摘要
以采用低温液氧/煤油补燃循环发动机的某运载火箭为研究对象,根据动量方程、能量方程和质量守恒方程,用模块化方法建立了补燃循环发动机特有的燃气发生器、涡轮、燃气导管和气-液型推力室的传递矩阵模型,基于Nyquist判据建立了全箭纵向耦合振动(POGO)稳定性分析模型。用新模型分析了该运载火箭的POGO稳定性,确定了蓄压器pV值设计要求为0.4MPa·L。飞行试验考核表明:整个飞行中未发生POGO振动,理论分析结论与飞行试验结论一致,稳定性分析模型合理可靠,可用于后续采用低温液氧/煤油补燃循环发动机火箭的POGO稳定性分析。
Based on the launch vehicle of LOX（liquid oxygen）/kerosene staged combustion cycle engine,the transfer matrix models for gas generator,turbo,gas pipe and combustion chamber of LOX/kerosene staged combustion cycle engine were developed by modular modeling method and the model for POGO stability analysis of launch vehicle based on Nyquist principle was established.The model proposed had been applied in the simulation of POGO vibration and the pVvalue of accumulator had been decided which was 0.4MPa·L.The result of fly test showed that there was no POGO vibration in the flight.It meant that the results of the simulation could give the precise stability analysis of POGO vibration and the model of POGO stability analysis was reliable,which could be used to analysis of POGO stability for the future launch vehicles of LOX/kerosene staged combustion cycle engine.
出处
《上海航天》
2016年第B05期36-42,共7页
Aerospace Shanghai
