组合航天器转动惯量在轨两步辨识标定

在轨辨识转动惯量参数是主动航天器与非合作空间目标构成组合体后实现高精度姿态控制的重要前提，文章提出了一种两步在轨辨识组合航天器转动惯量参数的方法。第一步以航天器本体坐标系滚动轴转动惯量为基准将转动惯量矩阵归一化，得到特殊的转动惯量比矩阵，建立与其相关的姿态动力学模型，提出了基于扩展卡尔曼滤波的在轨辨识算法，基于星上陀螺角速率测量信息在100s左右辨识出所有转动惯量比参数，克服了由于模型简单导致转动惯量信息辨识不完整的缺点；第二步基于第一步辨识得到的转动惯量比参数，采用最小二乘算法辨识得到滚动轴转动惯量值，计算量小，消耗能量少。最后给出仿真算例，辨识精度基本在1|之内，验证了方法的有效性。

On-orbit Calibration Technique Based on the Two-step Moment of Inertia Identification of the Combination Spacecraft

On-orbit identification of the moment of inertia parameters is an important prerequisite to achieve high-precision attitude control of the combination which is combined by the active spacecraft and non-cooperative space target.With that combination,a method for on-orbit identification of inertia parameters in two steps was proposed.The first step,making the moment of inertia of X axis as a benchmark normalized the spacecraft moment of inertia matrix in order to get the special combination of inertia ratio matrix.Then the spacecraft combination attitude dynamics model was established.Based on the angular rate measurement information given by a star gyro,the extended Kalman filter method was proposed to identify all the inertia ratio parameters in about 100s and overcome the shortcomings which the simple model cannot completely identify the rotational inertia parameters information.The second step,according to the identification of the inertia ratio matrix in the first step and using the least squares algorithm,the X axis moment of inertia was obtained.The simulation example verifies the effectiveness of the method,and the identification accuracy is about 1%.