Encyclopedia Astronautica
RD-224


Glushko Nitric acid/UDMH rocket engine. 1778 kN. R-26 stage 1. Out of production. RD-224 is a block of 2 RD-225s. An upper stage thrust chamber was developed under designation U102-000. Isp=294s. First flight 1961.

Application: R-26 stage 1.

Chambers: 4. Engine: 1,250 kg (2,750 lb). Chamber Pressure: 83.40 bar. Area Ratio: 21. Propellant Formulation: AK27P/UDMH. Thrust to Weight Ratio: 145.04. Oxidizer to Fuel Ratio: 2.5.

AKA: 8D721.
Status: Out of production.
Unfuelled mass: 1,250 kg (2,750 lb).
Height: 2.00 m (6.50 ft).
Diameter: 2.27 m (7.44 ft).
Thrust: 1,778.00 kN (399,710 lbf).
Specific impulse: 294 s.
Specific impulse sea level: 251 s.
Burn time: 100 s.
First Launch: 1960-62.

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • R-26 Ukrainian intercontinental ballistic missile. Two stage light ICBM developed 1960-1962, but cancelled so that Yangel could concentrate his efforts on the R-36. After project cancellation, a mock-up of this missile was shown in Moscow parades and misidentified for years by Western analysts as the 'SS-8'. More...

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

Associated Propellants
  • Nitric acid/UDMH Drawing on the German World War II Wasserfall rocket, nitric acid (HNO3) became the early storable oxidiser of choice for missiles and upper stages of the 1950's. To overcome various problems with its use, it was necessary to combine the nitric acid with N2O4 and passivation compounds. These formulae were considered extremely secret at the time. By the late 1950's it was apparent that N2O4 by itself was a better oxidiser. Therefore nitric acid was almost entirely replaced by pure N2O4 in storable liquid fuel rocket engines developed after 1960. 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
  • Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.

Associated Stages
  • R-26-1 Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 60,300/3,000 kg. Thrust 1,451.00 kN. Vacuum specific impulse 310 seconds. Orevo has sectioned hardware. Tsniimash has 1:10 structural simulation model. All figures accurate except empty mass estimated. Source: Placard, TsNIIMASH, Orevo. More...

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