简介：Asetofparameterscalledrelativeorbitalelementsweredefinedtodescribetherelativemotionofthesatellitesintheformationflying.Withthehelpoftheseparameters,theeffectoftheperturbationsontherelativeorbittrajectoryandgeometricpropertiesofsatelliteformationcanbeeasilyanalyzed.First,therelativeorbitalelementsarederived,andpointedout:iftheeccentricityoftheleadingsatelliteisasmallvalue,therelativeorbittrajectoryisdeterminedbytheintersectionbetweenanellipticcylinderandaplaneintheleadingsatelliteorbitframereference;andtheparametersthatdescribetheellipticcylinderandtheplanecanbeusedtoobtaintherelativeorbittrajectoryandtherelativeorbitalelements.Second,byanalyzingtheeffectsofgravitationalperturbationsontherelativeorbitusingtherelativeorbitalelements,itisfoundthatthepropagationofarelativeorbitconsistsoftwoparts:oneisthedriftoftheellipticcylinder;andtheotheristherotationoftheplaneresultedfromtherotationofthenormaloftheplane.Meanwhile,theanalyticformulaeforthedriftandrotationratesofarelativetrajectoryundergravitationalperturbationsarepresented.Finally,therelativeorbittrajectoryandthecorrespondingchangeswereanalyzedwithrespecttotheJ2perturbation.
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