编队飞行卫星相对半长轴的变化分析和应用  

Analysis and application of relative semi-major axis variation for formation flying satellites

作　　者：高燕 苏鹏 陈宁 杨钊 王莉 张玮[2] Gao Yan;Su Peng;Chen Ning;Yang Zhao;Wang Li;Zhang Wei(State Key Laboratory of Astronautic Dynamics,Xi’an 710043,China;DFH Satellite Co.,Ltd.,Beijing 100094,China)

机构地区：[1]宇航动力学国家重点实验室,西安710043 [2]航天东方红卫星有限公司,北京100094

出　　处：《国外电子测量技术》2021年第8期156-160,共5页Foreign Electronic Measurement Technology

摘　　要：针对某编队飞行卫星控制频次高、控制难度大的问题,分析了卫星间相对运动规律,建立了平面内相对距离、平面外相对距离、相对相位、相对升交点赤经与相对半长轴的数学模型。仿真了某编队飞行卫星副星与主星的相对半长轴变化规律,并通过实际在轨控制对仿真结果进行验证。验证结果表明,选择合适的相对半长轴作为目标控制量,在地球非球形摄动J2项影响下,主副星间相对位置变化情况满足仿真分析结果,在确保星座构型满足载荷使用的约束条件下,极大的降低了星座构型保持的控制频次。In order to solve the problem of high frequency and difficult control of a formation flying satellite, the relative motion law between satellites is analyzed, and the mathematical models of relative distance in plane, relative distance out of plane, relative phase, relative right ascension and relative semi major axis are established. The variation law of the relative semi major axis between the secondary satellite and the primary satellite of a formation flying satellite is simulated, and the simulation results are verified by the actual in orbit control. The verification results show that the relative position changes between the primary and secondary satellites meet the simulation analysis results under the influence of the non spherical perturbation J2 term of the earth, and the control frequency of the satellite is greatly reduced under the condition of ensuring that the constellation configuration meets the constraints of the payload.

关 键 词：编队飞行卫星 相对半长轴 多星协同载荷任务 构型保持 

分 类 号：V557.3[航空宇航科学与技术—人机与环境工程]