试验飞行器Max-Max类再入轨迹优化的序列差凸规划方法
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中山大学航空航天学院

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V249

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跨域飞行交叉技术实验室(2024-KF02201)


Max-Max Type Entry Trajectory Optimization for Testing Vehicle by Successive Difference-of-Convex Programming
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    摘要:

    靶场试验前,利用轨迹优化方法对飞行器的极端边界进行模拟是一项有效仿真手段。采用差凸(Difference-of-Convex,DC)规划方法,对试验再入飞行器在峰值热流密度方面的极端性能进行研究。通过DC分解方法对热流、动压和过载约束进行处理,将其分解思路推广到对Max-Max类代价函数,如峰值热流、峰值动压和峰值过载等。采用大-法将原问题转为混合整数非线性规划子问题,将凹凸分解和罚函数相结合,解决迭代过程中代价函数的振荡不收敛问题,并提出基于DC松弛模型的改进序列DC规划算法。数值实验表明基于DC松弛模型比传统直接线性化的近似精度要高,且提出的算法具有较高的数值稳定性,算法鲁棒性和代价函数最优性。

    Abstract:

    Simulating the extreme boundaries of the entry vehicle using trajectory optimization methods is an effective simulation method before the range test. The Difference-of-Convex (DC) programming method was employed to study the extreme performance of the testing entry vehicle in terms of peak heat flux. The DC decomposition method was utilized to handle constraints such as heat flux, dynamic pressure, and nomal load, and this method was extended to Max-Max type cost functions, such as peak heat flux, peak dynamic pressure, and peak normal load. The Big-M method was adopted to transform the primal problem into a mixed-integer nonlinear programming sub-problem, combining concave-convex decomposition with penalty function technique to address the oscillation and non-convergence issues for the cost function during the iteration process. An improved successive DC programming algorithm based on the DC relaxation model was proposed. Numerical experiments show that the DC relaxation model-based approach has higher approximation accuracy than traditional direct linearization methods, and the proposed algorithm demonstrates high numerical stability, robustness, and optimality of the cost function.

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  • 收稿日期:2025-01-14
  • 最后修改日期:2025-04-20
  • 录用日期:2025-04-21
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