北京航空航天大学学报 ›› 2019, Vol. 45 ›› Issue (11): 2257-2265.doi: 10.13700/j.bh.1001-5965.2019.0165

• 论文 • 上一篇    下一篇

基于自适应伪谱法的高超声速飞行器再入轨迹优化

任鹏飞, 王洪波, 周国峰   

  1. 中国运载火箭技术研究院, 北京 100076
  • 收稿日期:2019-04-15 出版日期:2019-11-20 发布日期:2019-11-30
  • 通讯作者: 王洪波.E-mail:caltwang2017@126.com E-mail:caltwang2017@126.com
  • 作者简介:任鹏飞 男,硕士研究生。主要研究方向:飞行器设计;王洪波 男,博士,研究员,博士生导师。主要研究方向:飞行器设计;周国峰 男,博士,研究员。主要研究方向:飞行器设计。

Reentry trajectory optimization for hypersonic vehicle based on adaptive pseudospectral method

REN Pengfei, WANG Hongbo, ZHOU Guofeng   

  1. China Academy of Launch Vehicle Technology, Beijing 100076, China
  • Received:2019-04-15 Online:2019-11-20 Published:2019-11-30

摘要: 针对高超声速飞行器再入轨迹优化问题,建立考虑地球自转的三自由度再入运动方程,以美国通用空天飞行器为对象建立再入约束模型。采用Legendre-Gauss-Radau配点对3种典型优化问题:最大纵程、最大横程及最小航迹角变化率问题进行离散,将连续时间最优控制问题转化为非线性规划问题。基于Legendre多项式近似理论,引入衰减系数构建相对误差估计关系式,并以此提出一种有效的自适应网格重构策略。最终获得了3种典型再入轨迹优化问题的最优解。仿真结果表明,该算法的求解结果与变步长Runge-Kutta-Fehlberg法积分一致。相比传统自适应伪谱法,其配点和区间分配更合理,迭代次数少,求解速度高,且对人工参数不敏感。

关键词: 高超声速飞行器, 复杂约束, 轨迹优化, 自适应伪谱法, Legendre系数

Abstract: In order to solve the reentry trajectory optimization for hypersonic vehicle, a three-degree-of-freedom reentry kinematic equation considering the earth rotation was established, and a reentry constraint model was built, which took America's universal space vehicle as the object. Firstly, Legendre-Gauss-Radau points were employed to transform the continuous-time optimal control problem into a nonlinear programming problem, and three typical optimization problems including maximum downrange, maximum crossrange and minimum change rate of path angle were discretized. Secondly, an estimation relational expression of relative error relying on decay rate of Legendre polynomial approximation was established, and an effective adaptive mesh refinement strategy was proposed. Finally, three typical reentry trajectory optimization problems were well solved. The simulation results show that the result solved by the proposed method is consistent with the integral of variable-step-size Runge-Kutta-Fehlberg method. Compared to the traditional adaptive pseudospectral method, the proposed method achieves more reasonable mesh refinement, less mesh iteration numbers, faster computation speed and less sensitivity to the user-specified parameters.

Key words: hypersonic vehicle, complex constraints, trajectory optimization, adaptive pseudospectral method, Legendre coefficient

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