[1]李-鹏,陈兴林,宋申民,等.交会对接最后逼近段姿轨耦合控制[J].智能系统学报,2010,5(6):530-533.
LI Peng,CHEN Xing-lin,SONG Shen-min,et al.Research on an attitude and orbit coupling control over the final approach phase of rendezvous and docking[J].CAAI Transactions on Intelligent Systems,2010,5(6):530-533.
点击复制
LI Peng,CHEN Xing-lin,SONG Shen-min,et al.Research on an attitude and orbit coupling control over the final approach phase of rendezvous and docking[J].CAAI Transactions on Intelligent Systems,2010,5(6):530-533.
交会对接最后逼近段姿轨耦合控制
《智能系统学报》[ISSN 1673-4785/CN 23-1538/TP] 卷:
5
期数:
2010年第6期
页码:
530-533
栏目:
学术论文—智能系统
出版日期:
2010-12-25
- Title:
- Research on an attitude and orbit coupling control over the final approach phase of rendezvous and docking
- 文章编号:
- 1673-4785(2010)06-0530-04
- 分类号:
- TP18;TN911.23
- 文献标志码:
- A
- 摘要:
- 针对交会对接最后逼近段的制导律和姿态控制律的设计问题，首先对逼近段轨道与姿态的耦合问题进行了分析，并利用高阶滑模控制设计了最后逼近段的姿轨控制系统；然后设计了基于Hill方程的直线型制导律；最后对所采用的直线型变结构制导律和最后逼近段相对姿态控制律进行了仿真.仿真结果表明所设计的控制系统满足对接要求.
- Abstract:
- To achieve the high precision requirement in the final approach phase of autonomous space rendezvous and docking (RVD) on a relative attitude, first an analysis was made on the coupling of attitude and orbit. Next, the highorder sliding mode (HOSM) controller was used to design the attitude and orbit control system in the final approach phase. After that, a beeline guidance law based on the Hill equation was designed. The attitude control strategy shown here used the HOSM controller. Lastly, with the help of Simulink software, a simulation was carried out in terms of the linear variable structure guidance law and relative attitude control law. The results of simulation show that the designed control system meets the requirements of docking.
- 参考文献/References:
-
［1］WALLSGROVE R J, AKELLA M R. Globally stabilizing saturated attitude control in the presence of bounded unknown disturbances［J］. Journal of Guidance Control and Dynamics, 2005, 28(5): 957963.
［2］Di GENNARO S. Stabilization of rigid spacecraft with uncertainties and input saturation in a central gravitational field［C］//Proceedings of 36th Conference on Decision and Control. San Diego, America， 1997: 42044209.
［3］VADALI S R. Variablestructure control of spacecraft largeangle maneuvers［J］. Journal of Guidance, Control and Dynamics， 1986, 9(2): 235239.
［4］DWYER T A W, SIRARAMIREZ H. Variable structure control of spacecraft attitude maneuvers［J］. Journal of Guidance, Control and Dynamics, 1988, 11(3): 262270.
［5］PUKDEBOON C, ZINOBER A S I, THEIN M W L. Quasicontinuous higherorder sliding mode controller designs for spacecraft attitude tracking manoeuvres［J］. 1998(1):22442250.
［6］FRIDMAN L, DAVILA J, LEVANT A. Highorder slidingmode observation and fault detection［C］//Proceedings of the 46th IEEE Conference on Decision and Control. New Orleans, USA, 2007: 437442.
［7］DOREL L,LEVANT A. On chatteringfree slidingmode control［C］//Proceedings of the 47th IEEE Conference on Decision and Control Cancun， Mexico, 2008: 11471156.
［8］LEVANT A. Principles of 2sliding mode design［J］. Automatic， 2007(43): 576586.
备注/Memo
收稿日期：2010-02-16.
基金项目：国家“863” 计划资助项目（2006AA0488，2007AA0987，2008AA0987）.
通信作者：李 鹏.E-mail:pengli.hit@gmail.com.
作者简介：
李 鹏，男，1978年生，讲师，主要研究方向为非线性滤波.
陈兴林，男，1963年生，教授，博士生导师，哈尔滨工业大学控制科学与工程系副主任，控制科学与工程教学实验中心主任，国防科工委教材建设专家组成员，全国高等学校自动化专业系列教材编审委员会委员，中国人工智能学会智能控制与智能管理专业委员会委员.主要研究方向为飞行器控制与仿真、智能机器人、计算机控制.
更新日期/Last Update:
2011-03-03