航天器悬停构型设计与控制方法

饶殷睿; 韩潮; 殷建丰; 陈欢

doi:10.7527/S1000-6893.2014.0310

航空学报 >

2015 , Vol. 36 >Issue 7: 2361 - 2371

DOI: https://doi.org/10.7527/S1000-6893.2014.0310

电子与控制

航天器悬停构型设计与控制方法

饶殷睿 ,
韩潮 ,
殷建丰 ,
陈欢

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1. 北京航空航天大学宇航学院, 北京 100191;
2. 中国空间技术研究院总体部, 北京 100094

饶殷睿男, 博士研究生。主要研究方向: 航天器相对运动, 卫星编队飞行。 Tel: 010-82316536 E-mail: raoyinrui@sa.buaa.edu.cn;殷建丰男, 博士, 工程师。主要研究方向: 航天器动力学与控制, 航天器相对运动。 Tel: 010-68745433 E-mail: jianfengabc@gmail.com

收稿日期: 2014-08-06

修回日期: 2014-11-02

网络出版日期: 2014-11-06

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Method of spacecraft hovering formation design and control

RAO Yinrui ,
HAN Chao ,
YIN Jianfeng ,
CHEN Huan

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1. School of Astronautics, Beihang University, Beijing 100191, China;
2. Institute of Spacecraft System Engineering, China Academy of Space Technology, Beijing 100094, China

Received date: 2014-08-06

Revised date: 2014-11-02

Online published: 2014-11-06

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摘要

为满足航天器在轨服务任务对悬停技术的需求,对航天器悬停构型的设计与控制问题进行了研究。通过任务航天器轨道设计得出目标航天器与任务航天器的绝对轨道关系,并用以说明悬停轨道的形成机理。结合任务航天器相对于目标航天器的相对轨迹,采用具有严格定义的相对轨道要素,对悬停轨道在目标航天器轨道平面内和平面外的构型进行描述。对"间隔式"的悬停构型脉冲控制策略进行推导,以实现任务航天器在目标航天器任意位置的长期悬停,并在此基础上分析悬停构型变化对速度脉冲的影响。最后,通过典型仿真算例验证所提方法与结果的正确性和有效性,并获得任务航天器在不同悬停轨道间转移的实现过程。研究结果完善了航天器悬停轨道的设计与控制方法,并说明了设计的悬停轨道具有可行性,能够为工程任务设计人员提供参考。

关键词： 悬停构型; 悬停轨道; 相对轨道要素; 构型设计; 在轨服务

本文引用格式

饶殷睿 , 韩潮 , 殷建丰 , 陈欢 . 航天器悬停构型设计与控制方法[J]. 航空学报, 2015 , 36(7) : 2361 -2371 . DOI: 10.7527/S1000-6893.2014.0310

Abstract

To satisfy the need of the hovering technology in the spacecraft on-orbit servicing mission, a study on spacecraft hovering formation design and control is carried out. By designing the mission spacecraft orbit, the absolute orbit relationship between the target spacecraft and the mission spacecraft is presented and the mechanism of the hovering orbit is illustrated. According to the relative trajectory of the mission spacecraft relative to the target spacecraft, and using the well-defined relative orbit elements, the configuration of the hovering orbit in the target spacecraft orbital plane and out of the target spacecraft orbital plane are described. An interval impulse control strategy for hovering formation is derived and the mission spacecraft can be remained at a specified position to the target spacecraft for a long time. Furthermore, the effect of the hovering formation on the required velocity impulse is analyzed. The proposed method and conclusions are validated by simulation through some typical examples. A process of making the mission spacecraft transfer between two hovering orbits is presented. The study improves the design and control methods of spacecraft hovering orbit, and indicates the feasibility of the designed hovering orbit. The theory of spacecraft hovering dynamics and control is improved and the results could provide some references for the designers of the engineering missions.

Key words： hovering formation; hovering orbit; relative orbit elements; formation design; on-orbit servicing

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