›› 2014, Vol. 34 ›› Issue (2): 22-27.doi: 10.3780/j.issn.1000-758X.2014.02.003

• 研究探讨 • 上一篇    下一篇

基于线性化运动方程的超低轨飞行器轨道修正算法

 王涛, 张洪波, 汤国建   

  1. (国防科学技术大学航天科学与工程学院,长沙410073)
  • 收稿日期:2013-06-25 修回日期:2013-08-29 出版日期:2014-04-25 发布日期:2014-04-25
  • 作者简介:王 涛 1989年生,2011年毕业于河北科技大学测控专业,现为国防科学技术大学航空宇航科学与技术专业硕士研究生。研究方向为飞行器动力学、制导与控制。

OrbitCorrectionStrategyofLEOVehicleBasedonLinearizedOrbitalMotionEquation

 WANG  Tao, ZHANG  Hong-Bo, TANG  Guo-Jian   

  1. (CollegeofAerospaceScienceandEngineering,NationalUniversityofDefenseTechnology,Changsha410073)
  • Received:2013-06-25 Revised:2013-08-29 Online:2014-04-25 Published:2014-04-25

摘要: 超低轨飞行器受到大气的严重影响,需要不断地实施轨道修正才能在标称轨道附近飞行。文章针对超低轨飞行器的轨道保持问题,建立了考虑地球非球形J2项摄动和大气阻力摄动的线性化运动方程,给出了基于线性化方程的修正速度增量计算方法,并研究了补偿线性化误差的方法。数值仿真表明,该方法能够保证飞行器不超出要求的精度通道。对于轨道高度为120km的飞行器,飞行1h的最佳修正次数为6,所需速度增量为63.7971m/s。

关键词: 轨道修正, 线性化运动方程, 摄动, 冲量, 超低轨, 航天器

Abstract: It is very necessary to execute orbit correction for ultra-low-orbit vehicle, whichisbadlyinfluenced by near-earth environment.The orbital motion equation which considered the non-spherical perturbation and atmospheric perturbation was linearized. Then, an impulse correction method was introduced and used to keep a near-earth vehicle flying along the standard orbit. Furthermore, a method to eliminate errors caused by linearizationwasalso studied.The feasibility of the correction method was validated by simulation. For a 120km-altitude vehicle, flying one hour, the optimal correction times is 6, the required △v is 63.7971m/s.

Key words: Orbitcorrection, Linearizedmotionequation, Perturbation, Impulsethrust, Ultralowearthorbit, Spacecraft