燃气自增压混合火箭发动机特性及关键技术分析

Characteristics and key techniques of gas self-pressurization hybrid rocket motor

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。

Computation model was developed and the specific impulse and thrust regulation characteristics were studied for gas self-pressurization hybrid rocket motor.The key techniques were also discussed in this paper.The results show that, the specific im- pulse of gas hybrid rocket is higher than that of common solid rocket motor and the volumetric specific impulse is also higher with N20 as the oxidizer;the volumetric specific impulse is higher than that of classical hybrid rocket motor, although the theoretical specific impulse is a bit lower;the mass flow rate ratio of oxidizer to fuel has a little change with proper buming-rate pressure exponent of the propellant.