Orbit Determining Strategy Analysis for BeiDou Satellite in Different Attitude Control Modes
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摘要: 北斗卫星的姿态控制分为动态偏置、零偏置和连续动偏3种，不同类型卫星、不同姿态控制模式、不同时段下定轨精度不一致，影响了北斗系统的连续性。详细研究了北斗不同类型卫星在不同姿态控制模式下的最优定轨策略，并基于实测数据进行试验，结果表明，BeiDou-2 IGSO（inclined geosynchronous orbit）/MEO（medium earth orbit）卫星采用基于星地钟差约束下多星定轨方法和ECOM（extended CODE model）5参数模型相结合的方法定轨精度最优，零偏期间，用户等效距离误差值为2.08 m，全球激光评估轨道视向精度约为1 m；BeiDou-3 IGSO/MEO卫星采用常规多星定轨和ECOM 5参数模型相结合的方法定轨精度最优；连续动偏期间，用户等效距离误差值为1.22 m，全球激光评估轨道视向精度为0.23 m，与动偏期间精度一致；GEO（geostationary earth orbit）卫星在春秋分附近时段采用基于星地钟差约束下多星定轨方法和ECOM 9参数模型相结合的方法定轨精度最优，用户等效距离误差值为0.72 m。Abstract: The BeiDou navigation satellite system have three attitude control modes-yaw-steering(YS) mode, orbit-normal(ON) mode and continuous yaw-steering(CYS) mode. The orbit accuracy and best orbit determination projects for different satellites were a hot topic at present in different time and different attitude control mode, which are researched and whose the dynamical mechanisms is analyzed in this paper. The results are as follows. For BeiDou-2 satellites, multi-satellite precise orbit determination by fixing satellite/station clock offset and extended CODE model (ECOM) 5 SRP should be the best project, user equivalent range errors (UERE) root mean square (RMS) in ON mode is 2.08 m, global satellite laser ranging (SLR) data fitting RMS is ablout 1 m. For BeiDou-3 satellites, multi-satellite precise orbit determination and ECOM 5 SRP should be the best project, UERE RMS in CYS mode is 1.22 m, SLR data fitting RMS is 0.23 m, which is comparable to that in YS mode. For GEO satellites near spring or autumn equinox, multi-satellite precise orbit determination by fixing satellite/station clock offset and ECOM 9 SRP should be the best project, UERE RMS is 0.72 m.
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图 2 C03在秋分附近、C34连续动偏期间UERE图
Figure 2. UERE for C03 Nearby Autumnal Equinox and C34 in Continuous Yaw-Steering Mode
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图 4 北斗卫星在不同姿控模式下的激光残差图
Figure 4. SLR Residuals in Different Attitude Control Modes for BeiDou Satellites
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图 5 春分期间GEO卫星两种钟差互差的STD
Figure 5. STD of the Differences Between Satellite Clock Offset by MPOD and TWSTFT at Spring Equinox Period
表 1 动偏、零偏、连续动偏IGSO/MEO卫星受照状态比较
Table 1 Solar Irradiation on IGSO/MEO Satellites in Different Attitude Modes
工作方式 偏航姿态 星体面板 太阳帆板 动偏 偏航角随太阳位置连续变化 对地面板(+Z轴)、背地面板(-Z轴)轮流受照，东面板(+X轴)始终受照，南北面板(+Y和-Y轴)不受照 太阳光线垂直入射 零偏 偏航角恒为0° 对地面板(+Z轴)、背地面板(-Z轴)轮流受照, 东西面板(+X和-X轴)轮流受照, 南面板(+Y轴)或北面板(-Y轴)部分受照 太阳光线与太阳帆板法向夹角不超过5° 连续动偏 正常时段偏航角随太阳位置连续变化，正午和子夜附近采用偏航机动 对地面板(+Z轴)、背地面板(-Z轴)轮流受照，东面板(+X轴)始终受照，南面板(+Y轴)或北面板(-Y轴)部分受照，西面板(-X轴)不受照 太阳光线与太阳帆板法向夹角不超过5° 
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表 2 GEO卫星在非地影期和地影期星体面板受照状态比较
Table 2 Solar Irradiation on GEO's Body in and not in Earth Eclipsing Period
+X和-X面板受照情况 +Y和-Y面板受照情况 +Z和-Z面板受照情况 非地影期 +X面与-X面受太阳照射的时间相等，为轨道周期(设为T)的一半 整个轨道周期内Y面板均受照，β>0°时，-Y面受照，β < 0°，+Y面受照 +Z面与-Z面受太阳照射的时间相等，为轨道周期(设为T)的一半 地影期(春秋分附近时段) +X和-X面受照时间依然相等，但受照时间均小于T/2 Y面板在轨道周期内并非全弧段受照，卫星进地影后，+Y和-Y面板均不受照 +Z和-Z面受照时间依然相等，但受照时间均小于T/2
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表 3 连续动偏期间基于不同光压模型的UERE精度比较/m
Table 3 UERE by Different Solar Radiation Pressure Models in Continuous Yaw-Steering Mode/m
卫星 ECOM 9 ECOM 5 T20 C31 1.85 1.28 1.36 C33 1.79 1.23 1.30 C34 1.60 1.15 1.21 平均 1.75 1.22 1.29
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表 4 北斗GEO卫星基于不同定轨模式的UERE精度比较/m
Table 4 UERE by Different POD Projects for GEO Satellite/m
卫星 模式1 模式2 模式3 C01 1.86 0.51 0.47 C02 2.10 0.77 0.72 C03 2.54 0.82 0.75 C04 2.31 0.75 0.73 C05 1.85 1.28 0.95 平均 2.13 0.83 0.72
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