高速变形飞行器制导控制一体化设计方法  

Integrated guidance and control method for high-speed morphing wing aircraft

作　　者：何昊 王鹏[1] HE Hao;WANG Peng(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073

出　　处：《航空学报》2024年第S1期299-312,共14页Acta Aeronautica et Astronautica Sinica

基　　金：国家自然科学基金(92371203)

摘　　要：针对高速变形飞行器制导和姿态回路耦合特性强所导致的分离设计难问题,以反步法和固定时间滑模控制方法作为基础,利用变形飞行器的变形特性,设计了一种考虑飞行器变形特性的制导控制一体化方法。首先建立了飞行器在变形条件下的六自由度完整运动模型,并推导了含有变形附加项的严格反馈形式制导控制一体化模型。随后结合反步法与固定时间滑模控制方法提出了一种新的制导控制一体化设计方法,并通过Lyapunov理论证明了系统的稳定性。最后,在不变形情况下进行了传统方法与所提出设计方法的对比,验证了新方法的快速性和有效性;在有无变形情况下进行了新方法的对比,验证了变形情况下制导控制一体化设计的优越性。The guidance and attitude loops of high-speed morphing wing aircraft has strong coupling characteristics,and are difficult to separate and design.In this paper,an Integrated Guidance and Control(IGC)method considering morphing characteristics is designed based on the Backstepping Method and the Fixed-Time Sliding Mode Control(FTSMC)method.Firstly,a six-degree-of-freedom complete kinematic model of the aircraft under morphing condi⁃tions is established,and a strict feedback form of the IGC model with additional deformation terms is derived.Sec⁃ondly,a novel integrated design method for guidance and control is proposed using the Backstepping Method(BM)combined with FTSMC,and the stability of the system is proved by the Lyapunov theory.Finally,comparison be⁃tween the traditional method and the new integrated design method is carried out in the case without morphing,which verifies the rapidity and effectiveness of the new method.Comparison of the new method with and without morphing is carried out,which verifies the superiority of the new method in the case with morphing.

关 键 词：变形飞行器 制导控制一体化 反步控制 固定时间滑模控制 标称轨迹跟踪 

分 类 号：V249[航空宇航科学与技术—飞行器设计] V448