Otrag Stage Cutaway
Credit: courtesy Lutz Kayser
Otrag N2O4/Kerosene rocket engine. 27.5 kN. First and upper stages of low-cost booster. Out of production. Isp=297s. Pressure-fed, using cheapest possible propellants. Injection pressure: 40-15 bar; thrust control: 100-40 %. First flight 1977.
Pressurization: Compressed air 66% tank filling in blow-down mode; Injector: Radial like on like; Chamber cooling: Ablative phenolic; Material of injector, valves, bulkheads: AlMg5.
Application: First and Upper Stages.
Throttled thrust(vac): 11.000 kN (2,472 lbf). Thrust (sl): 25.000 kN (5,620 lbf). Thrust (sl): 2,500 kgf. Propellant Formulation: High Density Acid (HDA) (50% N2O4- 50% HNO3) Den: 1.66 gr/cm^3 / Diesel fuel or Kerosene.
Status: Out of production.
More... - Chronology...
Diameter: 0.27 m (0.88 ft).
Thrust: 27.50 kN (6,182 lbf).
Specific impulse: 297 s.
Specific impulse sea level: 270 s.
Burn time: 150 s.
First Launch: 1975-1987.
Number: 1152 .
Associated Launch Vehicles
Otrag $200 million was spent from 1975-1987 by Lutz Kayer in a serious attempt to develop a low-cost satellite launcher using clusters of mass-produced pressure-fed liquid propellant modules. The project was finally squelched by the German government under pressure from the Soviet and French. More...
Associated Manufacturers and Agencies
Otrag German manufacturer of rocket engines and rockets. Orbital Transport-und-Raketen Aktiengesellschaft, Germany. More...
N2O4/Kerosene Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. 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...
Kayser, Lutz, Personal communication, 2005.,
Otrag N2O4/Kerosene propellant rocket stage. Loaded/empty mass 1,500/150 kg. Thrust 26.96 kN. Vacuum specific impulse 297 seconds. Clustered to form Otrag launch vehicles. Pressure-fed, using cheapest possible propellants. Injection pressure: 40 - 15 bar; Thrust control: 100% - 40 %; Pressurization: Compressed air 66% tank filling in blow-down mode; Injector: Radial like on like; Chamber cooling: Ablative phenolic; Material of injector, valves, bulkheads: AlMg5; Material of cylindrical tank sections: cold rolled low carbon stainless steel. More...
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