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时间:2019-03-05
《嫦娥三号动力落月段轨迹确定策略_昌胜骐》由会员上传分享,免费在线阅读,更多相关内容在教育资源-天天文库。
1、第33卷第3期飞行器测控学报Vol.33No.32014年5月JournalofSpacecraftTT&CTechnologyMay2014引用格式:昌胜骐,黄勇,宋叶志,等.嫦娥三号动力落月段轨迹确定策略[J].飞行器测控学报,2014,33(3):236-243.ChangShengqi,HuangYong,SongYezhi,etal.OntrajectorydeterminationstrategyforsoftlandingofCE-3onthemoon[J].Jour-nalofSpacecraftTT&CTechnology,201
2、4,33(3):236-243.*嫦娥三号动力落月段轨迹确定策略昌胜骐1,2,黄勇1,宋叶志1,李培佳1,胡小工1(1.中国科学院上海天文台·上海·200030;2.中国科学院大学研究生院·北京·100049)摘要:针对CE-3(嫦娥三号)月球探测器动力下降弧段,特别是悬停避障段频繁机动的特点,提出了采用B样条函数逼近方法进行落月轨迹确定。仿真分析表明:在动力下降运动较平滑弧段,B样条逼近法计算结果略优于多项式拟合法;而在频繁机动弧段,B样条逼近法有明显优势。计算结果表明,加入VLBI(VeryLongBaselineInter-ferometry
3、,甚长基线干涉测量)数据后能有效提高落月轨迹确定精度,在没有系统误差的情况下联合定位后位置精度优于50m。此外,还分析了三向测量系统差对定位的影响,可对CE-3任务提供参考。最后对CE-3实测数据进行处理,动力落月段末点位置和着陆器定位计算值相差不到200m。关键词:落月轨迹;B样条函数;三向测量;软着陆;嫦娥三号(CE-3)中图分类号:V412.41文献标志码:A文章编号:1674-5620(2014)03-0236-08DOI:10.7642/j.issn.1674-5620.2014-03-0236-08OnTrajectoryDetermi
4、nationStrategyforSoftLandingofCE-3ontheMoon1,2,HUANGYong1,SONGYezhi1,LIPeijia1,HUXiaogong1CHANGShengqi(1.ShanghaiAstronomicalObservatory,ChineseAcademyofSciences,Shanghai200030;2.GraduateSchool,ChineseAcademyofSciencesUniversity,Beijing100049)Abstract:AmethodbasedonBsplineappr
5、oximationisproposedfordeterminationofthelandingtrajectoryofCE-3(Chang’e-3)probeonthemoonbasedonthefeatureoffrequentmaneuversoftheprobeintheboosteddescendingarcand,particularly,duringthehoveringandobstacle-avoidanceperiod.Simulationshowsthatthemethodgivesahigherprecisionresultc
6、omparedwiththemethodbasedonpolynomialfunctionfittingintherelativelysmootharcintheboosteddescendingperiodanditissignificantlybetterinthearcwithfrequentmaneuvers.ComputationresultsindicatethattheaddingofVLBI(VeryLongBaselineInterferometry)dataeffectivelyincreasestheaccuracyinde-
7、terminationofthemoon-landingtrajectory.Thepositionaccuracyisbetterthan50mafterjointtrajectorydetermi-nationwithoutsystematicerror.Theimpactofthesystematicerrorofthree-waymeasurementontrajectorydetermi-nationisalsoanalyzed.Finally,themethodistestedwithdatafromtheCE-3mission.Com
8、paredwiththecomputedlocationofthelander,thepositionaccuracyat
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