CAJ | 학술논문

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.
수공위성동역학모형중추력가속도적량급원원고우기타섭동적오차량급,관측량주요반영수공위성동역학모형적오차.본문이근종화정학정위공간궤동목표위목적,급출기우지면뢰체관측,실시고계추력가속도,수정위성동역학모형적궤도학정산법.통과건립련속추력공제과정변질량동역학모형,급출상추력변가속도만족적운동학미분방정;건립변가속도고계계통상태방정,화확전잡이만려파궤도학정산법;병급출련속추력공제위성운동상태관우추력가속도적변분운동방정;실제비행공제응용표명:이용지면측량수거,실시고계추력가속도병보상계통동역학모형,해결료련속수공위성궤도정학학정문제.
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.