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1、 2006M7327tbt?vJournalofBeijingUniversity ofAeronautics andAstronautics July 2006Vo.l 32 No17l: 2005-08-15:t?7Te: ( 1982- ),o,pV3, jinghumm etang. com.;v|t4胡 静 杨 博(tbt?vt,100083)K 1: 高精度星光折射间接敏感地平的自主导航方法,目前被国内外广泛关注,由于大气参数变化的不确定性,国内外现用星光折射模型有一定局限性,使得利用星光折射导航定位精度大打折扣.根据大气密度随高度a纬度a季节等变化规律,有效改进现有固定高度( 2
2、5km)的观测模型,可从整体上提高自主导航精度及可靠性.并通过对大气折射原理a平流层大气数据a大气模型以及影响星光折射观测模型的诸多因素的深入研究,建立了自适应连续高度(20 50km)的星光折射观测模型,同时建立带摄动的系统方程,利用Unscented卡尔曼滤波算法进行了计算机仿真研究,并对仿真结果进行了误差分析.1 o M: 航天器; 导航; 折射; 观测模型; 轨道摄动ms|: V 448. 22+ 4DSM: A cI|: 1001-5965(2006) 07-0773-05Precise research on stellar horizon atmospheric refracti
3、on modelHu Jing Yang Bo( SchoolofAstronautics, BeijingUniversity ofAeronautics and Astronautics, Beijing 100083, China)Abstract: The concept of stellar horizon atmospheric refraction is considered to be oneof themostprom-ising concepts for satellite autonomous navigation. However, the precision of t
4、hemethod is lim ited due to theuncertainty of the stellarhorizon atmospheric refractionmode.l According to the rule that atmospheric densitywould varywithaltitude, latitude, season and so on, the fixed altitudemeasurementmodel( 25km) canbe a-vailablymodified. Consequently, the navigation precision a
5、nd dependability can be effectively improved. Bythoroughly studying on the principle of the atmospheric refraction, the stratospheric atmosphere data, the a-tmosphericmodeland other factors related to the precision of themeasurementmode,l a sel-f adapted continu-ous altitude (20 50km) measurementmod
6、elwas established, and then the system modelwith theorbit per-turbationwas establishedaswel.l Finally, a simulation experimentwasperformedbyusing theUnscentedKa-lman Filterprogramme, and an error analysiswas achieved.Key words: aircraf;t navigation; refraction; measurementmode;l orbitperturbationt?1
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8、M9,P;v|W1VVU,V7V;v,4y|t?W1,|;|t?1t1o,Vt?EZ?8$,dLroZE9t?.2 ;|4y;|Gv.bvM,vM|%1#y.-,vs1bopz!W7,K$z9y.7|T(nT(7)VA|M_)v1.yNv;v|.oS=v?UdM,X4KEy.-?XL|.2. 1 v1)SHS,v/TlH = RgTmM 0g + Rg dTmdh(1), Rga8; Tms0S;M0Z)vs0; gF.Xv,Fgs0STm7?3M,H9M7M.L!H (h) = C0 + C1h+ C2h2,u1976MSSvvwLEC0, C1, C2,V7VHhM:H (h) = 7. 6351- 0. 01144h+ 0. 0024h22)vL=ovMd,7vaaM1,vav#XvZ,VvM,LBS=(20 50km),vV$fT3.-PoVvTQ
