机构地区: 空军工程大学航空航天工程学院
出 处: 《空军工程大学学报(自然科学版)》 2004年第4期13-16,共4页
摘 要: 为了保证改装后机翼大梁的承力性能,采用有限元方法对改装部位进行了分析计算,得到了危险部位的细节应力。从某飞机机翼中获取了改装部位的实际结构,并对其进行了全尺寸破坏特性试验,结果表明:计算和试验结果吻合良好,改装后的机翼大梁承力性能满足要求。 In order to keep the mechanical performance of wings in an aircraft, the strengthened part is analyzed by means of FEM, and the maximum stress at this part is gained. On the other hand, a real structure of the modified part is intersected from an aircraft to serve as the test structure. The result indicates that the calculation coincides with the tested result and the load-bearing performance of the modified spar can meet the requirements.
领 域: [航空宇航科学与技术] [航空宇航科学技术]