摘要
基于工程弹性理论,对平流层平台柔性飞艇进行了结构分析.分别运用无矩薄壳理论和虚功原理推导了柔性飞艇应力和总体变形的计算式;将薄膜充气梁挠度计算式进行推广,运用叠加原理推导了柔性飞艇总体变形的解析表达式,计算结果验证了变形计算方法的正确性.给出了飞艇正常设计极限状态临界弯矩与最小气压计算公式.最后,对25 m验证飞艇进行计算,得到了浮心、重心等参数,进行了柔性飞艇的最小压力设计,讨论了飞艇承受的弯矩及其作用下的变形,为验证飞艇的设计提供依据.
On the basis of engineering elastic theory,structural analysis of flexible airship on stratospheric platform was conducted.Using non-moment shell theory and virtual work principle respectively,the envelope stress and overall deflection were formulated for flexible airship.The deflection formula of inflatable fabric beam was extended to calculate the deflection of flexible airship with superposition principle,and the results of these two methods were validated.The critical load-carrying moment and minimum pressure were presented for the airship in normal operation serviceability limit state.Eventually,buoyant center,gravity center,and other parameters of a 25-meterslong demonstration airship were obtained,the minimum pressure of this airship was calculated,and the moment of flexible airship and corresponding deflection were investigated sequentially,providing valuable information for flexible airship designing.
出处
《上海交通大学学报》
EI
CAS
CSCD
北大核心
2010年第11期1583-1587,1594,共6页
Journal of Shanghai Jiaotong University
基金
国家自然科学基金资助项目(50808122)
航天支撑技术基金项目(HT-08-35)
关键词
平流层平台
柔性飞艇
临界弯矩
最小气压
正常设计极限状态
stratospheric platform
flexible airship
critical load-carrying moment
least pressure
operation serviceability limit state
