Encyclopedia Astronautica
RD-0235



wrd0235.jpg
RD-0235
Credit: KBKhA
Kosberg N2O4/UDMH rocket engine. 240 kN. UR-100N / RS-18 (SS-19) stage 2. Main engine based on RD-0217 with larger nozzle for altitude operation. Staged combustion cycle. Isp=320s. First flight 1972.

Application: UR-100N / RS-18 (SS-19) stage 2.

Chamber Pressure: 175.00 bar.

Thrust: 240.00 kN (53,950 lbf).
Specific impulse: 320 s.
First Launch: 1969-74.
Number: 315 .

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • UR-100N Russian intercontinental ballistic missile. The UR-100N was designed as a replacement for the UR-100 at the end of its ten year storage life. Although it could be installed in the same silos, it was 50% heavier. The competing design of Yangel, the MR-UR-100, was also put into production when the Soviet hierarchy deadlocked and could not pick one design over the other. More...
  • Rokot Russian all-solid orbital launch vehicle, consisting of decommissioned UR-100N ICBMs with a Briz-KM upper stage. More...

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

Associated Propellants
  • N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...

Bibliography
  • Pavutniskiy, Yu M; Mazarchenko, V A; Shilenkov, M V; Gerasimov, A B, Otechestvennye Rakety-Nos 1 and 2, St.Peterburg (State Marine-Technol. Univ.), 1996 via Dietrich Haeseler.
  • ROCKOT Users Guide, Issue 2, Rev. 0, Eurockot Launch Services, Bremen 1998. via Dietrich Haeseler.

Associated Stages
  • UR-100N Stage 2N N2O4/UDMH propellant rocket stage. Loaded/empty mass 12,195/1,485 kg. Thrust 214.27 kN. Vacuum specific impulse 322 seconds. Engine has one main engine and four verniers. Verniers continue to burn for 19 seconds after mainstage shutoff. More...

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