Encyclopedia Astronautica
RD-161P


Glushko H2O2/Kerosene rocket engine. 24.5 kN. Soyuz M stage 3 (block LM). Developed 1993-. Two thrust levels. Minimum 1500 kgf. Proposed for use on Soyuz M-3. Version for H2O2 fuel, concentration 96-98%. Isp=319s.

Application: Soyuz M stage 3 (block LM).

Throttled thrust(vac): 14.700 kN (3,305 lbf). Engine: 105 kg (231 lb). Chamber Pressure: 117.70 bar. Area Ratio: 265. Thrust to Weight Ratio: 23.79. Oxidizer to Fuel Ratio: 5.9.

Status: Developed 1993-.
Unfuelled mass: 105 kg (231 lb).
Height: 1.45 m (4.75 ft).
Diameter: 1.24 m (4.06 ft).
Thrust: 24.50 kN (5,508 lbf).
Specific impulse: 319 s.
Burn time: 900 s.
First Launch: 1993-.

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Associated Countries
See also
Associated Launch Vehicles
  • Soyuz M Rus project was to result in first major propulsion upgrade to R-7 family in forty years, using first stage engines derived from those developed for Zenit second stage to boost performance. It would have permitted launches from Plesetsk with same or greater payload than launch of standard Soyuz-U from Baikonur, permitting move of more launch operations back onto Russian territory. Instead the more modest Soyuz ST / Soyuz FG upgrades were made. More...

Associated Manufacturers and Agencies
  • Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. More...

Associated Propellants
  • H2O2/Kerosene Hydrogen peroxide is used as both an oxidiser and a monopropellant. Relatively high density and non-toxic, it was abandoned after early use in British rockets, but recently revived as a propellant for the Black Horse spaceplane. Rocket propellant RP-1, or its foreign equivalents, is a straight-run kerosene fraction, which is subjected to further treatment, i.e., acid washing, sulphur dioxide extraction. Thus, unsaturated substances which polymerise in storage are removed, as are sulphur-containing hydrocarbons. More...

Bibliography
  • Haeseler, Dietrich, NPO Energomash exhibit at Moscow Airshow MAKS 93, Moscow, 1993 via Dietrich Haeseler.

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