CAJ | 학술논문

文章对半长轴、偏心率、倾角、升交点赤经相近的两航天器的远距离轨控接近方案进行了理论分析.首先研究了通过改变轨道半长轴调整航天器升交点赤经变化率,进而控制轨道法向振幅的方法;其次给出控制点的选择时机与相对绕飞椭圆大小的定量关系;然后提出采用径向矢径模之差估计远距离相对运动参数方法;最后通过"神舟七号"伴星与轨道舱的远距离接近及绕飞控制仿真对理论推导进行了验证.
문장대반장축、편심솔、경각、승교점적경상근적량항천기적원거리궤공접근방안진행료이론분석.수선연구료통과개변궤도반장축조정항천기승교점적경변화솔,진이공제궤도법향진폭적방법;기차급출공제점적선택시궤여상대요비타원대소적정량관계;연후제출채용경향시경모지차고계원거리상대운동삼수방법;최후통과"신주칠호"반성여궤도창적원거리접근급요비공제방진대이론추도진행료험증.
The orbit control technology of two long-distance satellites with similar semi-major axis, eccentric angle and inclination RAAN was analyzed. First, a new method of controlling the swing of orbit normal axis by changing the semi-major axis to adjust the change rate of RAAN was studied; secondly, the relationship between the control time and the size of relative ellipse was given; thirdly, the method of estimating the parameter of the relative ellipse by the module difference of radial vector was put forward; finally, the proposed methods were verified by the long-distance approaching and companion flying simulation of SZ-7 companion satellite and orbital module.