固体推进剂空气涡轮火箭发动机的非设计点性能研究

Research on off-design performance of solid propellant air-turbo-rocket

为了简化控制系统和节流装置,采用涡轮进口富燃燃气流量为常数的调节计划,建立了固体推进剂空气涡轮火箭发动机(SPATR)的非设计点计算数学模型。分析了不同设计点涡轮进口富燃燃气流量对SPATR性能的影响,确立了设计点富燃燃气流量选择的方法。计算了SPATR的非设计点性能。结果表明,所建数学模型合理、可行,能满足SPATR在不同高度和速度下飞行任务的需要。

In order to simplify the control system and throttle valve, a numerical model for off-design points of solid propellant air-turbo-rocket （SPATR） was derived by using fuel-rich gas flow in turbine inlet as constant of the regulating plan. The effects of fuel-rich gas flow in different design point turbine inlet on performances of the SPATR were analyzed. The method for selecting design point fuel-rich gas flow was determined. The off-design performance of SPATR was calculated based on this model. The results indicate that the model is rational and feasible, which can meet requirements of SPATR under different altitude and velocity conditions.