分离模块异构航天器集群松散队形设计  

Fractionated Isomerized Spacecraft Cluster Incompact Formation Design

作　　者：黄河[1] 周军[1] 刘莹莹[1] 

机构地区：[1]西北工业大学精确制导与控制研究所,西安710072

出　　处：《宇航学报》2014年第12期1405-1411,共7页Journal of Astronautics

基　　金：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 m2/kg和0.0032 m2/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。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 incumpact 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 km, and the area mass ratio of two satellites is 0. 0030 m2/kg and 0. 0032 m2/kg respectively, the relative distance of the two satellites can be within from 200 m to 20 km in 50 days.

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 

分 类 号：V44[航空宇航科学与技术—飞行器设计]