Abstract: It′scomparativelydifficulttomodelthesolarradiationpressurewhencalculatingthepreciseorbitofthespacecraft.Especiallywhentheshapeofthespacecraftisinvolute,therewouldbesuperpositionandobscurationbetweendifferentmaterials,sothatthenormalexperimentalmethoddoesn′twork.Basedontheprecise3-DGeometricModel,thesimulativevisionwasusedtogetthesectionshapeofthespacecraftwhichperpendiculartotheSunvector,andthencalculatedtheequivalentSRPareaandthecoefficientwiththeSRPcharacteristicsofthematerial.Toreducetheamountofcalculation,anewmethodwasprovidedusingprior-calculatingandreal-time-interpolation.ConsideringthattheSRPcharacteristicswouldchangeinspace,thecalculationwastransformedintoasemi-empiricalformulasothecoefficientscouldbeestimatedbytheobservationdata.Thesimulationindicatesthattheanalysismethodcaneffectivelyreflecttheobscurationbetweenthepartsofthespacecraft.

Key words: Solarradiationpressureforcemodel, 3-Dgeometricmodel, Shadowinganalysis, Semi-empiricalformula, Spacecraft