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现代航天任务中,各类航天器由于工作的需要必须进行适时的变轨或进行其它轨道机动。由于这些轨道机动的动作导致前后数据不能有效的拟合,降低了定轨精度。为此,建立了适用于各类航天器轨道机动的动力学模型,通过运用测轨数据使用数值积分方法求解各类模型参数,着重探讨近地航天器的轨道机动的影响,并主要使用GPS导航定位数据分析其精度,实现了轨控参数的求解标定,同时提高了短弧段的定轨能力和预报精度。
In modern space missions, all kinds of spacecraft must undergo proper orbit changes or other orbital maneuvers due to their work needs. Due to these orbital maneuvers leading to data before and after the effective fitting, reducing the orbit accuracy. For this purpose, a dynamic model suitable for orbital maneuvering of various spacecraft was established. The numerical integration method was used to solve various parameters of the model by using the orbital data. The effects of orbital maneuver of the near spacecraft were mainly discussed. GPS navigation Positioning data analysis of its accuracy, to achieve the trajectory control parameters of calibration, and improve the short arc orbit determination and forecast accuracy.