摘要
针对嫦娥三号探测器的连续姿控喷气对飞行轨道产生的扰动影响,在精密定轨中建立了经验力补偿模型,并使用最小二乘估计算法计算经验力模型参数与探测器轨道。通过重叠弧段轨道精度评估法对该模型补偿效果进行了验证,结果显示,定轨预报的星历误差以及拟合残差均有所改善,特别是环月轨道的定轨精度由百米量级提高到十米量级。
The continuous attitude control jet propulsion of Chang＇e 3 probe has disturbing force effect on the probe orbit, in this paper an empirical force compensation model is added to the high accuracy orbit determination model. The empirical model parameter and the probe orbit are calculated by the weighted least squares estimation algorithm. The new model is verified by assessment of overlapping arctraek accuracy. The result shows that both the orbit ephemeris errors and the fitting residuals of forecasted orbit are improved, and the orbit determination accuracy is enhanced from 100 m to 10 m.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2015年第5期489-495,共7页
Journal of Astronautics
基金
国家自然科学基金(11173005
11373013
11203003
11303001)
关键词
嫦娥三号
姿控喷气
轨道动力学
模型补偿
Chang＇e 3 probe
Attitude control jet
Orbit dynamics
Model compensation
