摘要
在传统星座自主定轨中,SST(satellite to satellite tracking)可以同时提供轨道的大小、形状和星座相对方位信息,但不能确定星座的绝对定向。针对这一亏秩问题,联合圆型限制性三体模型CRTBP(circle restricted three bodyproblem)下的一种平动点周期轨道-Halo轨道飞行器,与二体问题轨道卫星组成扩展星座。利用两种力模型的特性差异,可以去除星座系统上的相关性,避免星座的整体旋转,从而确定星座的全部轨道状态参量。分析Halo轨道的力模型及性态特点,从系数矩阵的相关性角度讨论引进Halo轨道对定轨法矩阵正定性的改善作用,利用地月系L1平动点附近的Halo轨道与月球低轨卫星(LMO)的星间链路,在理想CRTBP框架下进行自主定轨仿真。初步验证了LMO-Halo星座定轨可行性,为开展附加平动点轨道的星座SST定轨提供了参考依据。
SST（satellite-satellite tracking） can provide size,shape and relative orientation of the classical constellation satellites,whereas it can not determine the absolute orientation of the constellation.To solve the problem of rank deficiency in SST autonomous orbit determination,spacecraft moving in Halo orbit,a kind of periodic orbits in CRTBP（circle restricted three body problem）,is augmented into the classical constellation.The characteristic differences in force model between Halo orbit and perturbed Kepler orbit can remove the systematic correlation of state parameters of the traditional constellation,and thus prevent the overall constellation from rotating with respect to the inertial space.The mechanisms of force model and spatial configuration of Halo orbiters are analyzed.The multi-colinearity of the coefficient matrix of normal equation is investigated for the classical and libration orbit involved constellations.Some simulations using LMO-Halo crosslink range in CRTBP are designed to test the orbit determination method.The results show that owing to the involved libration orbit,autonomous orbit determination based on SST only,has the feasibility to estimate the absolute orientation of the constellation simultaneously.
出处
《测绘学报》
EI
CSCD
北大核心
2013年第2期184-190,共7页
Acta Geodaetica et Cartographica Sinica
基金
国家自然科学基金(41174025
41174026)
上海市空间导航与定位技术重点实验室开放课题(0901)
中国科学院精密导航定位与定时技术重点实验室开放基金(2012PNTT07)
关键词
圆型限制性三体问题
平动点
星间跟踪SST
HALO轨道
低轨月球卫星
circle restricted three body problem（CRTBP）
libration points
satellite-satellite tracking（SST）
Halo orbit
low moon orbiters（LMO）
