Test Equipment Test Facilities validation • National Instruments based PXI chassis, modules, • Design Liaison for production support and drivers & support certification • Graphical language : LabVIEW2017
ENVIRONMENTAL TEST FACILITY
Vibration Specification: Rate Table Specification : • 1500 KgF • 2 axis rate table with Hot • Sine, Sine on Random, Random, and Cold chamber Random on Random, Shock High Temperature Fire Test HOT & COLD Chamber Facility Specification : Specification : • High temperature test up to • -70ºC to +180ºC temp. 1100°C • Rate of change: heating 3.2º/min Penetration Test Facility • Cooling 2.8º/min Specification : • Useful Dimension (LXWXH) (mm): 230±3 kg drop facility from • 548 X 447 X 447 3m Heights Centrifuge machine Specification : • Max. linear acceleration: 40 ‘g’ • Max. speed: 300 RPM • Object weight: 40 kg (max)
75 STRATEGIC ELECTRONICS RESEARCH & DESIGN CENTRE (HYDERABAD)
ABOUT SLRDC Strategic Electronics Research & Design Centre (SLRDC) of HAL, co-located with Avionics Division at Hyderabad, is AS 9100D certified R & D centre for Avionics in India. It has more than 50 years of expertise in Design and Development, Qualification, Engineering support and Field Support of Communication, Radar, Mission Computers, Navigation, Identification Systems and Missile Electronics. With the sustained R & D efforts, over 70 types of Avionics Systems consisting of secure communication, Ground Radars, Traffic Control Radars, Airborne Radars, Flight Control systems, on Board Computers, Navigation, Hybrid Micro-electronics, Missile Electronics and Space Applications have been indigenously designed, developed and successfully produced till now. SLRDC has also Ventured in Civil Avionics systems and currently many avionics systems are undergoing Indian Technical Standing Order (ITSO) certification through Directorate of Civil Aviation (DGCA) , India .
Indigenous Design & Development of IFF began in TECHNOLOGICAL ADVANCEMENT 2016 2015 CIT 1970s with IFF Mk-X with the use of analog signal IDENTIFICATION OF FRIEND OR FOE (IFF) IFFI 34xx Series processing and RF tubes having conventional 2014 IFFT-MK-XII wired system. In 1980s, its features were Civil Mode S 24xx Series enhanced with the use of semiconductor devices Crypto 1990s Highly Modular IFFT-MK-XI and modular structure. In 1980s, with the 14xx Series advancement in technology, IIF Mk-XI was Military Mode-S 1980s developed using solid-state Tx/Rx devices, hybri d IFFT-MK-XA 40xA Series components and DSP. Latest product in the series, Modes 1,2,3, C IFF Mk-XII is based high speed DSPs and FPGAs Modular 1970s IFFT-MK-X with modular structure & Civil Mode S. Combined BAT Interrogator & Transponder (CIT) is delivered to Conventional Indian armed forces. Design and Development of Wired System YEAR OF DEVELOPMENT & TECHNOLOGY USED IFF Mode 5 with Crypto is under progress. RF Tube Version RF Tube / Semi Conductor Version Solid State Transmitter & Dual Channel Receiver Analog Signal Analog Signal Processing using Receiver devices High Speed DSP FPGA Processing Discrete components DSP Hybrids Secure Modes
