| 摘要 |
Method for the operation of a bypass flow rocket engine running on liquid oxygen and hydrogen, which functions both as a surface engine and as a high altitude engine, with a main combustion chamber, to which in each case the same quantities of liquid oxygen and hydrogen are directly fed during surface operation and during operation at high altitudes in a mass ratio of oxygen to hydrogen of approximately 6:1, the main combustion chamber during surface operation being additionally charged with oxygen-rich gases produced in the precombustion chamber in a mass ratio of oxygen to hydrogen of approximately 20:1, so that during surface operation the main combustion chamber functions with a mass ratio of oxygen to hydrogen of approximately 13:1. For operation at high altitudes the precombustion chamber is switched off.
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