运载火箭发射窗口的一种计算方法  

A Computational Method for Carrier Rocket Launch Window

作　　者：李伟建[1] 刘旭光 刘兴威[1] 李伟 LI Wei-jian;LIU Xu-guang;LIU Xing-wei;LI Wei(Jiuquan Satellite Launch Center,Jiuquan Gansu 732750,China)

机构地区：[1]酒泉卫星发射中心,甘肃酒泉732750

出　　处：《计算机仿真》2023年第12期65-68,共4页Computer Simulation

摘　　要：发射窗口的计算对于发射活动而言是一项重要的内容,决定着航天器是否能准确入轨。提出一种基于几何方法的发射窗口计算方法,首先通过轨道递推模型计算卫星轨道平面的法向矢量,再根据入轨点大地坐标以及坐标系间的转换关系求得入轨点地心矢量,两矢量垂直的时刻即为发射窗口前沿。通过与STK仿真计算结果对比发现,在给定的一个计算时长内两者误差相当小,并在一定范围内变化。上述方法用于常规航天发射任务发射窗口的计算,逻辑清楚,简单实用。The calculation of the launch window is an important aspect for launch activities,and it decides wheth⁃er the spacecraft can enter orbit accurately.A method for calculating the launch window based on the geometric meth⁃od is presented.The normal vector of the satellite orbit plane was first calculated by using the orbit propagation mod⁃el,and then the earth center vector of the injection point was obtained according to the geodetic coordinates of the in⁃jection point and the transition relationship between the coordinate systems.The vertical moment of the two vectors is the front of the launch window.Comparing with the STK simulation results shows that the error between theory calcu⁃lation and simulation calculation is quite small within a given computational length and it varies over a certain range.When the proposed method is used for the calculation of the launch window for conventional space launch missions,its logic is clear and itself is simple and practical.

关 键 词：发射窗口 轨道递推 轨道平面 平面窗口 

分 类 号：V417.9[航空宇航科学与技术—航空宇航推进理论与工程]