| 摘要: |
| 固体火箭上升段轨迹优化设计具有重要的工程意义。针对此问题，提出了一种求解上升段最优轨迹的可行方法。在零侧滑角假设下构建飞行器模型，以推力方向为最优控制量，根据极小值原理推导一阶最优条件。采用间接法，将真空条件下上升段最优轨迹的解作为初值，以状态响应方程构造一种迭代的方法，最后在满足攻角过程约束下，通过同伦算法获得真实大气环境下的最优轨迹。仿真结果表明，该优化算法能够稳定收敛，具有良好的鲁棒性。 |
| 关键词: 固体火箭 上升段 最优控制 轨迹优化 间接法 |
| DOI： |
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| 基金项目: |
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| Indirect Method-based Ascent Trajectory Optimization |
| WU Jia-liang |
| (Beijing Electromechanical Engineering Research Institute) |
| Abstract: |
| Ascent trajectory optimization of solid rockets is important for engineering.Aiming at this problem，a feasible approach is proposed to obtain optimal ascent trajectory.Based on zero sideslip assumption to construct model，the direction of body longitudinal axis is chosen as control input.The minimum principle is used for optimization.Using indirect method，the vacuum solution is taken as initial guess，and based on state response to construct an iteration approach.With the path constraint of attack of angle，the optimal trajectory is gotten through homotopy algorithm.The results indicate that this method converges steadily and robustly. |
| Key words: Solid rockets Ascent Optimal control Trajectory optimization Indirect method |
