| 摘要 |
The invention relates to a method for operating a rocket engine, which method makes it possible to provide single-stage carrier rockets that achieve an optimal thrust and a maximum specific impulse over the combustion duration of the engine. The invention further relates to a rocket engine that allows the method according to the invention to be carried out. In the method according to the invention, at least one hydrocarbon is reacted with oxygen in a first combustion chamber of the rocket engine and hydrogen is reacted with oxygen in a second combustion chamber of the rocket engine. The reaction in the first combustion chamber is maintained until the hydrocarbon is consumed; the reaction in the second combustion chamber is continued until the hydrogen is consumed. The fuel amounts are selected so that the hydrocarbon is consumed earlier than the hydrogen. The rocket engine, designed as a plug nozzle engine, for carrying out the method comprises a main body (1), at the lower end of which a central cone (2) (plug nozzle/spike) is connected, wherein the main body (1) is surrounded by a first annular combustion chamber (3.1), which has a first annular throat nozzle (6.1), and a second annular combustion chamber (3.2) having a second annular throat nozzle (6.2) is located in the central cone (2). |
