| 摘要 |
The invention relates to a device for driving a rocket engine (16) pump (2) of a spacecraft having an internal combustion engine (1a, 1b) of the air-breathing type and operating with an oxidizer, air-type fuel, hydrocarbon mixture, said oxidizer and fuel being supplied by a circuit and tanks (3) of rocket engine (16) propellants. The invention is intended for a rocket engine supply apparatus including at least two pumps which are each driven by the device of the invention and means (8, 9) for controlling internal combustion engines driving pumps designed to vary the operating parameters of the engines independently so as to control the rotation speeds of the pumps independently. The invention also relates to a method for starting and powering a rocket engine using pumps driven by at least one device in accordance with the invention. |
