摘要
为了保证空间站正常运行所需要的大量能源及发射入轨时的较小重量代价,我国空间站采用大面积柔性电池翼的设计方案.大柔性电池翼因其结构复杂且频率极低,在轨运行时又要承受多次大机动过程产生的载荷,各承力组件的强度校核和参数设计成为影响整个空间站任务成败的重要环节.本文从工程应用角度出发建立了空间站柔性电池翼的线性简化模型,计算并分析了柔性电池翼在轨大机动过程中各关键组件的载荷,计算结果可对大柔性电池翼的强度校核和减重设计起到一定指导作用.
In order to ensure the huge energy for normal working of China Space Station and less weight costs in launching,China Space Station adopted the large area flexible solar array（ LAFSA） design scheme. The LAFSA has complex structures and extremely low frequency,and bearing loads produced by multiple large maneuver procedure in orbit running,so the strength check and parameter design for each load-carrying component become very important segments for the mission＇s success or failure of China Space Station. This paper established a simplified linear modal for the flexible solar array of China Space Station from the perspective of engineering applications,and computed the loads of every important component of the flexible solar array in on-orbit large maneuver procedures,which can be used as the instruction for strength check and lightweight design of the LAFSA.
出处
《动力学与控制学报》
2014年第3期230-234,共5页
Journal of Dynamics and Control
关键词
空间站
柔性电池翼
伸展机构
载荷计算
模态综合法
china space station
flexible solar array
deployable mechanism
load computation
modal synthesis method
