高超声速飞行器俯冲段多约束蛇形机动喘振制导控制集成设计

IF 0.1 4区 工程技术 Q4 ENGINEERING, AEROSPACE
Xiaojun Yu, Shi-shi Luo, Haiqiao Liu
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引用次数: 0

摘要

针对高超声速滑翔飞行器具有多约束和不确定干扰的大机动突防问题,设计了一种能实现蛇形机动的鲁棒综合制导控制律。讨论了在正弦函数框架下,由高度、瞄准线目标赤角和弹靶距离决定的蛇形机动加速度指令。综合制导控制律包括多约束末制导律、姿态控制律和角速度控制律。在末制导律设计中,采用滑模控制,采用自适应技术对扰动进行估计。所选的滑模表面具有可变增益,由估计的剩余时间决定。采用所设计的末制导律,以蛇形机动加速指令为偏置项,使瞄准线角速度收敛于零,同时使瞄准线角度收敛于期望值。设计了姿态控制律和角速度控制律来跟踪预期攻角和预期倾斜角。应用李亚普诺夫定理证明了整个系统的稳定性。仿真结果验证了该制导控制律的有效性和鲁棒性。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Integrated Design of Multi-Constrained Snake Maneuver Surge Guidance Control for Hypersonic Vehicles in the Dive Segment
Focusing on the large maneuver penetration of the hypersonic glide vehicle with multiple constraints and uncertain disturbance, a robust integrated guidance and control law, which can achieve the snake-shape maneuver, is designed. A snake-shape maneuver acceleration command, in the framework of sine function, determined by the altitude, target declination of the line of sight and the missile-target distance, is discussed. The integrated guidance and control law includes the terminal guidance law with multiple constraints, attitude control law and angular velocity control law. In the terminal guidance law design, the sliding mode control is adopted while the adaptive technique is applied to estimate the disturbance. The selected sliding mode surface has variable gain determined by the estimated time-to-go. With the designed terminal guidance law, using the snake-shape maneuver acceleration command as the bias item, the angular rate of the line of sight will converge to zero and the line of sight angle will converge to the expected value, simultaneously. The attitude control law and angular velocity control law are designed to track the expected attack and bank angles. The stability of the whole system is proved with the application of the Lyapunov theorem. The effectiveness and robustness of the proposed integrated guidance and control law is verified by simulation.
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来源期刊
Aerospace America
Aerospace America 工程技术-工程:宇航
自引率
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发文量
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审稿时长
4-8 weeks
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