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针对燃气自增压混合火箭发动机,建立了性能计算模型,对该型发动机的比冲性能及推力调节性能进行了研究,并系统梳理了该型发动机存在的主要关键技术。计算结果表明,燃气混合火箭发动机具有比常规固体火箭发动机更高的比冲性能,其中氧化剂采用N2O时,可同时兼顾高比冲和高体积比冲的优势;相对于传统的固液混合火箭发动机,燃气混合火箭发动机的理论比冲略低,但具有更高的体积比冲;合理选用燃气发生器中推进剂的燃速压力指数,可确保推力调节过程中氧燃比不发生大幅变化。
Aiming at the gas self-supercharging hybrid rocket engine, a performance calculation model is established, and the specific impulse performance and thrust adjustment performance of the engine are studied. The key technologies of the engine are also systematically reviewed. The calculation results show that the gas-mixing rocket engine has higher specific-impulse performance than the conventional solid rocket motor. When using N2O as the oxidizer, the advantages of high specific impulse and high volume ratio impulse can be taken into account. Compared with the conventional solid-liquid hybrid rocket engine , The theory of gas-mixing rocket engine is lower than the theory of impulse but with a higher volume ratio impulse; reasonably selecting the burning rate pressure index of the propellant in the gas generator can ensure that the oxygen to fuel ratio does not change greatly during the thrust adjusting process.