连续推力非合作航天器切向加速度预辨识方法  

Tangential acceleration pre-identification of continuous thrust non-cooperative spacecraft

作　　者：郭雯 胡敏 陶雪峰 GUO Wen;HU Min;TAO Xuefeng(Space Engineering University,Beijing 101416,China)

机构地区：[1]航天工程大学,北京101416

出　　处：《航天控制》2025年第1期62-67,共6页Aerospace Control

摘　　要：针对非合作连续小推力机动航天器定轨问题,提出了一种基于单弧段轨道确定的推力加速度快速预辨识方法。该方法基于卫星轨道参数变化与加速度大小的关系,利用具有一定时间间隔的两次雷达观测数据的单弧段定轨结果,反解连续切向推力作用下航天器切向加速度,在短时间稀疏数据条件下保持较小的求解误差。将其分别应用于Starlink和OneWeb的轨道爬升过程中,结果表明,观测间隔分别大于11 h和15 h时,本文提出的方法能够实现Starlink和OneWeb卫星切向加速度的快速预辨识,求解误差在2%以下。计算结果可作为初值应用于连续小推力机动航天器的精密定轨中。Aiming at the orbit determination of non-cooperative continuous low-thrust maneuvering spacecraft,a rapid pre-identification method of thrust acceleration based on single-arc orbit determina⁃tion is proposed.Based on the relationship between satellite orbit parameters and acceleration,the single-arc orbit determination results of two radar observations with a certain time interval are used to inversely solve the tangential acceleration of the spacecraft under continuous tangential thrust,and fairly smaller solution error is remaining under the condition of sparse data in a short time by using this method Which is applied respectively to the orbital climb of Starlink,OneWeb and the Qianfan constellation.The results show that when the observation interval is greater than 11 h and 15 h separately,the proposed method can realize the rapid pre-identification of the tangential thrust acceleration of Starlink and OneWeb satellites,and the solving error is less than 2%.The calculation results can be used as initial values for precise orbit determination of continuous low-thrust maneuvering spacecraft.

关 键 词：连续小推力 切向加速度 轨道确定 雷达观测 

分 类 号：V474.1[航空宇航科学与技术—飞行器设计]