摘要
根据星箭连接处受力情况及紧锁装置的特点，分析了星箭连接处发生松动的可能性，导出了星箭紧锁所需包带预紧力计算公式，提出了解决包带应力分布不均匀的方法。通过与两种型号的实验结果对比，证明了本文分析方法的正确性和计算公式的可信性。本文所得结论为包带式星箭紧锁结构设计提供了依据。
According to the force ofconnecting place and feature of the locking device,the possibilities of loosening in the connecting pla ce of the satellite and launchingvehicle are studied in this paper．The formulae of preforce the wrapband needs are obtained by applying the theory of a general force system and friction，The distribution of wrapband stress is analysed，and the method for solving the nonuniform,distribution ofthe stress is put forword．Compard with the experimental results of the two types of thedevice，it is proved that the method of analysis and the formulae of calculation are redable．The conclusions provide a basis for designing the locking structure of a satellite and launching vehicle with wrapband．
出处
《国防科技大学学报》
EI
CAS
CSCD
北大核心
1996年第2期20-25,共6页
Journal of National University of Defense Technology
关键词
星箭紧锁
预紧力
包带式
紧锁装置
火箭
locking of satellite and launching vehicle,wrapband, preforce