Indigenous Design & Development of RAM started RADIO ALTIMETER (RAM) in 1982 with RAM-700 using analog signal 2011 processing and discrete components & 4 % 6.0 Km 28V DC 20 W RAM-2700 1% Accuracy 2.7 Kg accuracy. Next product in the line ,RAM - 1700 , 2007 developed in 2000 s , used hybrid components and RAM-1750 1.5 Km 28V DC 24 W super components resulting in reduced weight & 2% Accuracy 3.0 Kg 1997 better performance . RAM-1750 was next in line, RAM-1700 1.5 Km 28V DC 35 W enhanced by Digital Signal Processing , SMD 3% Accuracy 3.5 Kg 1982 components and CPLD devices for better accuracy RAM-700 and reduced weight . Latest Radio Altimeter RAM - 1.5 Km 115 AC 80 V 4% Accuracy 4.7 Kg. YEAR OF DEVELOPMENT & TECHNOLOGY USED 2700 is lightweight and has one of the best accuracy level of 1% available in the world making Discrete Compnents HYME Based devices SMD Components TX Power Control Analog Signal RF super compnents CPLD Devices Improved SNR it an ideal unit for light Airborne platforms. Processing Digital Signal Processing Improved DSP FPGA
COMMUNICATION RADIO Journey of Communication Systems began in1970 2018 SCDLU s with design & development of stand by VHF UHF 4 Kgs. 2016 SDR communication radios like COM 104A, Network Centric COM 105 A & COM 150 A. In 1980 s VUC201A, V/UHF Dynamic TDMA 2010 ACS 235 radio was developed using discrete components & Less Volume & analog signal processing. Later, INCOM 12XX Weight with 2000 30 - 88MHZ INCOM 12xx series was developed using DSP technology for Anti-Jam Secure mode of operatio .he latest FH DS 1982 Secure Mode VUC 201 COM Series Radio in UHF Range is COM 1150A. In 100-156 MHz 2010 ACS 235 , Advanced Communication System 225-400 MHz YEAR OF DEVELOPMENT & TECHNOLOGY USED was developed using high speed DSPs with ECCM Discrete Compnents Digital Signal SMDs / CPLDs SW Configurable features and modular architecture. Presently Analog Signal Processing DSP High Speed DSP & Software Defined Radio is developed in V /UHF and Processing DDS / VCO-PLL FPGA, GPP L Band with advance features for reconfigurable waveforms and Network Centric Operations . VHF civil Radio is the latest addition to this list.
76 TECHNOLOGY UNDER DEVELOPMENT Wideband RF front end receiver for communication and Radar Digital IF receiver Active T/R module array Masterless Dynamic TDMA Networking for L band E-scan antenna Light weight Avionics Power PC Based Embedded Hardware Encryption, Decryption Algorithms Video Processing Techniques ACCOLADES 125 Patents & 43 Copyrights and 3 Design registrations Filed Aeronautical Society of India Award for Indigenisation of Aeronautical Equipment in Year 2011 & 2017 Raksha Mantri Award for Excellence in Indigenisation for Year 2013-2014 Golden Peacock Award for Innovative product in Year 2017 SODET award technology innovation and technology development in Year 2016-17 ACCREDATIONS & CERTIFICATIONS
IS / ISO 9001
Bureau of Indian Standards QMS
AS 9100 Rev ‘D’ ISO 14001 : 2004 DGAQA CEMILAC ISO 9001
ENVIRONMENTAL TEST FACILITY
Vibration Thermal Shock Combined Altitude Thermal Humidity Test (CATH) Thermal chambers Highly Accelerated Life test (HALT) & Highly Accelerated Stress Screen (HASS) EMI/EMC Acceleration Facility
PLATFORMS WITH SLRDC AVIONICS SYSTEMS Fighter A/C Transport A/C Trainer A/c Helicopter Surviellance Ships LCA AN-32 IJT ALH P8I IN & Jaguar DARIN II, III AVRO HAWK AJT Cheetah Dornier CG Ships SU-30 MKI Dornier HTT 40 Chetak MIG-27 LCH MIG-29 (Naval) K/KU/UPG LUH MIG-23 MI 17 BISON Cheetal KM 31 FUTURE PLATFORMS SU-30 UPG IMRH AMCA LCA MKII UAV
77 TEST FACILITIES AT SLRDC
EMI/EMC TEST FACILITY POWER SUPPLY VARIATION TEST FACILITY
CE 101, CE 102, RE 101 AND RE 102 Test The facility is capable of injecting Power Supply Variation on DC, SAC (Single Phase AC) and (TAC) Chamber: 3 M Semi Anechoic Chamber with Three Phase AC power supplies, as per 3 M Shielded Room MIL-STD-704-8 and DO 160.
