摘要
通过对飞机襟翼卡阻可靠性分析,把对卡阻失效起主要作用的前梁、前缘蒙皮及内端肋作为优化对象,根据适航条例要求计算出失效点处的临界卡阻约束位移;基于MSC.Patran&Nastran软件对襟翼结构进行卡阻约束下的优化,得出满足卡阻约束条件下的襟翼结构优化设计方案。
By the blocked reliability analysis of a certain type of aircraft flaps,the first beam,the leading edge skin and inner side ribs which play the major role in blocked failure were selected as the optimization objects.According to airworthiness regulations requirement,the critical displacement conditions of the blocked failure point was worked out.Basing on MSC.Patran & Nastran software,flap structural was optimized under the blocked constraints,and the optimization program has been obtained to fulfill the blocked constraints.
出处
《机械设计与制造》
北大核心
2010年第12期32-34,共3页
Machinery Design & Manufacture
基金
国家自然科学基金(10577015)
航空基金(2006ZD53050)
航空基金资助(2008ZD53006)
