基于滑模控制的高升阻比飞行器协同制导方法  

Cooperative guidance method of high lift-to-drag ratio aircraftbased on sliding mode control

作　　者：郭博 铁鸣 范文慧[2] 李传旭 GUO Bo;TIE Ming;FAN Wenhui;LI Chuanxu(Science and Technology on Space Physics Laboratory,Beijing 100076,China;Department of Automation,Tsinghua University,Beijing 100084,China)

机构地区：[1]空间物理重点实验室,北京100076 [2]清华大学自动化系,北京100084

出　　处：《系统工程与电子技术》2025年第2期580-590,共11页Systems Engineering and Electronics

摘　　要：针对多个高升阻比飞行器在飞行中间段的时间协同问题,提出一种基于滑模控制的高升阻比飞行器协同制导方法,建立多个高升阻比飞行器协同飞行力学模型,设计规划飞行器在中间段制导过程中的飞行程序与针对飞行器侧向机动的滑模控制策略。通过设计标称轨迹,对控制参数进行优化,进而生成各个飞行器不同初始条件所需的侧向过载并通过侧向过载得到所需的倾侧角指令,以实现对飞行器飞行时间的控制,从而使多飞行器能够同时到达目标点上方设定范围;考虑飞行器始末条件和状态约束,使飞行器能够满足协同任务需求。利用李雅普诺夫稳定性判据证明系统的稳定性以及滑模面非奇异性,仿真结果表明,该协同制导策略具备一定抗干扰性,能够满足异地非同步发射的多个飞行器协同制导需求。Aiming at the problem of time coordination of multiple high-lift-to-drag ratio aircrafts in mid-flight,a cooperative guidance method of high-lift-to-drag ratio aircraft based on sliding mode control is proposed.A cooperative flight mechanics model of multiple lift-to-drag ratio aircrafts is established,and the flight program of the aircraft in mid-flight guidance and the sliding mode control strategy for lateral maneuvering of the aircraft are designed and planned.By designing nominal trajectories,the control parameters are optimized to generate the lateral overload required by different initial conditions of each aircraft and obtain the required tilt angle command through the lateral overload,so as to control the flight time of the aircraft,so that multiple aircrafts can reach the set range above the target point at the same time,and consider the starting and ending conditions and state constraints of the aircraft,enabling the aircraft to meet collaborative mission requirements.Lyapunov stability criterion is used to prove the stability of the system and the non-singularity of the sliding mode surface.Simulation results show that the cooperative guidance strategy has a certain anti-interference property,and can meet the requirements of the cooperative guidance of multiple aircrafts launched asynchronously.

关 键 词：高升阻比飞行器 协同制导 滑模控制 参数优化 稳定性 

分 类 号：V448.232[航空宇航科学与技术—飞行器设计]