The invention discloses a planet landing guidance method for optimal control and rapid search, and belongs to the technical field of spacecraft guidance and control. The implementation method comprises the following steps: decoupling a lander dynamics model into a controlled dynamics model and an uncontrolled dynamics model; constructing an optimization model of the reachable region by taking thrust amplitude constraint and thrust direction constraint as constraint conditions, and solving a controlled motion reachable region in a prediction time domain; taking different positions in the reachable area as virtual end points, constructing a burn-up optimization model, performing off-line optimization to obtain burn-up optimal control of the lander arriving at the specified virtual end point position, storing the optimal control as an optimal control database, and storing the corresponding virtual end point state as an end point state database; in the landing process, the uncontrolled motion and the end point state database are superposed, the state prediction space of the lander is obtained, the optimal terminal state is searched, a corresponding optimal control instruction in the optimal control database is obtained, and planet landing guidance is achieved according to the optimal control instruction.
本发明公开的最优控制快速搜索的行星着陆制导方法,属于航天器制导与控制技术领域。本发明实现方法为:将着陆器动力学模型解耦为有控动力学模型和无控动力学模型;以推力幅值约束和推力方向约束为约束条件构建可达区的优化模型,求解一个预测时域内的有控运动可达区;以可达区内不同位置为虚拟终点,构建燃耗优化模型,离线优化获得着陆器抵达指定虚拟终点位置的燃耗最优控制,将最优控制存储为最优控制数据库,将对应的虚拟终点状态存储为终点状态数据库;在着陆过程中将无控运动与终点状态数据库进行叠加,得到着陆器的状态预测空间,搜索最优终端状态,得到最优控制数据库中对应的最优控制指令,根据最优控制指令实现行星着陆制导。
Planetary landing guidance method for optimal control and rapid search
最优控制快速搜索的行星着陆制导方法
2024-04-19
Patent
Electronic Resource
Chinese