›› 2014, Vol. 34 ›› Issue (2): 69-75.doi: 10.3780/j.issn.1000-758X.2014.02.009

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Control Method Based On e/i Vector to Realize Satellites Formation with Relative Inclined Configuration

 WU  Sheng-Gang1,2, QIAN  Shan1,2, LI  Heng-Nian1, TAN  Wei1,2   

  1. (1StateKeyLaboratoryofAstronauticDynamics,Xi′an710043)
    (2Xi′anSatelliteControlCenter,Xi′an710043)
  • Received:2013-06-28 Revised:2013-10-25 Online:2014-04-25 Published:2014-04-25

Abstract: The problem of relative inclined configuration design and orbit control of the distributed InSAR satellites formation flying was studied. First, the algorithm of relative inclined configuration design based on e/i vector was put forward. Then the relationship between the relative inclined configuration and the errors of eccentricity, inclination and the right ascension of ascending node were given.According to the properties of relative inclined configuration of distributed satellites, the four impulse orbit maneuver strategy was put forward based on the Gauss perturbation functions satelliteformation control model. Simulation results show that the method of relative inclined configuration design is intuitionistic, the orbit maneuver strategy is simple and the configuration is stable.

Key words: Distributed satellites, e/i vector, Relative inclined configuration, Flying-around angle, Orbit control