COMBINED ALTITUDE ESS CLIMATE CHAMBER TEMPERA-TURE HUMIDITY (CATH) CHAMBER Test Space Volume : 480 litres Temperature Range: -70°C to 180°C Test Space Volume: 600 litres Rate of Change: Up to 15°C per minute. Temperature Range: -70°C to Humidity Range: 10% to 95% RH 180°C Humidity Range:10% to 95% RH Vacuum Range: Up to 200 mBar absolute
COMBINED ALTITUDE THERMAL SHOCK CHAM-BER TEMPERATURE HUMIDITY (CATH) CHAMBER—2 Test Space Volume : 120 litre Temperature Range: -70°C to 180°C Temperature Range: -70°C to 125°C Hot Cabinet : Amb to 220°C Cold Rate of change of temperature: 5°C/ minute Cabinet: -70°C to 85°C between -55°C and 85°C & 10°C between -40°C and +65°C Test Space Volume: 1000 litre Humidity Range: 10% to 95% RH Vacuum Range: Upto 1 mBar absolute Over Pressure: 1700kPa
78 RAIN DRIP TEST
Drip Hole Pattern: 25 mm, Height of dispenser:1.2 meters from bottom, Standard Volume Flow Rate: 280liters / m2 / hr Height: 1.4m, Dispenser Area (2nos):38cm × 75 cm each
HALT/HASS TEST
Temperature Range:-100°C to 200°C, Rate of change of temperature: 60°C/ minute, Test Space Volume: 600 litre, Vibration: Up to 60 Grms Quasi Random Vibration, Degree of Freedom (DOF): 6 DOF
ACCELERATION TEST FACILITY (CENTRIFUGE)
Acceleration Range: 1g - 75g, Max Payload: 100 Kg per side, Arm radius: 1200 mm (Nominal), Platform Radius range: 800 mm - 1600mm.
VIBRATION TEST FACILITY (3.5 TON MACHINE)
Vibration shaker (3.5 ton) Machine type with slip table, Shaker can rotate to do vibration test in different orientations.
79 MISSION AND COMBAT SYSTEM R&D CENTRE (MCSRDC)
About MCSRDC MCSRDC is one of the R & D Centre of HAL established in November 2008 for design and development of Mission and Combat systems for Fixed wing and Rotary wing Aircraft and other aerial vehicles. MCSRDC develops avionics systems from concept to final product and certification for aircraft and helicopter applications. Design of avionics systems architecture, system software & hardware development, installation, integration and testing for aircraft and helicopters are its strengths.
