固体火箭发动机流量调节半实物仿真系统

摘要

A pressure sensitive propellant is used in the choked solid rocket ramjet gas generator. Then the gas production rate can be adjusted by changing the nozzle throat area. The control algorithm of gas generator pressure closed loop is complex as the time varying characteristic of controlled member. So it is necessary to debug controller repeated. But as the restriction of experiment condition, firing run can' t be done repeated. In order to design the controller effectively and complete the test of controller and driver, a semi-physical simulation system is designed. Through semi-physical simulation experiment, solid rocket ramjet gas generator pressure closed loop characteristic is tested. According to the result, pressure closed loop controller design method is analyzed.%壅塞式燃气发生器利用燃速对压力敏感的推进剂,通过调节喷管喉部面积来达到调节燃气流量生成率的目的.由于控制对象的时变性,燃气发生器压力闭环控制算法比较复杂,控制实际应用时需要反复调试,但是由于试验条件的限制,无法多次进行点火试验或在点火试验过程中进行调试.为了能够有效的实现控制器的设计、完成对流量可调燃气发生器驱动控制装置的测试、提高点火试验的安全性,提出一套半实物仿真方案,可以实现对流量可调燃气发生器驱动控制装置的冷调试验.在此基础上,对固体火箭发动机流量可调燃气发生器压力闭环控制系统进行了半实物仿真,并针对仿真结果给出了压力闭环控制器设计的方法.