基于相对偏心率/轨道倾角矢量的分离模块航天器队形设计方法

分离模块航天器是分布式空间系统的一种创新应用。针对分离模块航天器中伴飞模块经典轨道根数设计的问题,本文从运动学角度出发,给出了基于相对偏心率/轨道倾角矢量的分离模块航天器队形设计方法。在已知主模块经典轨道根数的情况下,通过定义的队形参数可以反算出伴飞模块的经典轨道根数,该方法描述简洁,并且具有很高的精度。最后的仿真结果表明了该方法的有效性。

The Design Method of Formation for Fractionated Spacecraft Using an Eccentricity Inclination Vector

Fractionated spacecraft is an innovative application of distributed Space Systems. For the problem of the classic orbit design for the flying around module in fractionated spacecraft, from the kinematic point of view in this paper, the author gives a design method for the formation of the fractionated spacecraft based on an relative eccentricity / inclination vector. Under the condition of the known classic orbit of the main module, classic orbit of the flying around module can be calculated through the defined parameters of formation, this method uses an easy way to describe the formation and has a very high precision. Finaly, the simulation results show the effectiveness of the proposed method.