Deceleration transition controller design of thrust-vectored short takeoff and vertical landing aircraft based on control allocation

被引：0
|
作者：
Liu L. [1 ]
Tang Y. [2 ]
Tao C. [2 ]
Zhen Z. [1 ]
Liu J. [1 ]
机构：
[1] College of Automatic Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing
[2] AVIC Chengdu Aircraft Design & Research Institute, Chengdu
来源：
Harbin Gongcheng Daxue Xuebao/Journal of Harbin Engineering University | 2022年 / 43卷 / 06期
关键词：
Angular acceleration estimation; Deceleration transition process; Improved particle swarm algorithm; Intelligent control allocation; Kalman filter; Nonlinear; Nonlinear incremental dynamic inversion; Short takeoff and vertical landing aircraft;
D O I：
10.11990/jheu.202104006
中图分类号：
学科分类号：
摘要：
The thrust vectoring short takeoff and vertical landing (STOVL) aircraft is faced with nonlinearity, control redundancy, and control coupling during the deceleration transition from flat flight to hover. In this paper, a six degrees of freedom (6DOF) nonlinear mathematical model of the thrust vector STOVL aircraft with actuator constraints is established to solve the above problems. A deceleration transition process control method based on intelligent control distribution is proposed, which uses nonlinear incremental dynamic inversion as the control law to obtain the virtual control input. Taking the execution capability of the actuator and the transition process expectation index design optimization function into account, the improved particle swarm algorithm is used to calculate the actual control amount online. Simulation experiments verify that the method has high command tracking accuracy during the transition process and strong robustness against aerodynamic parameter perturbation and external wind interference. © 2022, Editorial Department of Journal of HEU. All right reserved.
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页码：832 / 841
页数：9
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