| 摘要 |
A device for supplying rocket engine propellant (10A, 10B) comprising at least one propellant tank (10, 11), a combustion chamber (18), a supply pipe (12, 13) extending from the tank (10, 11) to the combustion chamber (18) to supply propellant to the combustion chamber. A valve (14, 15) and a main pump (16, 17) are disposed respectively on the supply pipe. The rocket engine device further comprises at least one bypass pump (20, 21, 120, 220) connected in bypass to the tank upstream of the valve, in order to supply an auxiliary pipe (22, 23, 122, 222) carrying out an auxiliary function of the rocket engine. |
