摘要
在对某型飞机襟翼卡阻可靠性分析的基础上,结合可靠性要求计算出有限元模型结点的位移限作为约束条件,利用MSCNastran的优化模块对该型襟翼进行基于可靠性的刚度优化,给出了满足可靠度要求下的蒙皮厚度,对该型飞机襟翼的改设计有一定的参考价值。
The purpose of this paper is to study the change design of an aircraft＇s flap structure. A jamming reliability analysis of an aircraft is conducted,and the result shows that the deformation of the former structure cannot meet the reliability requirements. The deformation values of the flap structure which can meet the reliability requirements are calculated,and those values are treated as constraints. The objective function is structure weight,and the design variable is skin thicknesses. Then,the MSC Nastran optimization module is employed to conduct reliability-based stiffness optimization. The best value of design variable which can meet the reliability requirements is given; the necessity and rationality of change design are explained from the seaworthiness. The innovation of this paper is that the concept of reliability is adopted in the process of optimum design of flap structure.
出处
《机械科学与技术》
CSCD
北大核心
2010年第8期1076-1079,共4页
Mechanical Science and Technology for Aerospace Engineering
基金
国家自然科学基金项目(10577015)
航空科学基金项目(2006ZD53050
2008ZD53006)资助
关键词
襟翼
可靠性
刚度
优化
flap
reliability
stiffness
optimization
