近地轨道电磁编队飞行相对轨道动力学建模

Relative orbital dynamics to LEO electromagnetic formation flying

摘要:

本文将电磁力引入编队飞行应用中,在考虑地球扁率和大气摄动情况下,建立了电磁编队飞行相对轨道动力学模型．基于磁偶极子假设,推导了编队飞行任意两颗卫星间电磁力模型,采用Hill方程的形式给出了电磁编队飞行的相对轨道动力学表述．分别对编队飞行任意两颗卫星间电磁力、大气阻力以及地球扁率摄动进行线性化,得到了电磁编队飞行线性化相对轨道动力学模型．仿真结果表明,线性化相对轨道动力学模型合理可行,与非线性模型相比,运行3圈后误差为0.05～5 m,误差主要来自于电磁力线性化．

Abstract:

Taking account of earth oblateness and atmospheric drag, this article established the relative orbital dynamics for electromagnetic formation flying. The model of electromagnetic force is derived by the dipole approximation of the coils, and the relative orbital dynamics of EMFF is derived by Hill equation. Utilizing the linearization of electromagnetic force between any two satellites, atmospheric drag and earth oblateness, the linear relative orbital dynamics is presented. The results indicate that the linear relative orbital dynamics is reasonable and feasible. Compared to the nonlinear dynamics, the error of 3 revolution is about 0.05 m~5 m, which is resulted from the linearization of electromagnetic force. 