近空间飞行器爬升段跟踪控制  

Tracking control for a near-space vehicle in the ascent phase

作　　者：顾臣风 江驹[1] 吴雨珊 

机构地区：[1]南京航空航天大学自动化学院,江苏南京210016

出　　处：《哈尔滨工程大学学报》2016年第11期1526-1531,共6页Journal of Harbin Engineering University

基　　金：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)

摘　　要：在近空间飞行器加速爬升模态下,传统的滑模控制方法在处理不确定性问题时,存在收敛速度慢、鲁棒性不强和抖振严重等不足。针对这些问题,本文提出双幂次趋近律滑模控制方法来设计飞行控制器,从而实现飞行器爬升段轨迹的精确跟踪。将飞行器非线性模型进行精确反馈线性化处理,并利用李雅普诺夫稳定性理论进行稳定性分析。仿真分析了双幂次趋近律滑模控制方法和传统滑模控制方法的控制效果。结果表明:在处理具有参数不确定性和外界干扰的非线性系统时,双幂次趋近律滑模控制方法能够精确地跟踪指令信号,并且具有较强的稳定性和鲁棒性。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 uncertainty. 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 fullstate 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 traditional 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 robustness 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 

分 类 号：V249[航空宇航科学与技术—飞行器设计]