Yuzhnoye State Design Office named after M.K.Yangel was founded in 1954 to initiate development of strategic- purpose missile-weapon complexes.
More than 50 years of collaboration with PA Yuzhny Machine-Building Plant, academic, science and research, manufacturing enterprises of former Soviet Union resulted in the development and production of four generations of strategic missiles, represented by 13 modifications which formed the basis of strategic missile forces. There were also produced 7 types of world-class launch vehicles (Kosmos, Interkosmos, Cyclone-2, Cyclone-3, Zenit-2, Zenit-3SL, Dnepr). SDO YUZHNOYE’S ORGANIZATION CHART
General Designer – General Director Dr. Stanislav Konyukhov
First Deputy General Designer – First Deputy General Designer – First Deputy General Director – General Director General Director Chief Engineer System Design and Business Development Mr. Alexander Mashchenko Dr. Alexander Degtyarev Mr. Vladimir Vasilina
Deputy General Deputy General Deputy General Deputy General Deputy General Deputy General Designer on Designer on Designer on Designer on Designer on Designer on Scientific work Propulsion testing and Management and personnel Information Systems operations Coordination Resources Dr. Perlik Mr. Shnyakin Mr. Agarkov Mr. Kuryachiy Mr. Novikov Mr. Polyakov
Heads of Design Offices, Divisions and Departments
Analysis and Experimental Design Analysis Design Design Division Design Design Experimental Testing Division Division Division Division Division Testing Division Division Development of Ballistics, Manufacture Development of Development of Development Structural Strength Power Supply Space Launch Aerodynamics, Vehicles and Drawings Space Systems Liquid\Solid of Actuators, of Units, Systems and Missiles Heat, Mass Documentation and satellites; Propellant Special Subsystems and Liquid Propellant Complexes for Launch Telemetry and Engines and Systems and systems of Launch Propulsion Vehicles and Communications Pyrotechnics Assemblies Vehicles and Systems Missiles Equipment Missiles Finalizing
Material Design Design Preparation Division Marketing Department Division Development Supervision Division and Support and Foreign Division and Conversion Division Administration, Economic Scientific and Preparation, Operations Activities Planning, Affairs engineering Classification, Testing of Division Research Coordination of Division information; Coding, Manufacture Civil work and works, technical patent and Registration Technology, Products Experimental and economic license and Storage of Material Development Finalizing analysis and research Design Research and financial Documentation Analysis accounting SPACE-ROCKET TECHNOLOGY SYSTEM DESIGN AND DEVELOPMENT
ROCKET-SPACE COMPLEXES SPACE SYSTEMS Including Including LAUNCH VEHICLES SPACECRAFT
Upper Stages Platforms
Fuel Systems Actuators, Mechanisms
Rocket Body Sections Propulsion Systems
Liquid and Solid-Propellant Rocket Engines Thermostatic Control Systems
Aerodynamic Fairings Antenna-Feeder and Antenna-Waveguide Devices
Actuators and Special Systems Onboard Switchgear Equipment
Launch Complex and its Infrastructure
Processing Complex and its Infrastructure
Assembly, Integration and Test Facilities
Software Support
Experimental-Test Works
Support of Works Performed by Participating Institutions on Ground Complexes, Propulsion Systems, Control Systems, Measurement Systems and other Systems of Rockets and Spacecraft COMPETITIVE ADVANTAGES
¾ Over 50 years of experience in designing, developing and manufacturing rocket-space and spacecraft technologies;
¾ Rich experience in International cooperation with leading European, American, Asian and Arabic aerospace companies and organizations;
¾ Wide and long-term established cooperation with the leading Ukrainian and Russian aerospace companies, organizations and representatives of other industries;
¾ Experienced in cooperation under International Standards within the frames of different International Programs; COMPETITIVE ADVANTAGES
¾ Flexible in applying and adapting standards required by a Customer/ Contractual Terms and Conditions;
¾ Possesses a complete technological cycle starting from designing spacecraft up to the launch of spacecraft using launch-vehicles of its own development;
¾ Active in developing and commercializing new space and civil application technologies;
¾ Competitive pricing policy;
¾ Open for new directions of cooperation;
¾ Reliable and experienced Partner for new and already established partnership. STANDARDS AND CERTIFICATION
Quality Management - ISO 9001-2000;
SDO Yuzhnoye’s Quality Management System complies with the requirements of the International Standard ISO 9001:2000, its Ukrainian (DSTU ISO 9001-2001) and Russian (GOST R ISO 9001-2001) analogues.
