一种基于动态逆-滑模的变形飞行器姿态控制方法研究  

A Dynamic Inverse-Sliding Mode Based Attitude Control Method for Morphing Aircraft

作　　者：郭嘉宝 赵长见[1] 宋志国[1] Guo Jiabao;Zhao Changjian;Song Zhiguo(China Academy of Launch Vehicle Technology,Beijing 100076,China)

机构地区：[1]中国运载火箭技术研究院,北京100076

出　　处：《航天控制》2022年第4期12-17,共6页Aerospace Control

摘　　要：以某高速变形飞行器作为研究对象,针对变形过程中的姿态稳定控制问题,提出了一种将非线性动态逆与滑模控制结合的姿态控制方法。文中首先建立变形飞行器的运动模型和变形过程中的气动模型;随后采用动态逆方法来解决控制输入非仿射的问题,并在动态逆控制的基础上,采用动态滑模控制补偿由于模型误差带来的系统逆误差,实现了俯仰角响应对俯仰角指令的有效跟踪;最后进行了数值仿真验证,结果表明本文设计的控制器在飞行器快速变形过程中仍然对俯仰角指令具有良好的跟踪性能。In this paper, an attitude control method combined nonlinear dynamic inverse with sliding mode control is proposed for the attitude stability of a supersonic morphing aircraft. Firstly, the dynamic model and aerodynamic model of morphing aircraft are established. Then, the dynamic inverse method is used to solve the problem of nonaffine control input. Based on the dynamic inverse control, the dynamic sliding mode control is used to compensate the system inverse error caused by model error, and the effective tracking of pitch response by pitch command is realized. Finally, numerical simulation results show that the proposed method still has good tracking performance for pitch command in the process of aircraft rapid deformation.

关 键 词：变形飞行器 非仿射非线性系统 动态逆控制 动态滑模控制 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]