高超变体飞行器内点约束最小值原理突防制导

doi:10.12305/j.issn.1001-506X.2026.08.27

摘要/Abstract

摘要：

当具有可变后掠翼的高超声速滑翔飞行器攻击目标时，考虑末制导阶段存在防御弹拦截情况，设计了一种基于内点约束最小值原理的制导方法和基于事件触发的变外形切换策略。建立半速度系下突防模型；将防御弹的脱靶量视为攻击弹飞行过程的内点约束，利用最小值原理分析并求解最优加速度；利用事件触发原理，求解优化算法控制量对应的最优飞行器外形和所需攻角、倾侧角。仿真结果表明，该制导方法能够实现变体飞行器规避拦截弹对目标打击，切换器能够实现提升落速的外形最优切换，表明了算法的有效性，并通过蒙特卡罗仿真验证了算法的鲁棒性。

关键词: 高超变体飞行器, 防御弹拦截, 最小值原理, 内点约束, 事件触发原理

Abstract:

When a hypersonic gliding vehicle with a variable-sweep wing attacks a target, considering the possibility of interception by a defense missile during the terminal guidance phase, a guidance method based on the minimum value principle with interior point constraints and a variable-shape switching strategy based on event-triggered mechanisms are designed. A penetration model under half-speed conditions is established. The miss distance of the defense missile is treated as an interior point constraint during the attack missile’s flight process. And the optimal acceleration is analyzed and solved using the minimum value principle. Using the event-triggered principle, the optimal vehicle shape, required attack angle, and sideslip angle corresponding to the control quantities of the optimization algorithm are solved. Simulation results show that the guidance method can help the variant vehicle evade interception by the defense missile, and the switcher can achieve the optimal shape switch that enhances the landing speed, demonstrating the effectiveness of the algorithm, which is further verified for robustness through Monte Carlo simulations.

Key words: hypersonic morphing vehicle, defense missile, minimum principle, interior point constraint, event triggering principle

中图分类号:

TJ 765.3

姚冬冬, 周江华, 夏群利, 谢佳文. 高超变体飞行器内点约束最小值原理突防制导[J]. 系统工程与电子技术, 2026, 48(8): 2821-2832.

Dongdong YAO, Jianghua ZHOU, Qunli XIA, Jiawen XIE. Minimum principle penetration guidance for hypersonic morphing vehicle with interior point constraints[J]. Systems Engineering and Electronics, 2026, 48(8): 2821-2832.

图/表 22

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参数	Case1	Case2	Case3
效率/s	0.734	0.504	0.407
拦截规避	是	否	否
飞行时间/s	111.3	109	111.6
落角/（°）	−13	−20	−8.7
落速/（m/s）	1460	1405	1270