运载火箭外测弹道截断误差的洁化插值修正算法研究

Correction Algorithms to Truncation Error in Trajectories of Carrier Rocket

由于运载火箭飞行过程的复杂性,特别是多级发动机点火与关机的影响,采用曲线拟合微分平滑方法计算弹道参数不可避免地会有截断误差,对于位置和速度变化剧烈的弹道段,更是存在较大的截断误差。为能正确反映目标飞行轨迹,得到精确的弹道参数,必须对其进行修正。本文结合航天靶场外测数据处理工作的实际,构建了洁化插值截断误差修正算法,并利用实测数据仿真分析了方法的有效性和可行性。

Due to the complexity of the flight process of carrier rocket, particularly the ignition and shut-downs of stage-motor, truncation error will be brought when adopting the differential smoothing method to determine trajectory parameters. Truncation error becomes higher at those sections with strenuous changes of its positions and velocities. Correcting is performed to obtain a more precise trajectory and accurate ballistic parameters. Based on practical ballistic data processing, this paper proposes a cleaning inserted algorithm to correct truncation errors. Through simulating practical measuring data, results validate the effectiveness and feasibility of new algorithms.