摘要
根据大气阻力对卫星编队的影响,为了保持伴飞运动的长期稳定,采用改变卫星面质比的被动式轨控方法。针对如何具体改变卫星面质比的问题,推导了一种太阳能帆板固定的卫星构型中姿态与面质比的数学关系,并建立了优化模型。根据面质比保持和改变的不同需要,设计了对地稳定模式、偏置稳定模式及姿态机动模式等三种姿态控制模式。通过其在Matlab平台上数值仿真,结果表明方法可有效改变卫星面质比实现姿轨控一体化设计;同时可以在保证面质比达到期望值的前提下,使得太阳能帆板朝向太阳。
A passive method utilized the atmosphere disturb force is often used to control the orbit of satellite formation flying for stability. Adjusting area-mass-ratio is necessary for this method. The paper treats a satellite powered by an unmovable solar plane with a desired area-mass-ratio and describes a method to realize the change of area-mass-ratio by controlling the attitude of deputy satellite with considering the orientation of solar plane. The relation between the attitude and the area-mass-ratio is derived. The simulation shows that the method is feasibility and validity.
出处
《计算机仿真》
CSCD
北大核心
2010年第9期66-69,共4页
Computer Simulation
基金
中国科学院知识创新工程领域前沿项目:航天器伴星长期稳定伴飞的轨道和姿态控制方法研究
关键词
伴随卫星
面质比
优化
太阳能帆板
Deputy satellite
Area-mass-ratio
Optimal
Solar panel
