高比冲小推力脉冲爆震火箭发动机特性研究

Characteristics of Pulse Detonation Rocket Engine with High Specific Impulse and Small Thrust Demand

在轨快速机动与姿态调整问题成为近年来航天领域的研究热点之一,这一问题推动了高比冲小推力化学燃料发动机的发展.基于爆震燃烧的脉冲爆震火箭发动机,具有热效率高、比冲高、结构简单等特点.本文针对脉冲爆震火箭发动机开展了关键性能研究,首先给出爆震燃烧的数学物理模型,介绍了等容循环模型分析方法;然后将爆震波数值仿真结果与理论计算结果进行了对比,验证了所用模型与算法的合理性;最后采用数值仿真方法对不同外界气体工质、喷管构型、环境压力下发动机内流场特性及发动机性能参数进行了研究;结果分析表明脉冲爆震火箭发动机具备高比冲、小推力特性,其中收敛扩张型喷管对发动机性能增益最大,且随着环境压力降低,发动机推力增大.

The problem of continuous thrust orbit transfer has become one of the research hotspots in the aerospace field in recent years.This problem has also promoted the development of high specific impulse and small thrust engines.The pulse detonation engine based on detonation combustion has the characteristics of high thermal efficiency,high specific impulse and simple structure.The related performance research is carried out.First,the mathematical model of the detonation technology is given,and the analysis method of the equal volume cycle model is introduced.Then the numerical results of the CEA model and the simulation results are compared to verify the reliability of the designed detonation model.And different external gas working fluids,nozzle configurations,and respective simulation analysis of engine internal flow field and performance analysis are carried out under 0.1atm,0.01atm,0.001atm ambient pressure.The result analysis shows that the pulse detonation engine can meet the requirements of high specific impulse and small thrust,and the convergent expansion nozzle has the greatest gain in engine performance.As the ambient pressure decreases,the engine thrust increases.