N2O4/UDMH propellant rocket stage. Loaded/empty mass 9,400/900 kg. Thrust 98.00 kN. Vacuum specific impulse 330 seconds. Masses, thrust, specific impulse estimated based on total vehicle mass of 28.5 tonnes and first stage burn time of 140 seconds. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions.
Status: Development ended 1992.
More... - Chronology...
Gross mass: 9,400 kg (20,700 lb).
Unfuelled mass: 900 kg (1,980 lb).
Height: 5.50 m (18.00 ft).
Diameter: 1.60 m (5.20 ft).
Span: 1.60 m (5.20 ft).
Thrust: 98.00 kN (22,031 lbf).
Specific impulse: 330 s.
Specific impulse sea level: 230 s.
Burn time: 275 s.
Burlak Stage 2 N2O4/UDMH rocket engine. 98 kN. Burlak stage 2. Development ended 1992. Isp=330s. Air launched from Tu-160 at 13,500 m, Mach 1.7 release conditions. More...
Associated Launch Vehicles
Burlak Russian air-launched winged orbital launch vehicle. Burlak air-launched satellite launcher was proposed in 1992 and studied by Germany in 1992-1994. Evidently based on secret anti-satellite missile. Air launched from Tu-160 bomber, released at 13,500 m altitude and Mach 1.7. Development estimated to cost only DM 50 million, but not proceeded with. Burlak/Diana variant would have been launched from Concorde. More...
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...
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