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
何晨璐 1张强 1吴远航1
作者信息
- 1. 中航航空模拟系统有限公司,上海 201100
- 折叠
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.
Abstract
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 conver-gence property were proved by Lyapunov theorem.Then,the Fixed-Time INDI flight attitude con-troller with inner and outer loop control laws was designed.Finally,the Fixed-Time INDI flight atti-tude control was applied to F-16 model with high precision aerodynamic data and compared with fi-nite-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Key words
incremental nonlinear dynamic inversion/fixed time convergence/flight control/atti-tude control引用本文复制引用
出版年
2024
NETL
NSTL
万方数据