| 摘要 |
FIELD: engines and pumps.SUBSTANCE: spacecraft rocket engine pump drive comprises aerobic internal combustion engine 1a, 1b running on the mix of fuel oxidiser, air-type fuel and hydrocarbon. Fuel oxidiser and fuel are fed to said engine by tanks and circuit separated from tanks 3 of propergols for rocket engine 16. Invention may be used in rocket engine supply device composed of, at least, two pump incorporating above described drive and ICE pump drive control means 8, 9 adapted to independently vary ICE operating parameters to allow independent control over pump rpm.EFFECT: higher reliability, starting in flight, multiple use.14 cl, 3 dwg |