73 enterprise standards regulating various types of SDO Yuzhnoye’s activity;
Flexible in applying and adapting Standards required by Customers/ Contractual terms and Conditions;
Rich experience in cooperation with International Partners under such programs as SEA LAUNCH Program, VEGA LV Program and etc.
LAUNCH FACILITIES
Railroad Launch (SS-24) Cyclone 3 Air Based Launch
Plesetsk
Dniepropetrovsk Baikonur Cyclone 2
Platform Odyssey Dnepr Zenit 3SL Zenit 2 PROSPECTIVE LAUNCH SYSTEMS
In the nearest time Yuzhnoye will be able to propose newly developed launch vehicles for providing customers with reliable launch services. The new systems are Zenit-3SLB and Zenit-2SLB (launch services will be provided by the Land Launch Joint Stock Company) and Cyclone-4 (launch services will be provided by Alcantara Cyclone Space Joint Stock Company). CYCLONE-4
Number of stages 3 Launch site: Alcantara (Brazil) Lift-off mass, t (without PL) 191 Propellant components Launch site has convenient geographical position and provides wide range of launch Oxidizer NTO azimuths Fuel UDMH Propellant mass, t Performance capability for GTO is: 1600 kg 1st Stage 121 (Alcantara, i=5.1 degrees) 2nd Stage 49 3rd Stage 9 PAYLOADPAYLOAD CAPABILITIESCAPABILITIES Vacuum thrust 6000 of engines, tf 5000 1st Stage 303 4000 2nd Stage 101.5 3rd Stage 7.9 3000 Injection accuracy Gpl, kg 2000 for Hcirc=500 km, i=90º: 1000 On altitude, km ±5 0 On inclination, deg ±0.05…0.08 2000 3000 4400 6000 8000 for GTO: On altitude, km 5.0 (perigee) Hcirc, km 100 (apogee) On inclination, deg ±0.05…0.08 MAYAK FAMILY LAUNCH VEHICLES
Launch mass, t 130 185 250 320 375
# of stages/boosters 2/0 2/4 2/0 3/0 3/4 Payload mass, kg: 2800 0 Hcirc=200km, i=50 4500 6400 8800 11500 - H=150/35860 km, i=2.10 1300 1800 3000 3800 ROCKET ENGINES DEVELOPED BY YUZHNOYE More than 35 liquid rocket engines and liquid propulsion systems have been developed
TheThe achieved achieved level level ofof reliability reliability
ForFor L Liquiquidid Rocket Rocket En Engginesines ForFor Solid Solid propellant propellant nono less less than than RocketRocket Mo Motorstors 0,9920,992-0,999-0,999 0,9950,995-0,999-0,999 LIQUID ROCKET ENGINES RD858 AND RD859 OF THE LUNAR MODULE
A highly reliable engine cluster and propulsion system are designed for the N-1 Lunar Launch System. The propulsion system ensures soft landing on the Moon surface and take- off of the Moon, and insertion of the lunar vehicle into the lunar orbit.
The engine cluster includes: • RD-858, a single-chamber dual-mode main engine; • RD-859, a two-chamber single-mode backup engine. Each engine ensures two burns.
High reliability of the engines was proven by a large number of ground tests. Total operating time is: • 253281 s for RD-858; • 209463 s for RD-859.
Three propulsion systems were successfully flight-tested in the composition of the Earth artificial satellite. SDO YUZHNOYE IS CAPABLE OF INJECTING PAYLOADS INTO THE FLIGHT TRAJECTORY TO THE MOON OR DIRECTLY INTO THE NEAR-MOON ORBIT USING ITS LAUNCH-VEHICLES
PAYLOAD CAPABILITIES ILV Payload mass, kg into near-moon to the Moon orbit
Zenit – 3SL 4200 ~1000*
Zenit – 3SLB 3900 ~1000*
Dnepr-1 with AST-1 500 200-250
* using orbital propulsion system (DU-802) as an adjusting and inhibiting propulsion system. In case of development of propulsion system modification with increased propellant reserve (~1000 kg) the mass of payload into near-moon orbit can be increased up to ~2500 kg for Zenit-3SL ILV and up to ~2300 kg for Zenit-3SLB ILV. MAIN SPECIFICATIONS OF THE ENGINES RD858 AND RD859
Propellants NTO+UDMH Vacuum thrust, kgf – main engine from 400 to 2250 – backup engine 2045 Vacuum specific impulse, s – main engine 315 – backup engine 312 Burn time, s – main engine up to 470 – backup engine up to 400 Engine cluster mass, kg 110 Mixture ratio – main engine from 1,6 to 2,03 – backup engine 2,0 MAIN ENGINE ASSEMBLY FOR THE EUROPEAN VEGA LV
The Main Engine Assembly is a part of Liquid Propulsion System for Attitude Vernier Upper Module of the European Vega Launch Vehicle.
