有限推力下的航天器绕飞轨道保持与控制  

Orbital maintenance and control of spacecraft fly-around with finite-thrust

作　　者：师鹏[1] 李保军[1] 赵育善[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《北京航空航天大学学报》2007年第7期757-760,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：863基金资助项目(2005AA776012)

摘　　要：基于线性动力学模型,研究了有限推力下的航天器绕飞轨道保持与控制问题.首先,针对绕飞轨道控制问题推导了精确的动力学模型,给出了经过线性化的动力学方程.然后,在线性二次性最优控制理论的基础上,设计了一种针对绕飞轨道的反馈控制系统,同时为了实现有限推力,设计了一个有界的非线性环节对控制加速度进行限制.数值仿真结果证明了所设计的控制系统渐进稳定、收敛快速,并且具有良好的控制精度.最后,通过计算不同相对位置误差时轨道控制系统需用的发动机工作时间,估算了轨道维持与轨道控制的燃料消耗量.Based on the linear dynamics model, the relevant issues of orbital maintenance and control of spacecraft fly-around with finite-thrust was studied. Firstly, aimed at the problem of orbital control of spacecraft fly-around, the exact dynamics model was derived and the linear dynamics equation was presented. Secondly, based on the linear quadratic optimal control theory, the feedback control system for fly-around orbit was designed. To realize finite-thrust, a limited nonlinear function to restrict the control acceleration was presented. The numerical simulation show the control system has asymptotic stability, faster convergence rate and higher control accuracy. Lastly, from calculating the engine＇s working time of different relative position errors, estimate the cost of fuel for orbit control and maintenance.

关 键 词：绕飞 轨道控制 最优控制 有限推力 

分 类 号：V448[航空宇航科学与技术—飞行器设计]