一种基于火箭视位置与视速度的航天器初轨确定方法

为了充分利用航天器初始轨道确定的信息源,不断完善地面测控系统定轨手段和方法,提出了一种基于火箭视位置与视速度的航天器初始轨道确定方法.首先对火箭视位置与视速度测量弹道的原理进行了分析;然后利用火箭秒节点计算机字(视速度)以及某一点的初始弹道(初始位置矢量、速度矢量),通过对火箭的运动方程进行逐秒积分,以获得每秒的位置矢量和速度矢量,再转换为弹道数据,并利用此数据直接确定航天器初始轨道.最后通过某太阳同步轨道卫星实测数据仿真计算,证明了方法的正确性和可靠性.

Method of Spacecraft Initial Orbit Determination Base on the Launch Vehicle Apparent Position and Apparent Velocity

To make the best of information source for spacecraft initial orbit determination and to continuously inprove the ground Tracking, Telemetry and Command (TTC) orbit determination means and method, this paper proposes a spacecraft initial orbit determination algorithm based on the launch vehicle apparent velocity. Firstly, the principium of measuring trajectory by use of the launch apparent position and apparent velocity is analyzed. Secondly, using the launch vehicle second node computer word (i.e. apparent velocity) and the initial trajectory of a certain point (initial position vector and velocity vector), the position vector and velocity vector of each second are acquired by means of performing the second-by-second integration of the launch vehicle motion equation, and then converted into the ballistic data to directly determine the spacecraft initial orbit. Finally, simulation result on the real-measure data of a sun-synchronous orbit satellite proves the correctness and reliability of this algorithm.