The MEA is developed under a Contract with Avio (Italy) on the basis of units from serially produced engines.
Purposes of the MEA are as follows: 9Thrust generation; 9Pitch/yaw control; 9Upper Module maneuvering; 9Upper Module deorbit.
Propellants NTO+UDMH Vacuum thrust, kgf 250 Vacuum specific impulse, s 315.5 Number of burns 5 DU802 PROPULSION SYSTEM
Currently the Upper Stage for Ukrainian – Russian Dnepr LV has been designed and is now under intensive testing. A principally new propellants supply system was introduced with the use of Pneumopump Assembly (PPA). Utilization of PPA allows to increase power-mass characteristics, some of which cannot be reached by the existing propulsion systems.
Propellants: • Oxidizer NTO • Fuel UDMH Propellants mass, kg 250–500 Dry mass, kg 165.4
•Vacuum specific impulse, s •- Main engines (ME) 322,5 •- Thruster 243 •Vacuum thrust, kgf •- ME 450 •- Thruster 11,1 •Mixture rate 2,25 •Number of ME burns 10
Propellants supply system has been tested (pressurization system, propellants tanks and PPA). PNEUMOPUMP
The pneumopump unit is a component of DU 802 propulsion unit.
Working media: • Oxidizer NT • Fuel UDMH • Gas Helium • supplying pressure 25 - 70 kgf/cm2
Flow-rate: • oxidizer up to 1.1 kg/s • fuel up to 0.5 kg/s
Helium pressure 10-30 kgf/cm2
Helium temperature 450 К
Efficiency 0.75 ENGINE UNIT OF DU802 PROPULSION SYSTEM
The engine unit is a component of DU 802 liquid propulsion system
Propellants NTO+UDMH
• Vacuum thrust, kgf 450 • Vacuum specific impulse, s 322.5 • Mixture ratio 2.25 • Number of burns up to 10 • Burn duration of a single run, s: • - max 350 • - min 3 • Total burn duration, s 350
A phase of development tests has been accomplished LIQUID ROCKET ENGINE RD861K
The engine RD861K is designed for generating thrust and ensuring control in pitch and yaw channels through an active leg of the Cyclone-4 LV third stage flight.
Propellants: - Oxidizer NTO -Fuel UDMH Vacuum thrust, kgf 7916 Vacuum specific impulse, s 330 Mass, kg 207 Number of burns 3…5 Total burn duration, s 450 Length, mm 2000 Diameter of nozzle exit, mm 1010 TEST BASE OF YUZHNOYE SDO AND YUZHMASH PLANT
SDO Yuzhnoye is capable of performing firing tests of any engine with propellants NTO + UDMH and thrust of up to 120 tf, as well as engines with LOX + Kerosene and thrust of up to 100 tf.
SDO Yuzhnoye will soon be capable of performing tests of engines with propellants LOX + Methane. SATELLITES DEVELOPED BY YUZHNOYE MS-2-8 “SICH-2” SATELLITE
Mass, kg 160 Orbit:
- altitude, km 668 - inclination, deg 98 Wavelengths for imaging modes, μm: - panchromatic 0.50-0.89 - multispectral 0.50-0.59; 0.61-0.68; 0.79-0.89 Resolution in nadir, m 7.8 – pan; 30 – multi. Swath width in nadir, km 46.6 Coverage area width, km ±500 Accuracy, deg. 0.2 The MS-2-8 satellite is designed for the Frequency band for store & forward Earth Remote Sensing with the use of communication payload, MHz: mid-high resolution multi-band - uplink 144…146 imager. In addition, the satellite - downlink 435…438 provides store & forward messaging Frequency band for payload, MHz 8 025 … 8 400 service Frequency bands for radio-lines, 2 025 … 2 110 MHz 2 200 … 2 290