Novel orbit-attitude combination mode for solar power satellites to reduce mass and fuel  

作　　者：Qingjun LI Yi WEI Zhigang WU Jianping JIANG 

机构地区：[1]School of Aeronautics and Astronautics,Sun Yat-sen University,Shenzhen 518107,China [2]School of Medical Information Engineering,Jining Medical University,Rizhao 276826,China

出　　处：《Chinese Journal of Aeronautics》2022年第8期132-142,共11页中国航空学报（英文版）

基　　金：supported by the Guangdong Basic and Applied Basic Research Foundation(2019A1515110730)。

摘　　要：Solar power satellite receives great attention because it can release the energy crisis and environmental problems in the future.However,the launch and maintenance costs are tremendous due to the large system mass and large fuel consumption to counteract space perturbations.To reduce mass and fuel,a novel quasi-Sun-pointing attitude in Sun-frozen orbit is proposed.The Sun-frozen orbit has a nonzero eccentricity vector that always points towards the Sun.The quasi-Sun-pointing attitude is a periodic solution of the Sun-pointing attitude angle.Although about 3%electricity must be given up because of the variation of Sun-pointing attitude angle,little control action is required to deal with the solar radiation pressure and gravity-gradient torque.The algorithm to obtain initial conditions is proposed.The influences of system parameters and structural flexibilities are studied.Simulation results reveal that the quasi-Sun-pointing attitude in Sunfrozen orbit dramatically reduce fuel consumption,the dry mass,and complexity of the control system.In addition,structural vibration is hardly induced by the gravity-gradient torque.Thus,the bending stiffness as well as the mass of the supporting structure can be reduced.

关 键 词：Gravity gradient torque Quasi-Sun-pointing attitude Solar radiation pressure Space solar power station Sun-frozen orbit 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计] V474.2