摘要
航天器轨道精确测定重要环节之一是有效地消除观测系统误差，在轨道测量数据处理时，一类是利用轨道约束自校准技术来估算和校准系统误差，另一类可以应用测元差分方法来消除系统误差（例如导航卫星测定目标）。本文提出一种新的差分技术，即利用观测数据时序差分消除系统误差技术，并推导相应确定航天器轨道的公式。
One of the most important processes for accurate determination of spacecraft orbit is to eliminate observation system error. One type of orbit measurement data processing is using EMBET of orbit restraint to estimate and adjust system error and the other is using element reference to estimate and adjust the system error. This paper introduces a new type of differential technology that uses observation data scheduling reference to eliminate system error. A formula associated with the technology is derived for spacecraft orbit determination.
出处
《飞行器测控学报》
2006年第4期32-34,共3页
Journal of Spacecraft TT&C Technology
关键词
轨道测量
差分技术
差分方程
轨道状态参数
, Orbit Measurement
Differential Technology
Differential Formula
Orbit State Parameters
