摘要
对铝合金桁条蒙皮结构的承力筒、碳纤维蒙皮桁条结构的承力筒、波纹筒和蜂窝筒的力学性能、制造工艺、研制成本及周期等进行了多方面的综合比较 ,认为承力筒的结构应根据卫星总体构型及其要求、承载能力、经济实力和对有效载荷的适应性等多方面的需求 ,合理和适当地选用承力筒结构。给出了选用卫星承力筒结构的一般原则。
This paper synthetically compares the mechanical characteristics, the manufacturing techniques and the development costs and cycles of the central cylinder of aluminum alloy stringer skin structure and the central cylinder, wave cylinder and honeycomb cylinder of carbon fiber stringer skin structure. It is considered that the central cylinder structure should be selected suitably in terms of the satellite configuration and its requirements, the load bearing capacity, economic strength, the adaptability for payloads and so on. A common principle on selecting satellite central cylinder structure is given.
出处
《上海航天》
2000年第5期34-36,41,共4页
Aerospace Shanghai
关键词
卫星结构
承力筒蒙皮
桁条蒙皮
铝合金
碳纤维
Satellite structure
Skin structure
Stringer skin
Aluminum alloy
Carbon fiber
