Encyclopedia Astronautica

Credit: © Mark Wade
Glushko Nitric acid/UDMH rocket engine. 883 kN. R-16 stage 2. Isp=293s. Derivative of RD-217 with a truss and piping changes. Despite higher expansion ratio, engine was shorter than first stage version, with relatively low performance. Flown 1960-1972.

RD-219 is a derivative of RD-217 with a truss and some piping changes. Despite higher expansion ratio the engine is shorter than first stage engines. The result is relatively low performance, with Isp just 3 sec more than that of 1st stage in vacuum. Engine Cycle: Open. Feed Method: single turbopump feeding two gimballed chambers. Diameter is per chamber.

Application: R-16 stage 2.


Chambers: 2. Engine: 760 kg (1,670 lb). Chamber Pressure: 73.60 bar. Area Ratio: 25.8. Propellant Formulation: AK27I/UDMH. Thrust to Weight Ratio: 118.35. Oxidizer to Fuel Ratio: 2.5.

AKA: 11D26; RD-219; 8D713.
Unfuelled mass: 760 kg (1,670 lb).
Height: 2.03 m (6.66 ft).
Diameter: 2.16 m (7.08 ft).
Thrust: 883.00 kN (198,506 lbf).
Specific impulse: 293 s.
Burn time: 125 s.
First Launch: 1958-61.
Number: 212 .

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Associated Countries
See also
Associated Launch Vehicles
  • R-16 Ukrainian intercontinental ballistic missile. The Soviet Union's first practical ICBM, a two stage vehicle using storable propellants. Development began in 1956 and the missile was in service from 1962 to 1974. Peak deployment consisted of 186 launchers, about a third of them in missile silos, the rest in fixed 'soft' installations. 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...

  • Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
  • Haeseler, Dietrich, Information from NPO Energomash museum exhibit, Nov. 1992 via Dietrich Haeseler.
  • Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.

Associated Stages
  • R-16-2 Nitric acid/UDMH propellant rocket stage. Loaded/empty mass 27,000/3,000 kg. Thrust 882.10 kN. Vacuum specific impulse 293 seconds. Range 12,000 km. Tsniimash has 1:10 structural simulation model. Two stage ICBM with nitric acid oxidizer. Developed 1956-1961. Entered service 1961. Chief designer Yangel. Source: Placard, TsNIIMASH. More...

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