CAPABILITIES • System Architecture Design & Development • Mission Avionics Hardware Design & Development • Mission Software Design and Development • Algorithms for Navigation and Weapon Guidance • Development of System Test Facilities • Avionics System Integration on Aircraft • Design for Structural & Electrical Modifications • Ground & Flight Testing Leading to Certification • Full Mission Simulators Design, Development & Upgrade
PROJECT EXECUTED • Upgrade of Jaguar DARIN I and maritime aircraft to DARIN III with near glass cockpit configuration, multimode radar, indigenous mission computer, digital Engine and Flight Instrument System & latest weapons • Integration of Indian specific Sensors & Weapons on Mirage 2000 A/c for enhanced Air to Ground operational capabilities. • DARIN-II (Display Attack Ranging and Inertial Navigation) upgrade of Jaguar Aircraft significantly enhancing mission and operational capabilities • Integration of Next Generation Laser Guided weapon & Anti-Ship Missile and Anti-Airfield Weapon on DARIN I/II aircraft • Design & Development of Indigenous Mission Computer for Mirage and Display Mission Computer (DMC) for IADS of LCH • Design & Development of Indigenous Real Time Operating System (HAL- RTOS) for Airborne Computer • Development of the Full mission and combat simulators for various projects
80 AIRCRAFT UPGRADE PROJECTS
Mission Management System (MMS) Hawk Mk-132 Aircraft Upgrade (Hawk- I) for Mid Life Upgrade of DO-228 • Indigenous Mission Computer • Integrated Sensor Management • Integration of A.I based Voice Activated Command System • Enhanced Situational Awareness • Secured voice communication & data link operation • RADAR and EO/IR video display • Embedded Virtual Training System (EVTS) • Mission Planning with Debrief functions • Integration of Weapons & EW Systems (RWR & CMDS) • Single & Twin Operator Console • Digital Map Generation (DMG) with Ground Proximity Configuration Warning (GPW)
INDIGENOUS MISSION & DISPLAY SYSTEMS
Mission Avionics (MC, DMG & SMD) - Light Integrated Avionics Display Suite Combat Aircraft MK1A (IADS) -Light Combat Helicopter • Mission Computer with latest processors • Interface with Engine, aircraft sensors & • MC as Bus Controller for four MIL-STD-1553B data communication Sys. bus • Human-Machine Interfaces (HMI) for Mission • Supports Digital Video switching -ARINC 818 STD Management • DMG with advanced digital map • Navigation and weapon system functions • Smart MFD with graphics and video generation & • Get-U-Home in case of both DMC failure ARINC 818 support
Automatic Flight Control System (AFCS) - Light Engine & Flight Display Unit Combat Helicopter (EFDU) – Jaguar (DARIN III) • Stability Augmentation System and Attitude Hold reduce pilot • Flight critical system work-load in the presence of turbulence. • Interfaces with Engine, Fuel • Control Augmentation System to optimise handling qualities & Hydraulic Pressure sensors • Auto pilot modes to release the pilot from routine flying of a/c activities
INTEGRATION OF WEAPONS & SYSTEMS
Jaguar DARIN III A/c Mirage 2000 I/TI • Integration of Software Defined Radio • Integration of New Generation Air to Ground weapon (SDR) Light Combat Helicopter • Integration of AESA Radar • Integration of Rockets, Guns and Anti-tank missile • Integration of New Generation Air to Air Missile & HMDS
TECHNOLOGY DEVELOPMENT PROJECTS
• HAL-RTOS Enhancements along with advanced security features • Artificial Intelligence based Automatic Target Recognition System • Artificial Intelligence based Prognostic Tool for Maintenance of Helicopter Components • Development of modules for High Speed Video and Data Bus: ARINC 818-2 & Video IP CORES
FUTURE PROGRAMMES
• Design and Development of Mission Computer Hardware and software for MiG 29K/KuB & Su 30MKI • Contemporary weapon and allied system integration on MiG 29K/KuB • Simulators for upgraded Jaguar, Mirage 2000, HTT-40 and LCH • Development of AFCS and IADS for IMRH and LUH • Development of Mission Planning and Debrief Station (MPDS) for fixed and rotary wing A/c • Integration of Solid State Weapon Control System for Jaguar A/c • Integration of Anti-Ship and Anti-Airfield Weapon for Jaguar – DARIN III A/c
81 Vibration Shaker System 3 Ton Vibration shaker for Random over Random (RoR), Sine over Random (SoR), Shock for all axes.
