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针对某空间飞行器在轨运行时转动惯量变化大的特点,对其转动惯量的在轨估计方法进行了研究。基于姿态动力学模型建立状态方程,用陀螺测得的角速度、推力标称值和推力作用点的位置信息构造量测,用最小二乘法估计转动惯量。仿真结果证明了算法的有效性,误差小于5%。估计算法计算简单,估计时间和所用燃料消耗少,工程上易于实现。
Aiming at the large variation of moment of inertia of a spacecraft in orbit, the in-orbit estimation method of its moment of inertia is studied. The state equation is established based on the attitude dynamics model, the angular velocity, the nominal value of the thrust and the position information of the thrust point are used to construct the measurement, and the moment of inertia is estimated by the least square method. The simulation results show that the algorithm is effective and the error is less than 5%. The calculation of the estimation algorithm is simple, the estimation time and the fuel consumption are less, and the engineering is easy to realize.