Aircraft structural reliability and risk analysis
Aircraft structural reliability and risk analysis
复制标题
飞机结构可靠性与风险分析
DOI：
10.1007/978-94-017-2764-8_3
复制
发表时间：
1987
影响因子：
3.7
通讯作者：
F. H. Hooke
中科院分区：
文献类型：
--
作者：
F. H. Hooke
飞机结构设计的经典程序包括评估在使用寿命期间可能发生的各种载荷情况，估计每种情况下载荷的极值（极限载荷），将其乘以安全系数（通常为 1.5），得到最终设计载荷，并通过计算确保结构避免在极限载荷下发生永久变形，并在最终设计载荷下避免倒塌。
Classical procedures for aircraft structural design involve assessing the various loading situations which may occur during the lifetime, estimating the extreme values of the loads in each of these situations — limit loads — multiplying these by a factor of safety, usually 1.5, to give the ultimate design load, and ensuring by calculation that the structure would avoid permanent deformation at the limit loads, and collapse at the ultimate design loads.