Thermal Chambers Thermal Chambers for Low temp. & High temp. testing of Hardware modules & LRUs. Temperature Range: -54°C to + 125 °C
Mission Computers Tester Standalone test equipment for testing Mission Computers
System & Software Integration Rigs Integration Rigs for testing software & system functionalities Software Development Tools Software Design, Development and Validation Tools viz SCADE Suite, Rational suite, LDRA, Rhapsody, DOORS, etc. Hardware Development Tools Wide range of hardware test and measurement equipments such as Bus analyzers for Avionics Digital Data Buses, Development platforms for cPCI/VME/VPX, Full Tool chain for PCB design and analysis, Development tools for latest PowerPC, ARM processors & FPGAs & HDL testing tools for DO-254 compliant FPGAs
82 Aerospace Systems & Equipment R&D Centre, Lucknow, India A glorious past, challenging present and promising future….
A BRIEF INTRODUCTION
Beginning as a Design Liaison Cell established in 1970 along with HAL -Lucknow to provide support to license production, the department gradually entered into indigenization of large number units for Kiran-Mk1/2, Ajeet, Marut and MiG Series of aircraft. Functionally re-structured as ASERDC in 1997 towards self-reliance, the center had developed more than 400 LRUs, in addition to a number of other diversified products like ground support equipment, test rigs and indigenisation of thousands of detail parts for various Aircraft Programmes. The Centre has also contributed the space programme by developing LRUs for PSLV, GSLV and also for UAVs. The Centre has core designers for various accessories systems supported by Assembly and Test Engineers and other multifaceted Engineers for Support departments & technicians. FEM based stress & thermal analysis & reliability analysis capability also exists. R&D Centre has its dedicated Procurement, Finance Cells, Prototype Shop, Environmental Test facility and IT Department. Development is undertaken from specification finalisation up to system integration in close co-ordination with airworthiness agencies and the customer. Centre provides full hand-holding during series production batches. Over 100 IPR have been filed by the Centre. 31 copy rights have been received.
CORE STRENGTHS :
ECS LRUs Competence to take up design, development and certification of following systems and LRUs both for civil and military aircraft, helicopters and UAVs: Ü Electrical DC Power Generation System Ü AC/DC Electric Power Control & Protection System Ü AC/DC Electrical Distribution System Ü Fuel Management System Ü Environmental Control System Ü Hydraulic Pumps, Actuators, Valves, Reservoirs Ü Wheels & Brake System Ü Taking up life building /upgrades/ Obsolescence management
PARTICIPATION : Electronics LRUs
ASERDC has participated in every aircraft / helicopter programme in the nation and has also taken up design and development for customers abroad. These include all programme from Ajeet to Dhruv, Sitara, Tejas, LCA(Navy), Saras, LCH, LUH, HTT-40 etc. A number of technology development projects have also been taken up/completed successfully to maintain competitive edge. Soft Switching Technology, Pulse Width modulation, 18 Pulse, Three Tube Fuel Probes, Micro-Controller based Controller are some examples.
83 INFRASTRUCTURE: Hydraulic System LRUs
Analysis Software : Unigraphics Nx, Abaqus, Matlab, OrCad. Functional Test Facilities for Pneumatic LRUs, Cold Air Unit, Hydraulic LRUs, Pumps, Actuators, Wheels Strength & Fatigue, Engine Fuel System, Electrical System Integration, Electrical Rotating Machines. Mechanical Strength Test Facilities for Vibration, Acceleration, Shock. Environmental Test Facilties: Hot, Cold, Altitude, CATH, Salt Fog, Fungus, Sand & Dust Humidity, Rain Drip Prototype Shop : Equipped with state of art machines like CNC milling, Drilling and Cylindrical Grinding etc Tie ups with leading academic institutions like IIT-Kanpur, IIT-Roorkee etc. Close technical interaction in areas of mutual interest. Approvals : DSIR, CEMILAC, DGCA, AS9100D
Electrical System LRUs
FUTURE GROWTH ROAD MAP
Ü Develop innovative thinking. Ü Constant updating of knowledge and passionately refine available knowledge and expertise. Ü Proactively identify the future trend of technology and develop products using these technologies beforehand. Ü Develop Tier-2 and Tier-3 suppliers to carry out low technology activities to complement and fulfill full system supplier role.
