| 摘要 |
<p>The device, suitable for intermittent operation, comprises first (1) and second (2) main tanks of first and second liquid cryogenic propellants respectively, fuel and oxidizer respectively, first (3) and second (4) means of vaporizing the first and second liquid propellants respectively, and at least one propulsive combustion chamber (19) fed by the vaporized propellants. According to the invention, the first (3) and second (4) vaporization means are in thermal transfer relation with the combustion chamber (19), the first and second vaporized propellants pass into the first (9) and second (10) compression means respectively, and the gases compressed in these first (9) and second (10) compression means are stored in first (15) and second (16) surge tanks respectively, arranged between the compression means (9, 10) and the combustion chamber (19). Applicable to the top stage of a geostationary satellite launch vehicle.</p> |
