Rocket engine, particularly liquid rocket engine, has thrust chamber and pump unit, where thrust chamber is supplied to fuel component by pump unit, in which thrust chamber has aero spike nozzle

摘要

The rocket engine has a thrust chamber (20) and a pump unit (30), where the thrust chamber is supplied to a fuel component by the pump unit, in which the thrust chamber has an aero spike nozzle (3). The aero spike nozzle is connected downstream to a turbine (7) of the pump unit. The turbine is driven in the operation of the thrust chamber by combustion gases released in the operation of the aero spike nozzle. The pump unit has a pump (4), particularly an oxidant pump.