VISION:
Ü To be best-in-class accessories & full system provider for leading global aircraft/helicopter builders Ü To graduate from discrete LRU developer to complete system solution provider, both for military and civil aircraft/helicopter
LCA-Tejas Environmental Test Chambers
84 Facilities available at ASERDC, Lucknow
INFRASTRUCTURE & FACILITIES
Modeling and Analysis Tools like UG, Conventional & CNC Manufacturing facilities IDEAS, ABAQUS, ADAMS, ORCAD etc
ENVIRONMENTAL TEST FACILITY
HOT and COLD TEST CHAMBER
• Temp. range -55°C to 200°C • Environmental Stress Screening (ESS) (Ramp rate 7°C /min) • Chamber Size: 1x1x1.5 m3
HOT, COLD, ALTITUDE and HUMIDITY TEST CHAMBER
• Altitude: Up-to 80,000 ft. • Pressure Change rate: 2.5mBar/min • Temperature Range: -70°C to 110°C +/-1°C • Humidity upto 95+/-3% • Rotating Machines upto 9000 r.p.m. also can be tested • Chamber size: 1x1x1 m3
85 Facilities available at ASERDC, Lucknow
SAND & DUST TEST CHAMBER SALT-FOG TEST CHAMBER
• As per MIL-810F • As per MIL 810D • Chamber size: 1.0x1.0x1.0 m3 • Tank Volume: 1000 litre • Chamber size: 1.6 x 0.7 x 0.8 m3
RAIN DRIP TEST CHAMBER THERMAL SHOCK TEST
• Temperature Range: 23°C to 50°C • Chamber temp. Range: -70°C to +200°C • Size: 0.8X0.8X0.8 m3 • Change over time is less than a minute • Max. load capacity : 50 Kg • Size: 0.5X0.5X0.5m3
STRUCTURAL TEST
Vibration / Shock Test System: Pneumatic Shock Test Machine: Centrifugal Acceleration Machine: • Rated Force Sine Vector : ± 1500 Kg-F • Max payload: 200 Kg • Acceleration: 0.1 to 50g • Acceleration :50 g (Sine & Random), • Max Shock: 200 g (±10%) • Object Mass (max.): 100Kg 20 g (Shock)
86 Contact Us
MCSRDC Bengaluru
General Manager Mission and Combat System R&D Centre Hindustan Aeronautics Limited Bengaluru - 560017. India Tel: +91(80)22311712, 22323417 | Fax: +91-(80)22313185 Email: [email protected]
SLRDC Hyderabad
Business & Technology Development Group Strategic Electronics Research & Design Center Hindustan Aeronautics Ltd Balanagar, Hyderabad - 500042 Telangana, India Tel: +91-40-23878281, Extn: 6263 , Fax: +91-40-23879570 Email: [email protected] | Website: www.hal-india.co.in
ASERDC Lucknow
Aerospace Systems & Equipment Research & Design Center Hindustan Aeronautics Ltd Post Office HAL Lucknow - 226016, Uttar Pradesh, India Tel: +91-0522-2350994 | Fax: +91-0522-2349335 Email: [email protected] Website: www.hal-india.co.in
ASERDC Korwa
General Manager Hindustan Aeronautics Limited Korwa Division, P.O: HAL Korwa , Amethi, (U.P)-227412, India Tel: +91-5368-255005/255473 | Fax: +91-5368-256142/256148 Email: [email protected] | Web: www.hal-india.co
HAL Corporate Office Marketing
Hindustan Aeronautics Limited 15/1, Cubbon Road, Bengaluru - 560001, India Tel.: +91 80 2232 0197, 2232 0860, 22320017, 2232 0258 | Fax: +91 80 2232 0140 Email: [email protected] | Web: www.hal-india.co.in Bengaluru SHARAD
Hindustan Aeronautics Limited Corporate office : 15/1, Cubbon Road, Bengaluru-560 001 Website : www.hal-india.co.in