The invention discloses a fault-tolerant control distribution method for RCS torque output in the initial stage of reentry of an aerospace vehicle, and belongs to the field of aerospace. The implementation method comprises the following steps: establishing kinetic equations under a north-sky-east coordinate system and a body coordinate system to obtain an aircraft reentry initial attitude kinetic equation containing the influence of actual earth rotation angular velocity; rCS torque output characteristics are analyzed, and a reverse thrust acting force and torque model generated by the RCS spray pipe is established. And establishing an RCS control torque distribution model, obtaining an actual switching instruction of the RCS nozzle in a manner of solving the opening time of the nozzle in a fixed time through pseudo-inverse, and controlling the attitude of the aircraft to be stable. On the basis of a look-up table method, a limited number of RCS nozzles are utilized, a switching instruction of the nozzles is obtained in a manner of decoupling and uniformly distributing expected torque of a controller step by step, the aircraft performs attitude adjustment through actual output torque obtained by the RCS switching control instruction, the attitude control robustness of the aerospace aircraft is improved, and the application range of the aircraft type is expanded.
本发明公开的空天飞行器再入段初期RCS力矩输出的容错控制分配方法,属于航空航天领域。本发明实现方法为:建立在北天东坐标系以及机体坐标系下的动力学方程,得到包含实际地球自转角速度影响下的飞行器再入段初期姿态动力学方程。分析RCS力矩输出特性,建立RCS喷管产生的反推作用力和力矩模型。建立关于RCS控制力矩分配模型,通过伪逆求解固定时间内该喷管开启时间的方式获得RCS喷管的实际开关指令,控制飞行器姿态稳定。基于查表法利用有限数量的RCS喷管,通过分步解耦统一分配控制器期望力矩的方式获得喷管的开关指令,飞行器通过RCS开关控制指令获取的实际输出力矩进行姿态调节,提高空天飞行器姿态控制鲁棒性,扩大飞行器类型的适用范围。
Fault-tolerant control distribution method for RCS torque output at initial stage of reentry of aerospace vehicle
空天飞行器再入段初期RCS力矩输出的容错控制分配方法
2023-10-03
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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