基于相对轨道根数的航天器编队控制三冲量方法

在采用相对轨道根数描述航天器编队构形的基础上,把航天器平面内编队控制问题转化为航天器交会问题,根据编队构形的几何参数得到解决问题的三冲量控制方法,该方法具有燃料消耗少且只需沿航迹向安装推力器,便于工程应用的优点.最后对推力器的推力大小偏差、方向偏差对编队构形的尺寸以及相位控制精度的影响进行了理论分析.

Three-impulse Method for Formation Control of Spacecraft Based on Relative Orbit Elements

Through the employment of relative orbit elements for describing formation configuration, the problem of planar formation control is transformed to the problem of rendezvous. As a result, a three-impulse method is achieved in the light of geometric parameters of formation configuration which has merits of small fuel consumption and easier engineering implementation. Finally, the influences of the force and direction deviation of thruster on the control precision of size and phase of formation configuration are analyzed.