哈尔滨工程大学学报2016，Vol.37Issue(11)：1526-1531,6.DOI:10.11990/jheu.201503056
近空间飞行器爬升段跟踪控制
Tracking control for a near-space vehicle in the ascent phase
摘要
Abstract
In the accelerating ascent phase of a near⁃space vehicle, the traditional sliding⁃mode control method has defects such as low convergence speed, insufficient robustness, and severe chattering when dealing with uncertain⁃ty. With respect to these problems, in this paper, we propose a dual⁃power reaching⁃law sliding⁃mode control meth⁃od for designing the flight controller to achieve precise trajectory tracking in the ascent phase. This method uses full⁃state feedback to linearize the nonlinear model of the near⁃space vehicle, then analyzes the stability of the designed controller by the Lyapunov stability theory. A simulation analysis is conducted on the control effects of the tradition⁃al and the dual⁃power reaching⁃law sliding⁃mode control methods. The results demonstrate that the dual⁃power reac⁃hing⁃law sliding⁃mode control method can accurately track the command signal and promote system stability and ro⁃bustness in the treatment of nonlinear systems characterized by parametric uncertainty and outside interference.关键词
近空间飞行器/跟踪控制/爬升模态/双幂次趋近律/滑模控制/参数不确定/李雅普诺夫稳定性理论Key words
near-space vehicle/tracking control/climbing mode/dual exponential reaching law/sliding mode con-trol/parametric uncertainty/Lyapunov stability theory分类
航空航天引用本文复制引用
顾臣风,江驹,吴雨珊..近空间飞行器爬升段跟踪控制[J].哈尔滨工程大学学报,2016,37(11):1526-1531,6.基金项目
国家自然科学基金项目（61304223）；教育部高等学校博士学科点专项科研基金项目（20123218120015）；南京航空航天大学研究生创新基地（实验室）开发基金项目（ kfjj201420）． （）
