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分离模块异构航天器集群松散队形设计
引用本文:黄河,周军,刘莹莹.分离模块异构航天器集群松散队形设计[J].宇航学报,2014,35(12):1405-1411.
作者姓名:黄河  周军  刘莹莹
作者单位:西北工业大学精确制导与控制研究所,西安710072
基金项目:国家自然科学基金(61304238);国家高技术研究发展计划(2012AA120602); 中央高校基本科研业务费(3102014JCQ01004)
摘    要:针对近地轨道分离模块航天器集群,考虑航天器之间面质比差异,提出一种能在较长时间内维持两星之间相对距离的松散队形设计方法。该方法以相对偏心率向量和相对轨道倾角向量描述松散队形,以两颗卫星之间的轨道长半轴之差和相对相位角之差为优化变量,并且通过设置虚拟空间圆解决避碰问题,保证在考虑气动力摄动的情况下,异构航天器松散编队能够有较长时间满足距离要求。仿真研究表明,针对轨道高度为500 km的参考轨道,当两星面质比分别为0.003 m 2/kg和0.0032 m 2/kg时,两颗卫星之间的距离能够在50天内处于200 m到20 km之间。

关 键 词:分离模块航天器  松散编队  异构航天器  集群  队形设计  
收稿时间:2014-03-13

Fractionated Isomerized Spacecraft Cluster Incompact Formation Design
HUANG He,ZHOU Jun,LIU Ying ying.Fractionated Isomerized Spacecraft Cluster Incompact Formation Design[J].Journal of Astronautics,2014,35(12):1405-1411.
Authors:HUANG He  ZHOU Jun  LIU Ying ying
Affiliation:Institute of Precision Guidance and Control, Northwestern Polytechnical University, Xi′an 710072, China
Abstract:An incompact formation design method is proposed for a low earth orbit fractionated spacecraft cluster, the differential drag is considered. The relative distance of any two satellites in the incompact formation is required to be within a certain bound in a long time. The relative eccentricity vector and the relative orbit inclination are used to describe the incompact formation, and the relative semi-axis bias and the relative angular of latitude are considered as the optimal variables. A fictitious space circle formation is used to design the relative orbit for collision avoidance. The relative distance of the two isomerized satellites can be satisfied when considering the aerodynamic force. Simulation results manifest that while the satellite orbit is 500〖KG*9〗km, and the area mass ratio of two satellites is 0.0030 m 2/kg and 0.0032 m 2/kg respectively, the relative distance of the two satellites can be within from 200 m to 20 km in 50 days.
Keywords:Fractionated spacecraft  Incompact formation  Isomerized spacecraft  Cluster  Formation design    
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