基于固定时间收敛的增量动态逆飞行姿态控制  

Flight attitude control based on fixed time convergence incremental nonlinear dynamic inversion

作　　者：何晨璐 张强 吴远航 HE Chenlu;ZHANG Qiang;WU Yuanhang(AVIC Aviation Simulation System Co.,Ltd.,Shanghai 201100,China)

机构地区：[1]中航航空模拟系统有限公司,上海201100

出　　处：《飞行力学》2024年第2期13-21,共9页Flight Dynamics

摘　　要：为进一步提高增量非线性动态逆飞行姿态控制的收敛速度,提出了固定时间收敛增量非线性动态逆飞行姿态控制方法。首先,针对多输入多输出系统推导了固定时间收敛的增量非线性动态逆控制律,并利用Lyapunov定理分析了闭环系统的稳定性和收敛性。其次,设计了固定时间收敛增量非线性动态逆飞行姿态控制器,建立了内外环控制律。最后,将固定时间收敛增量非线性动态逆飞行姿态控制方法应用于具有高精度气动数据的F-16飞机模型,与有限时间收敛增量非线性动态逆飞行姿态控制方法进行仿真对比。结果表明,所提方法具有鲁棒性和更强的收敛快速性。To improve the convergence speed of incremental nonlinear dynamic inversion(INDI)flight attitude control,the fixed-time convergence INDI(Fixed-Time INDI)was proposed.Firstly,the control law was derived for a multi-input and multi-output system,and the stability and convergence property were proved by Lyapunov theorem.Then,the Fixed-Time INDI flight attitude controller with inner and outer loop control laws was designed.Finally,the Fixed-Time INDI flight attitude control was applied to F-16 model with high precision aerodynamic data and compared with finite-time convergence INDI(FINDI).Simulation results show that the proposed method is robust and has stronger convergence speed.

关 键 词：增量非线性动态逆 固定时间收敛 飞行控制 姿态控制 

分 类 号：V249.1[航空宇航科学与技术—飞行器设计]