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1、第35卷第5期2016年10月飛行器測控學(xué)報JournalofSpacecraftTT&CTechnologyVol_35NO.5October2016引用格式:王易南,閆杰.基于衛(wèi)星和星敏感器的冗余激光慣組在軌標(biāo)定[J].飛行器測控學(xué)報,2016,35(5):358—364.WangYinan,YanJie.On-orbitcalibrationmethodforredundantinertialmeasurementunitsbysatelliteandstarsensors[J].JournalofSpacecraftTT&cTechnology,2016,35(5):358—364
2、?;谛l(wèi)星和星敏感器的冗余激光慣組在軌標(biāo)定王易南,閆杰(西北工業(yè)大學(xué)航天學(xué)院·西安·710072)摘要:采用高精度衛(wèi)星導(dǎo)航速度、位置信息以及星敏感器提供的姿態(tài)信息設(shè)計十表冗余捷聯(lián)慣組的標(biāo)定模型,包含陀螺和加速度計的零次項和標(biāo)度因數(shù),對衛(wèi)星和星敏感器輔助的冗余激光陀螺捷聯(lián)慣組進(jìn)行實時在軌標(biāo)定。利用標(biāo)準(zhǔn)Kalman濾波和SageHusa自適應(yīng)濾波作為估計算法,對十表冗余捷聯(lián)慣組參數(shù)進(jìn)行在線估計。數(shù)值仿真結(jié)果表明:參數(shù)標(biāo)定精度均在7%以內(nèi),是一種實時的在軌標(biāo)定方法,滿足誤差補(bǔ)償要求。冗余慣組在軌標(biāo)定方法為航天器高精度定姿和定軌提供了一種理論參考。關(guān)鍵詞:在軌標(biāo)定;冗余慣組;衛(wèi)星導(dǎo)航;星敏感器;最
3、優(yōu)估計;自適應(yīng)濾波中圖分類號:V448.22文獻(xiàn)標(biāo)志碼:A文章編號:1674—5620(2016)05—0358—07Dol:10.7642/j.issn.1674—5620.2016-05—0358—07On-OrbitCalibrationMethodforRedundantInertialMeasurementUnitsbySatelliteandStarSensorsWANGYinan。YANJie(SchoolofAstronautics,NorthwesternPolytechnialUniversity,Xi’an710072)Abstract:Weproposedareal
4、—timeOil—orbitcalibrationmethodforredundantlasergyroinertialmeasurementu—nits.Highprecisionspeedandlocationinformationfromsatellitenavigationandattitudeinformationfromstarsen..sorsareusedtOdesignthecalibrationmodelwithteninertialinstruments(fivegyrosandfiveaccelerometers),in—cludinggyrosbiasandacc
5、elerometersbiasandscalefactor.StandardKalmanfilterandSage-Husaadaptivefilterareappliedastheestimationalgorithmandinertialinstrumentsredundantstrapdowninertialmeasurementunitparame—tersareestimatedon-line.Theresultsofnumericalsimulationshowthatparameterscalibrationpreeisioniswithin7%.Itisakindofrea
6、l—timeon—orbitcalibrationmethod,whichsatisfiestherequirementsoferrorcompensation.Atheoreticalreferenceforhighprecisionspacecraftpositionandattitudedeterminationmethodisproposedbyredun—dantinertialmeasurementuniton-orbitcalibration.Keywords:on-orbitcalibration;redundantinertialmeasurementunits;sate
7、llitenavigation;starsensor;optimales—timation;adaptivefiltering0引言制導(dǎo)工具誤差占到制導(dǎo)系統(tǒng)誤差的80~90%,因此,通過分析建立準(zhǔn)確的慣性元件誤差模型,在慣性元件的測量過程中對慣性元件進(jìn)行誤差補(bǔ)償,可以達(dá)到降低SINS(StrapdownInertialNavigationSystem,捷聯(lián)慣性導(dǎo)航系統(tǒng))制導(dǎo)工具誤差的目的。慣性系統(tǒng)地面標(biāo)定方法已經(jīng)比較成熟