弹性高超声速飞行器动态面制导控制一体化设计方法

doi:10.12305/j.issn.1001-506X.2022.03.28

系统工程与电子技术 ›› 2022, Vol. 44 ›› Issue (3): 956-966.doi: 10.12305/j.issn.1001-506X.2022.03.28

弹性高超声速飞行器动态面制导控制一体化设计方法

安通¹, 王鹏^2,*, 王建华³, 汤国建², 潘玉龙¹, 陈海山¹

1. 空军预警学院, 湖北武汉 430019
2. 国防科技大学空天科学学院, 湖南长沙 410073
3. 航天工程大学宇航科学与技术系, 北京 101400

收稿日期:2021-04-02 出版日期:2022-03-01 发布日期:2022-03-10
通讯作者: 王鹏
作者简介:安通 (1993—), 男, 讲师, 硕士, 主要研究方向为飞行器制导与控制|王鹏 (1984—), 男, 教授, 博士, 主要研究方向为飞行器导航、制导与控制|王建华 (1988—), 男, 讲师, 博士, 主要研究方向为飞行动力学、制导与控制|汤国建 (1964—), 男, 教授, 博士, 主要研究方向为高超声速飞行器动力学、制导与控制|潘玉龙 (1978—), 男, 讲师, 博士, 主要研究方向为动力工程|陈海山 (1976—), 男, 讲师, 本科, 主要研究方向为动力工程
基金资助:
国家自然科学基金(61903379);激光推进及其应用国家重点实验室基础研究项目(SKLLPA-14)

Integrated guidance and control schemes for dynamic surface of flexible hypersonic vehicles

Tong AN¹, Peng WANG^2,*, Jianhua WANG³, Guojian TANG², Yulong PAN¹, Haishan CHEN¹

1. Air Force Early Warning Academy, Wuhan 430019, China
2. College of Aerospace Science, National University of Defense Technology, Changsha 410073, China
3. Department of Aerospace Science and Technology, Space Engineering University, Beijing 101400, China

Received:2021-04-02 Online:2022-03-01 Published:2022-03-10
Contact: Peng WANG

摘要/Abstract

摘要：

面向弹性高超声速飞行器滑翔段制导控制系统设计问题, 应用动态面控制理论设计了两种制导控制一体化方法。建立了弹性高超声速飞行器滑翔段纵向运动模型, 并推导了具有严格反馈形式的弹性高超声速飞行器制导控制一体化设计模型。将弹性状态视为不确定项, 分别基于自适应方法和非线性干扰观测器(nonlinear disturbance observer, NDO), 开展动态面制导控制一体化系统设计, 并基于Lyapunov定理证明了系统的稳定性。在标称状态下和参数偏差状态下开展仿真试验, 验证了两种制导控制一体化方法的有效性和鲁棒性, 并进一步分析了两种制导控制一体化方法的性能差异及其原因。

关键词: 弹性高超声速飞行器, 动态面, 制导控制一体化, 自适应, 非线性干扰观测器

Abstract:

Two integrated guidance and control methods based on dynamic surface control theory are designed for flexible hypersonic vehicles in glide phase. The longitude translational and rotational equations of flexible hypersonic vehicles in glide phase are denoted. A strict-feedback integrated guidance and control design model for flexible hypersonic vehicles is deduced. The flexible states of the hypersonic vehicle are regarded as uncertainties. Two integrated guidance and control schemes are proposed based on adaptive approach and nonlinear disturbance observer (NDO) technique, respectively. The states of the closed-loop systems are proved to be uniformly ultimately bounded based on Lyapunov stability theorem. Simulation experiments are conducted to verify the effectiveness and robustness of the proposed schemes. The performance differences between the two schemes and the reasons behind are analyzed further.

Key words: flexible hypersonic vehicle, dynamic surface control method, integrated guidance and control, adaptive approach, nonlinear disturbance observer (NDO)

中图分类号:

V448

安通, 王鹏, 王建华, 汤国建, 潘玉龙, 陈海山. 弹性高超声速飞行器动态面制导控制一体化设计方法[J]. 系统工程与电子技术, 2022, 44(3): 956-966.

Tong AN, Peng WANG, Jianhua WANG, Guojian TANG, Yulong PAN, Haishan CHEN. Integrated guidance and control schemes for dynamic surface of flexible hypersonic vehicles[J]. Systems Engineering and Electronics, 2022, 44(3): 956-966.

图/表 11

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IGC方法	设计参数
自适应	k₁=k₂=2 k₃=8	τ₂=τ₃=0.5	ε₁=ε₂=ε₃=10 σ₁=σ₂=σ₃=1
NDO	${\bar k}$₁=${\bar k}$₂=2 ${\bar k}$₃=8	τ₂=τ₃=0.5	l₁=0.7 l₂=l₃=0.5

编号	参数偏差组合	标识线型	脱靶量/m
编号	参数偏差组合	标识线型	自适应	NDO
①	ρ+30% C_L、C_D+20%, m_z+20%	红色实线	0.52	1.00
②	ρ+30% C_L、C_D+20%, m_z-20%	绿色虚线	1.73	0.53
③	ρ+30%, C_L、C_D-20%, m_z-20%	蓝色点线	1.76	3.21
④	ρ+30%, C_L、C_D-20%, m_z+20%	橙色短点线	2.53	2.61
⑤	ρ-30% C_L、C_D+20% m_z+20%	□形红色实线	1.66	8.66
⑥	ρ-30%, C_L、C_D+20%, m_z-20%	○形绿色虚线	0.96	12.72
⑦	ρ-30%, C_L、C_D-20%, m_z-20%	△形蓝色点线	12 449.77	39.32
⑧	ρ-30%, C_L、C_D-20% m_z+20%	◇形橙色短点线	12 430.97	34.72

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弹性高超声速飞行器动态面制导控制一体化设计方法

Integrated guidance and control schemes for dynamic surface of flexible hypersonic vehicles

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