大推力发动机关机段干扰辨识及优化姿态控制技术

Disturbance Identification and Optimization Control Technology for High-thrust Rocket Engine Shutdown Flight

为了解决YF-75关机过程中推力及干扰与设计预示工况存在差异的问题,基于飞行数据辨识发动机关机段的推力变化历程及三通道干扰力矩,在此基础上,提出提高姿态精度的控制优化方案。地面验证试验及飞行搭载试验结果表明方案可行。根据试验结果进一步优化后的方案成功应用于CZ-3B/YZ-1、CZ-3C/YZ-1构型火箭首飞任务,显著降低关机段的姿态角速度偏差,保证了飞行任务的圆满完成,对大推力发动机关机后直接入轨进行了有益探索。

For the YF-75 rocket engine shutdown process of LM-3A series Launch Vehicle,the designed thrust and nominal disturbance torque is different from the actual flight condition.The evolution of thrust and disturbance torque for the three channels is identified based on flight data.On this base,an optimization control scheme is proposed to improve the separation attitude precision.Ground verification test and flight test results show that the scheme is feasible.According to the experimental results,the further optimized scheme has been successfully applied in the first flight tasks of CZ-3B/YZ1 and CZ-3C/YZ-1 configuration rocket,which significantly reduces the attitude angle deviation during the engine shutdown period and ensures the successful completion of the missions.The proposed control scheme is a beneficial exploration for direct-to-orbit using high-thrust engine shutdown flight.