The trajectory deviation analysis of relative motion in closed-loop control system was conducted with the concept of relative reachable domain (RRD),which is a geometric description for the collection of all the possible relative positions.Given that the state error of spacecraft is subjected to arbitrary Gauss distribution,the RRD could be obtained by assembling the time variable error ellipsoids of position.A closed-loop control system for close-range relative motion based on the linearized dynamical model with measurement and control errors was considered in the problem.The covariance matrix of spacecraft state,which defined the error ellipsoid,was analyzed by covariance analysis describing function technique (CADET).An algorithm for solving the envelope of RRD with the state covariance matrix was proposed subsequently.Comparison between the RRDs,solved in both open-loop and closed-loop systems,and the simulation result of 1 000 Monte Carlo runs demonstrates the feasibility and validity of the proposed method.%利用相对可达区(RRD)的概念对航天器在脉冲闭环控制方式下相对运动的轨迹偏差进行了分析.相对可达区是对航天器可能出现位置集合的一种几何描述.当航天器的状态误差服从高斯分布时,相对可达区可表示为随时间变化的误差椭球的集合.考虑航天器飞行过程中存在的不确定性因素,基于闭环控制系统下线性化的相对运动动力学模型,采用协方差分析描述函数法(CADET)对定义航天器误差椭球的协方差矩阵进行了分析,给出了根据协方差矩阵求解相对可达区包络的计算方法.通过将开环和闭环控制系统下的相对可达区包络与1 000次的Monte Carlo仿真结果进行比较,证明了偏差分析方法的适用性与有效性.
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