Flight Control for Hypersonic Vehicle Based on Quasi-Continuous Integral High-Order Sliding Mode
This paper first applied integral sliding mode concept to design of nonlinear robust controller for hypersonic vehicle model which is nonlinear, multivariable, and includes uncertain parameters. Firstly, the multi-input and multi-output (MIMO) quasi-continuous integral high-order sliding mode controller is proposed to track the responses of the vehicle to a step change in altitude and velocity. Furthermore, based on the simulation results, the virtual control is introduced into the design of fourth-order velocity and fifth-order altitude quasi-continuous integral sliding mode controller in order to reduce the control chattering. The arbitrary order robust sliding mode differentiator is used to calculate the missing differential which is used in the design of controller. Finally, Simulation results show that the proposed methodology guarantees the whole robustness of the system throughout an entire response of the system and achieves excellent tracking performances in spite of parameter uncertainties.
nonlinear robust controller integral high-order sliding mode control high-order sliding mode differentiator
Jie Wang Qun Zong Bailing Tian Fang Wang
School of Electric and Automation Engineering, Tianjin University, Tianjin 300072, China
国际会议
The 24th Chinese Control and Decision Conference (第24届中国控制与决策学术年会 2012 CCDC)
太原
英文
2197-2202
2012-05-23（万方平台首次上网日期，不代表论文的发表时间）