Robust Adaptive Control of Hypersonic Vehicle Considering Inlet Unstart

考虑进气道不起动的高超声速飞行器鲁棒自适应控制研究

¹ School of Astronautics, Northwestern Polytechnical University, Xi'an 710072, China
² Xi'an Aerospace Propulsion Institute, Xi'an 710072, China
³ Shanghai Electro-Mechanical Engineering Institute, Shanghai 201109, China

Received: 24 February 2019

Abstract

A large-scale change in the aerodynamic characteristics of the aircraft caused by the inlet unstart of the air-breathing hypersonic vehicle causes a large oscillation of the response or even a control system instability. A model reference adaptive control method considering the influence of inlet unstart is proposed. Firstly, the attitude control system is designed based on LQR-PI method for the model of inlet start, which is used as the reference model. When the inlet unstart, the model reference adaptive control is added on the basis of LQR-PI controller to improve the robustness of the system to the uncertainties caused by the inlet unstart. The method can quickly stabilize the attitude when the inlet unstart, and provides conditions for the inlet restart. Finally, the present method is verified by the simulation results. The simulation results show that when the inlet unstart, the system can re-track quickly the control command, and the steady-state error tends to zero, which verifies the effectiveness of the present method.

摘要

针对吸气式高超声速飞行器进气道不起动引起飞行器气动特性大范围变化，从而导致响应出现大幅振荡甚至控制系统失稳的问题，提出了一种考虑进气道不起动影响的模型参考自适应控制方法。该方法首先针对进气道起动时的模型，设计了基于LQR-PI方法的姿态控制系统，并以此作为进气道不起动时的参考模型；当进气道不起动时，在LQR-PI基准控制器的基础上增加模型参考自适应控制项，通过跟踪参考模型以提高系统对进气道不起动引起模型偏差的鲁棒性，在进气道出现不起动的情况下能快速稳定姿态，为进气道再起动提供条件。最后对所提方法进行了数字仿真，结果表明，系统在进气道出现不起动时能够快速跟踪控制指令，且稳态误差趋于零，验证了所提方法的有效性。