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SOLID-PROPELENT SPECIAL ENGINES PULSED CONTROL SRM Usage of micro SRM provides short-time control pulses along the yaw and pitch channels Basic characteristics: Propellant composite, high-energy Operating time, s 0.045 … 0.05 Thrust, kgf up to 500 Case high-strength steel...

SOLID-PROPELLANT MAIN ENGINES MAIN SOLID ROCKET MOTORS The main functions are: thrust application; producing control force along the yaw and pitch channels with rotating control nozzle (RCN); performance of all SRM characteristics under the specified external influences in every phase of...

LIQUID-PROPELLANT THRUSTERS LOW-THRUST Liquid-propellant thrusters are incorporated in liquid-propellant jet propulsion systems and generate thrust by propellant exhaust through a supersonic nozzle. Cyclone-3 Rocket 100 N Thruster Cyclone-3 Rocket 30 N Thruster...

RD-880 The engine is dual-chamber, two-mode, single firing, with turbopump propellant feed system, made according to oxidizing generator gas afterburning scheme. The engine is developed on the basis of Zenit LV proven technologies. RD880.1 single-chamber engine with thrust 500 tf can be...

RD-815 Main engine with turbopump propellant feed system, made according to generator gas afterburning scheme. The engine is developed on the basis of Zenit LV proven technologies. The engine has high mass-energy characteristics. This engine is designed for the use in most advanced LV of...

RD-810 The RD810 generates thrust and controls flight of launch vehicle first stages. The staged-combustion engine is based on proven Zenit launch vehicle technologies. The RD810 is a single-chamber, dual-mode single-burn engine with a turbo-pump-feed system. The engine gimbaling in two...

RD-801 The RD801 engine generates thrust and controls flight of the Mayak launch vehicle first stage. The engine is based on technologies tested on the Zenit launch vehicle. The RD801 is a single-chamber, dual-mode, single-burn engine with a turbo-pump-feed system. The engine uses...

RD-870 RD870 engine block (EB) with turbopump propellant feed system is made according to generator gas afterburning scheme. The EB is developed on the basis of Zenit LV proven technologies. RD872 engine can be developed on its basis for LV second stage with thrust ~90 tf. BASIC...

RD-835 RD835 main engine with turbopump propellant feed system, made according to generator gas afterburning scheme, and in-flight two-times firing. The engine has high mass-energy characteristics. This engine is designed for the use in most advanced LV of Mayak type, developed by Yuzhnoye...

RD-809K The RD809K engine generates thrust and controls flight of the upper stages of the Mayak family rockets. The engine is based on the Cyclone-4 rocket third-stage RD861K sustainer chamber and the Zenit rocket second-stage RD-8 steering engine assemblies. The staged-combustion RD809K is a...

RD-805 The main engine is single-chamber, single-mode, single firing, with turbopump propellant feed system, made according to oxidizing generator gas afterburning scheme. The engine is developed on the basis of proven units of Zenit LV RD-8 high-reliable series-production steering engine...

RD-860, RD-860L, DU-802 RD860 and RD860L engines with pneumatic pump propellant feed system are designed for LV upper stages, space tugs and unmanned takeoff and landing modules. RD860L engine consists of two blocks (EB-1 – dual-chamber, stationary, EB-2 – RD860 engine with gimballing). The...

RD-840 Apogee main engine is single-chamber, single-mode, multiple firing, with propellant-pressurized feed system. It is designed for SC add-on injection into orbits, including geostationary orbit. BASIC SPECIFICATIONS Engine mass, kg 4.3 Propellant components...

RD-861K The RD861K engine generates thrust and provides pitch and yaw control of the Cyclone-4 third stage powered flight. The engine is based on a highly reliable RD861 serial engine used in the Cyclone-3's third stage. The open-cycle RD861K is a single-chamber engine with a turbo-pump-feed...

RD-843 The RD843 engine generates thrust and provides two-axis flight control of launch vehicle upper stages and booster stages. The RD843 is a single-chamber engine with a pressure-fed supply system of hypergolic propellants. The engine gimbaling in two mutually perpendicular planes...

HISTORY OF SOLID ROCKET MOTORS The first solid rocket motor (SRM) designed by Yuzhnoye was a 15D15 main motor for the first stage of the 8K99 missile. The motor development started in 1963. The first firing of the 15D15 motor was conducted in April 1965. However, in October 1969, development...

HISTORY OF LIQUID-PROPELLANT ROCKET ENGINES In 1958, development of steering engines for the first and second stages of the 8K64 ICBM became Yuzhnoye’s first experience of independent development of liquid-propellant rocket engines (LPRE). The main feature of this missile was a new fuel...

LIQUID-PROPELLANT ROCKET ENGINES PROPULSION SYSTEM FOR MANNED LUNAR VEHICLE Propulsion engineers of Yuzhnoye design office carried out an important and complex task: they developed an 11D40 propulsion system for the lunar landing vehicle. The 11D410 propulsion system consisted of an RD-858...

As far as I know China is another costumer who selected Ukrainian gas turbines. Regarding gas turbines, Turkey and Ukraine formed a JV institute called Lodos and Acc to deal, The marine gas turbine engines will be manufactured in Turkey. Establishment of this new JV institute may give us an idea...

How they can export such products to Russia without taking permission of Ukrainian state?