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

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 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

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