The invention provides a closed-loop guidance method for a rocket sublevel recovery power decline stage, relates to a rocket guidance recovery method, fully considers the effect of nonlinear aerodynamic force, solves the PDG problem considering the nonlinear aerodynamic force through a terminal error method to perform trajectory planning, and can realize the optimal recovery of the nonlinear aerodynamic force at feasible calculation cost. The effect of nonlinear aerodynamic force is fully considered in each time of trajectory planning; moreover, the trajectory planning success rate is high, and the reasons for improving the trajectory planning success rate are as follows: 1, the planning times which can be tried are increased due to the acceleration of single planning, the planning success rate can be improved, and errors can be corrected in time; 2, a plurality of cores of the rocket-borne processor can be utilized to run the planning of cold start and hot start in parallel, and the number of attempts is also increased; and 3, the planning initial time point delay is reduced, so that the initial state prediction error is reduced.
本发明提供的火箭子级回收动力下降阶段闭环制导方法,涉及火箭制导回收方法,充分考虑非线性气动力的作用,通过末端误差法求解考虑非线性气动力的PDG问题进行轨迹规划,能够以可行的计算代价,在每次轨迹规划内部充分考虑非线性气动力的作用;并且轨迹规划成功率高,提高轨迹规划成功率的原因主要有:1.单次规划的加速使得可尝试的规划次数增加,能够提升规划成功率,并及时修正误差;2.能够利用箭载处理器的多个核心,并行运行冷启动和热启动的规划,也增加了尝试次数;3.降低了规划初始时间点延迟,从而降低了初始状态预测误差。
Closed-loop guidance method for rocket sub-stage recovery power descending stage
火箭子级回收动力下降阶段闭环制导方法
2023-10-27
Patent
Elektronische Ressource
Chinesisch
IPC: | B64G Raumfahrt , COSMONAUTICS |
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