| 摘要 |
A rocket drive for space flights, having a ground thrust nozzle and an altitude thrust nozzle, which can be adjusted in the axial direction and is located in a drawn-forward position during launching and flight at low altitudes, but in contrast is connected to the rear end of the ground thrust nozzle during flight at high altitudes. The ground thrust nozzle is designed as an overexpansion nozzle up to an altitude of approximately 12 to 14 km, and produces an exhaust pressure of approximately 0.2 to 0.15 bar. Up to an altitude of approximately 12 to 14 km, the altitude thrust nozzle is located in such a drawn-forward position that a second, outer thrust circle is produced, and in this case the rear region of the altitude thrust nozzle together with the radially inner ground thrust nozzle as well as its drawn-in central thrust jet, which drives the outer thrust jet by means of an injector effect, forms a convergent-divergent supersonic annular nozzle for this outer thrust jet. At an altitude of approximately 12 to 14 km, the altitude thrust nozzle is moved back and axially connected to the ground thrust nozzle. The altitude thrust nozzle is designed as an overexpansion nozzle with respect to the environmental pressure prevailing at the altitude of approximately 12 to 14 km such that it produces an exhaust pressure of approximately 0.03 to 0.02 bar. |
