• 论文 •

基于SMDO-TLC的高超声速飞行器姿态控制

1. 北京航空航天大学 飞行器控制一体化技术重点实验室, 北京 100191
• 收稿日期:2014-01-07 出版日期:2014-11-20 发布日期:2014-12-02
• 作者简介:邵星灵(1988-),男,江苏扬州人,博士生,huanying3557913@sina.com.
• 基金资助:

国家自然科学基金资助项目(61175084);长江学者和创新团队发展计划资助项目(IRT13004);航空科学基金资助项目

Attitude control for hypersonic vehicle based on SMDO-TLC

Shao Xingling, Wang Honglun

1. Science and Technology on Aircraft Control Laboratory, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
• Received:2014-01-07 Online:2014-11-20 Published:2014-12-02

Abstract:

In consideration of actuator input constraints, a novel attitude control method driven by sliding-mode disturbance observer was presented for supersonic vehicle which is fast time-varying, strong coupling combining with parameter non-deterministic. Firstly, via introducing the concept of second-order linear differentiator (SOLD), it was indicated that peaking phenomenon caused by a combination of first-order lag and pseudo differentiator, which is similar with SOLD, would emerge during the transient profile of differentiation of the nominal command in the existing trajectory linearization control (TLC). Nonlinear tracking differentiator (TD) was used to produce the nominal command and its derivative, saturation of actuator during transition time was solved. Secondly, second order sliding-mode disturbance observer (SOSMDO) based on integration of sign function was designed to reconstruct compound disturbances in the loops of attitude and angular rate respectively, and then compensation control law was proposed to realize attitude control. Simulation results show that the technique proposed can overcome the impact of large-scale perturbations of interference and aerodynamics parameters, meanwhile good dynamic character and steady quality was achieved, the hypersonic vehicle control demand of fast time-varying, high precision and strong robustness can be satisfied.