摘要
Satelliteattitudeinformationisessentialforpico-satelliteapplicationsrequiringlight-weight,low-power,andfast-computationcharacteristics.Theobjectiveofthisstudyistoprovideamagnetometer-onlyattitudeestimationmethodforalow-altitudeEarthorbit,biasmomentumpico-satellite.Basedontwoassumptions,thespacecraftsphericalsymmetryanddampingofbodyrates,alinearkinematicsmodelofabiasmomentumsatellite'spitchaxisisderived,andthelinearestimationalgorithmisdeveloped.ThealgorithmcombinesthelinearKalmanfilter(KF)withtheclassicthree-axisattitudedeterminationmethod(TRIAD).KFisusedtoestimatesatellite'spitchaxisorientation,whileTRIADisusedtoobtaininformationconcerningthesatellite'sthree-axisattitude.Simulationtestsconfirmedthatthealgorithmissuitedtothetime-varyingmodelerrorsresultingfrombothassumptions.Theestimateresultkeepstrackingsatelliteattitudemotionduringalldamping,stable,andfreerotatingcontrolstages.Comparedwithnonlinearalgorithms,suchasextendedKalmanfiler(EKF)andsquarerootunscentedKalmanfiler(SRUKF),thealgorithmpresentedherehasanalmostequalperformanceintermsofconvergencetimeandestimationaccuracy,whiletheconsumptionofcomputingresourcesismuchlower.
出版日期
2010年06月16日（中国期刊网平台首次上网日期，不代表论文的发表时间）
