亚轨道飞行器任务中止再入轨迹优化设计

Mission Abort Re-entry Trajectory Optimization of Suborbital Reusable Launch Vehicle

针对亚轨道飞行器上升段由于动力故障任务中止时再入返回的问题,考虑飞行模型简化和故障后的燃料处理方案,通过遗传算法优化设计最优返回轨迹,优化时选取经向飞行航程最远作为性能指标,并采用遗传算法,解决用于再入轨迹优化所涉及的关键问题,并进行仿真。仿真结果表明,方法不但满足飞行器返回过程中加热率、过载、动压约束以及终端状态约束,能够通过飞行航程最远消耗飞行器能量从而安全着陆,而且可以较快地搜索到全局最优解,能够用于亚轨道飞行器故障再入轨迹的优化设计。

Considering the mission abort of engine failure during the ascent stage of Suborbital Reusable Launch Vehicle, the simple model and the failure project, genetic algorithms is used to design the optimal reentry trajectory, the longitudinal flight range is defined as the performance index, and some key problems such as parameterized method are discussed in detail. Simulation results demonstrate that not only the designed reentry trajectory satisfies various constraints such as overload, heat rate, dynamic pressure and the boundary constraints, the optimal trajectory maximizes flight range and a safe landing can be reached, but also the optimization results can be obtained faster. The genetic algorithms of Suborbital Reusable Launch Vehicle can be used to design optimization reentry trajectory.