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

作　　者：安通 王鹏[2] 王建华 汤国建[2] 潘玉龙[1] 陈海山[1] AN Tong;WANG Peng;WANG Jianhua;TANG Guojian;PAN Yulong;CHEN Haishan(Air Force Early Warning Academy,Wuhan 430019,China;College of Aerospace Science,National University of Defense Technology,Changsha 410073,China;Department of Aerospace Science and Technology,Space Engineering University,Beijing 101400,China)

机构地区：[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

出　　处：《系统工程与电子技术》2022年第3期956-966,共11页Systems Engineering and Electronics

基　　金：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)资助课题。

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。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.

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 

分 类 号：V448[航空宇航科学与技术—飞行器设计]