Design of Flight Control Law of Tilt-rotor Aircraft Based on Incremental Dynamic Inversion

被引：0
|
作者：
Zheng C. [1 ]
Tang P. [2 ]
Li Q. [1 ]
机构：
[1] School of Energy and Power Engineering, Beihang University, Beijing
[2] School of Transportation Science and Technology, Beihang University, Beijing
来源：
Binggong Xuebao/Acta Armamentarii | 2019年 / 40卷 / 12期
关键词：
Flight control law; Nonlinear incremental dynamic inversion; Simulation verification; Tilt-rotor aircraft;
D O I：
10.3969/j.issn.1000-1093.2019.12.009
中图分类号：
学科分类号：
摘要：
A flight control law of tilt-rotor aircraft based on incremental nonlinear dynamic inversion (INDI) is designed for the high precision and poor robustness of nonlinear dynamic inversion (NDI) control law. The incremental dynamic inversion control law is derived based on the dynamic model of tilt-rotor aircraft. In view of the redundancy of tilt-rotor aircraft, the control allocation algorithm of rudder surface is introduced based on the incremental dynamic inversion algorithm. A real-time solution to control the efficiency B-matrix is proposed, and a full-mode control law which can reduce the dependence on accurate mathematical model is designed. The effectiveness of the proposed algorithm for tilt-rotor aircraft is verified by simulation. © 2019, Editorial Board of Acta Armamentarii. All right reserved.
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页码：2457 / 2466
页数：9
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