动力学补偿受控卫星轨道确定算法(英文)  

A Dynamic Model Compensation Orbit Determination Method for Maneuvering Satellite

作　　者：李恒年[1,2] 李济生[1,2] 黄永宣[2] 

机构地区：[1]中国西安卫星测控中心宇航动力学国家重点实验室,西安710043 [2]西安交通大学系统工程研究所,西安710048

出　　处：《宇航学报》2010年第10期2269-2275,共7页Journal of Astronautics

基　　金：国家 863 基金( 2010AA7041014)

摘　　要：受控卫星动力学模型中推力加速度的量级远远高于其他摄动的误差量级,观测量主要反映受控卫星动力学模型的误差。本文以跟踪和精确定位空间机动目标为目的,给出基于地面雷达观测,实时估计推力加速度,修正卫星动力学模型的轨道确定算法。通过建立连续推力控制过程变质量动力学模型,给出常推力变加速度满足的运动学微分方程; 建立变加速度估计系统状态方程,和扩展卡尔曼滤波轨道确定算法; 并给出连续推力控制卫星运动状态关于推力加速度的变分运动方程; 实际飞行控制应用表明: 利用地面测量数据,实时估计推力加速度并补偿系统动力学模型,解决了连续受控卫星轨道精确确定问题。The uncertainty of thrust acceleration will cause enormous error to model and track the accelerating spacecraft,it’s reasonable to assume that the measurements mainly reflect the uncertainty of the thrust acceleration. This paper focuses on modeling and building on-line filter to identify the continuous thrust acceleration to compensate the uncertainty of the force model during the maneuver process,an elegant differential equation is derived for variable acceleration,an Extended Kalman Filter （ EKF） is developed for dynamic system to identify forwardly the variable acceleration in real time, also the variational equation for the measurement vector to acceleration is detailed to linearise the discrete-time measurement equations. The mission flight scenery shows the algorithm developed here can estimate the acceleration and determine the orbital parameters precisely during the continuous thrust maneuver process.

关 键 词：受控卫星 参数估计 轨道确定 轨道机动 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]