Encyclopedia Astronautica

Credit: Yuzhnoye
Yuzhnoye Lox/Kerosene rocket engine. 88 kN. Upper stages. Isp=345s. 2007 design concept for a four-chamber restartable main engine for launch vehicle upper stages.

The engine was evidentaly a restartable version of the RD-8 Zenit-2 second stage vernier engine assembly and had the following features:

  • Long service life (4000 seconds, five restarts)
  • Designed for installation in the upper stage after a factory firing test without the need for post -test refurbishment
  • Stage flight control is effected by gimballing each combustion chamber 10% in one plane.
  • All four-chambers pump-fed using a combustion scheme with oxidizer-rich gas feeding the turbopumpts.
  • Turbine rotor spun-up by a pneumatic starter
  • Propellants in the combustion chamber and gas generator ignited by dedicated startup fuel
  • Pneumatic gimabl units used helium gas delivered via electric-pneumatic valves
  • Single-mode engine providing constant thrust and propellant mixture ratio within 4.5% / 8.
  • Pressure sensors provide data for automatic startup and shutdown of engine

Application: Upper stages.


Chambers: 4. Chamber Pressure: 87.75 bar. Oxidizer to Fuel Ratio: 2.5. Restarts: 6.

Status: Design concept 2007.
Height: 1.67 m (5.47 ft).
Thrust: 88.00 kN (19,783 lbf).
Specific impulse: 345 s.
Burn time: 4,000 s.

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Associated Countries
See also
Associated Manufacturers and Agencies
  • Yuzhnoye Ukrainian manufacturer of rockets, spacecraft, and rocket engines. Yangel Design Bureau, Dnepropetrovsk, Ukraine. More...

Associated Propellants
  • Lox/Kerosene Liquid oxygen was the earliest, cheapest, safest, and eventually the preferred oxidiser for large space launchers. Its main drawback is that it is moderately cryogenic, and therefore not suitable for military uses where storage of the fuelled missile and quick launch are required. In January 1953 Rocketdyne commenced the REAP program to develop a number of improvements to the engines being developed for the Navaho and Atlas missiles. Among these was development of a special grade of kerosene suitable for rocket engines. Prior to that any number of rocket propellants derived from petroleum had been used. Goddard had begun with gasoline, and there were experimental engines powered by kerosene, diesel oil, paint thinner, or jet fuel kerosene JP-4 or JP-5. The wide variance in physical properties among fuels of the same class led to the identification of narrow-range petroleum fractions, embodied in 1954 in the standard US kerosene rocket fuel RP-1, covered by Military Specification MIL-R-25576. In Russia, similar specifications were developed for kerosene under the specifications T-1 and RG-1. The Russians also developed a compound of unknown formulation in the 1980's known as 'Sintin', or synthetic kerosene. More...

  • Yuzhnoye Company Web Site, Web Address when accessed: here.

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