The invention discloses a rocket power landing phase guidance control method, system and device and a medium, and relates to the technical field of rocket guidance recovery. The method comprises the following steps: in a current control period, obtaining a state quantity according to a control parameter and a rocket power landing section motion model; taking the minimum guidance control comprehensive target mathematical model as a target, and updating the to-be-adjusted parameter value according to the parameter updating period and the state quantity; according to the guidance cycle, the updated partial to-be-adjusted parameter values, partial parameters in the state quantity, the flight time and the guidance model, a thrust amplitude and a channel expected attitude are obtained; and according to the attitude control period, the updated part of parameter values to be adjusted, the attitude, the attitude angular rate, the thrust amplitude, the channel expected attitude and the attitude control model, obtaining a channel engine swing angle, and entering the next control period for control. According to the method, the problems of low terminal constraint satisfaction precision, fuel consumption loss, poor attitude control quality and the like can be solved, and the reliability of recoverable rocket power landing is improved.
本发明公开一种火箭动力着陆段制导控制方法、系统、设备及介质,涉及火箭制导回收技术领域。所述方法包括:在当前控制周期内,根据控制参数以及火箭动力着陆段运动模型得到状态量;以制导控制综合目标数学模型最小为目标,根据参数更新周期、状态量对待调节参数值进行更新;根据制导周期、更新后的部分待调节参数值、状态量中部分参数、飞行时间以及制导模型得到推力幅值和通道期望姿态;根据姿态控制周期、更新后的部分待调节参数值、姿态、姿态角速率、推力幅值、通道期望姿态以及姿态控制模型得到通道发动机摆角,进入下一控制周期控制。本发明可解决终端约束满足精度低、燃料消耗损失以及姿态控制品质差等问题,提高可回收火箭动力着陆的可靠性。
Rocket power landing phase guidance control method, system, equipment and medium
一种火箭动力着陆段制导控制方法、系统、设备及介质
2025-03-28
Patent
Electronic Resource
Chinese
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