固体火箭冲压发动机燃气流量调节的负调现象

摘要

研究了可变流量固体火箭冲压发动机所存在的燃气流量负调现象，分析了负调现象产生的机理是由于燃气发生器压强的变化过程滞后于喷嘴面积的变化过程。基于燃气发生器动态工作模型，以某型固体火箭冲压发动机为例，通过仿真分析研究了燃气发生器空腔容积和燃气阀门调节速度对负调过程的影响：当燃气发生器空腔长度为0．1 m、阀门调节时间分别为0 s和2 s时，对应的燃气负调量为82．6％和1．7％、响应时间为0．21 s和1．76 s；当燃气发生器空腔长度为0．8 m、阀门调节时间分别为0 s和2 s时，对应的燃气负调量为82．6％和11．4％、响应时间为1．69 s和2．85 s。基于上述分析结果，还提出了减小固体火箭冲压发动机燃气流量负调程度的措施。%The flow negative regulation characteristics due to the delay between the pressure variation of gas generator and the area variation of fuel valve for the solid propellant variable flow ducted rocket(SPVFDR)was analyzed in this paper.The influence of the gas generator cavity volume and the gas valve rate on the negative regulation in a SPVFDR was investigated using numerical sim⁃ulation based on the gas generator dynamic model.The results show that:the negative regulations are 82.6% and 1.7% and the re⁃sponse time is 0.21 s and 1.76 s when the gas generator cavity length is 0.1 m and the regulation time is 0 s and 2 s.The negative regulation are 82.6% and 11.4% and the response time is 1.69 s and 2.85 s when the gas generator cavity length is 0.8 m and the regulation time is 0 s and 2 s.Based on the results,this paper brings forward the methods to reduce SPVFDR flow negative regula⁃tion.