【作者】 张华；

【导师】 姚卫星；

【作者基本信息】 南京航空航天大学 ， 飞行器设计， 2012， 硕士

【摘要】 将飞行器结构设计得尽可能地符合理想目标，如质量轻、强度和气动弹性品质满足要求、成本低、耐久性好、寿命长等，一直是结构设计师的愿望。结构优化设计已经受到研究人员的普遍关注。结构优化设计分为尺寸优化、形状优化、布局优化、拓扑优化等。本文针对飞行器结构形状优化问题提出了一种基于有限元分析的结构尺寸和形状并行协同优化方法。将飞行器结构形状优化问题分为尺寸优化和形状优化两个子问题。将设计变量分为尺寸设计变量和形状设计变量，在优化尺寸子问题时，形状设计变量最为状态变量；同样在形状优化子问题时，尺寸设计变量为状态变量。经过一次迭代后，两类设计变量都得到新的值，此时用本文提出的经验中值法协调两类设计变量，而后进入下一次迭代。最优解的判断条件是在每次迭代得到两类优化问题的目标函数值后判断它们的差得绝对值，若符合收敛条件则再判断两类设计变量值得差，只有当两类设计变量也达到收敛条件时认为优化问题得到最优解。由此可见，本文的优化方法总体思路是先将优化问题分为两个独立的子问题：尺寸优化问题和形状优化问题；再将两类问题分别优化；通过经验中值法协调统一每次迭代得两类设计变量值；最后通过两类独立问题的目标函数和设计变量的判定来确认是否达到最优解。本文分别对桁架结构、加筋板结构、复合材料飞机尾翼安定面结构用上述方法进行优化，结果表明该方法对于不同桁架结构形式以及不同载荷工况都有很好的通用性以及实用性，并且对加筋板以及复合材料水平尾翼的优化表明该优化方法对大规模复杂结构同样适用。更多还原

【Abstract】 The structure designers have been devoted to make an air vehicle which is lighter, costing less,longer life. The structure optimization design has been concerned increasingly by the researchers.The structure design optimization contains size optimization, shape optimization, layoutoptimization and topology optimization. In this thesis, a parallel collaborative optimization method ofelement size and structure shape for air vehicle is proposed. The aircraft structure optimization isdivided into size optimization and shape optimization. Meanwhile, the design variables are alsodivided into size design variables and shape design variables. According to the method presented inthis thesis, the shape design variables are as state variables during the size optimization. Similarly, thesize design variables are as state variables during the shape optimization. After one iteration, theexperience middle value method proposed in this paper is used to coordinate two kinds of designvariables to make them consistent. The criterion about optimal solution is that the objective function’sdifference absolute value between two optimization problems’ is less than a given small value. Thiscriterion is also needed for the two kinds of design variables.The optimization design of the truss structure, stiffened plate and the horizontal stabilizer of anairplane are completed based on the above method. The results show that this method is proved to begenerality and practical applicability for different structures, different load cases. The optimizationdesign of stiffened plate and the horizontal stabilizer also prove this method effective.更多还原