航天器姿轨控始末时刻的动力学标定方法

Dynamic Detection Algorithm for Spacecraft Attitudinal Control and Orbital Control Epoch

航天器姿控和轨控始末时刻的精确标定,是精确模制机动过程的基础。本文针对传统χ2检验法对模型小异常不敏感,提出了移动窗口的多步检测量和双检验因子,通过调节高、低置信因子的大小,提高检验量敏感性的同时,可保证检验结果的可靠性,从而实现航天器姿控开始时刻的精确标定。通过建立线性姿控力和平均化的轨控推力,对姿控和轨控过程进行概略补偿,标定轨控始末时刻,实现姿控、轨控和巡航过程的剥离。本文以CE-1第3次近月轨道机动为例,采用国内VLBI网的监测数据,验证了该方法对姿控轨控始末时刻的在线标定。

The detection of spacecraft attitude control and orbital control epoch is of great importance for modeling the orbital maneuver process. Since the traditional residualsx2detection method is insensitive to small model fault, a multi-dimensional statistical test method is proposed using double test confidences in the moving window. The proposed method is able to enhance statistic sensitivity by adjusting the values of the two confidences and the reliable test solution can then be used to detect attitude control beginning epoch accurately. In order to further detect orbital control epoch, a linear attitude control force model and an orbital control thrust model are presented to roughly compensate the maneuver process. Taking the third lunar orbital brake process of CE-1 as example, the proposed method is validated to detect attitude control and orbital control epoch nearly in real-time with observations from domestic VLBI network .