›› 2015, Vol. 35 ›› Issue (5): 22-32.doi: 10.3780/j.issn.1000-758X.2015.05.004

• 研究探讨 • 上一篇    下一篇

微纳卫星共面伴飞相对运动椭圆短半轴最省燃料控制

周美江, 吴会英, 齐金玲   

  1. (上海微小卫星工程中心,上海201203)
  • 收稿日期:2015-04-01 修回日期:2015-05-26 出版日期:2015-10-25 发布日期:2015-10-25
  • 作者简介:周美江 1989年生,2012年获哈尔滨工业大学飞行器设计专业硕士学位,工程师。研究方向为航天器轨道动力学与控制。

Minimum Fuel Control of Relative Ellipse Semi-Minor Axis in Micro/nano-Satellite In-Plane Companion-Flying

 ZHOU  Mei-Jiang, WU  Hui-Ying, QI  Jin-Ling   

  1. (ShanghaiEngineeringCenterForMicrosatellites,Shanghai201203)
  • Received:2015-04-01 Revised:2015-05-26 Online:2015-10-25 Published:2015-10-25

摘要: 针对伴随微纳卫星资源受限、轨控需要尽可能节省燃料的现实问题,基于希尔(Hill)方程,研究推导了共面编队伴飞卫星的轨控时机和轨控方向对相对运动椭圆短半轴控制效率的影响。理论推导和仿真均表明:当控制量大小|ΔV|与相对运动椭圆短半轴b满足|ΔV|≤nb/2关系时(n为参考星平均轨道角速度),在相对运动椭圆上下点进行横向或反横向控制,最大效率地将相对运动椭圆短半轴改变了|Δb|=2|ΔV|/n。其中,在上点反横向或下点横向进行控制,可以最大效率地增大椭圆短半轴;在上点横向或下点反横向进行控制,可以最大效率地减小椭圆短半轴。

关键词: 共面伴飞, 希尔方程, 椭圆短半轴, 最省燃料控制, 控制时机, 控制方向, 微纳卫星

Abstract: It is essential to save fuel in orbit control for micro/nano satellite due to the lack of resources. The  influences of control direction and control time on the relative ellipse semi-minor axis in in-plane companion-flying satellites were studied based on the Hill equation. Both theoretical analysis and simulation results show that the most efficient control method of relative ellipse semi-minor axis is to impose control parallel to the lateral direction on the top or bottom points while the control quantity |ΔV|≤nb/2 is certain and the relative ellipse semi-minor axis will change |Δb|=2|ΔV|/n at the same time.

Key words: In-planecompanion-flying, Hillequation, Ellipsesemi-minoraxis, Minimumfuelcontrol, Controltime, Controldirection, Micro/nanosatellite