简介:Thisletterproposesamethodfordesigningaspecificformationofsatelliteswheretheflyingmotiononlyexistsinacircleorbitplaneofthereferencesatellite,whichmeansthattheorbiteccen-tricityiszero.ThismethodcombinestheHillequation,theKeplerequation,andthegeometricalmeaningoforbitelements.Itcreatestheredundancyconditiontosimplifythededucingprocess,utilizesmultipleconditionstosolvetheorbitelementsforthesatelliteformation,andobtainstheanalyticalrelationshipoftheorbitelementsfortheformationsatelliteswiththeformationparametersandtheorbitelementsofthereferencesatellite.Usingtheseformulations,theorbitelementsandformationparametersfortheformationsatellitescanbesolvedforthegivenorbitelementsofthereferencesatellite.Theletterdescribestheproposeddouble-ellipseformationforbothGMTIandInSAR,andthevalidityoftheformationisdemonstratedviasimulation.