飞机总体设计阶段机翼结构质量分配方法研究

提出了一种机翼结构质量分配方法，能根据飞机总体设计参数，把机翼结构质量分配到承弯结构、承剪结构、分布气动载荷所需结构、起落架安装影响结构等12个功能结构部分。建立了飞机总体设计阶段机翼结构质量分配的分析模型，然后根据现有飞机机翼的质量和飞机总体几何参数，用参数优化方法确定了该分析模型中的结构修正系数，从而得到一个机翼结构质量分配模型，用8架飞机的机民办所完成的算例证明了该方法的有效性和合理性。

A Method for Wing Functional Structural Weight Distribution in Aircraft Configuration Design

A method for wing functional structural weight distribution in aircraft configuration design is presented. The data of 8 fighter wings are used to produce this method. First, a weight function based on mechanics is produced to identify a suitable model function for the functional weight estimation. Geometric and loading parameters that are likely to appear in the weight function model are also identified. The wing weight function model consists of 12 parts: bending structure, shear structure, aerodynamic load distributing structure, landing gear mount affected structure, store mount affected structure, fuel tank mount affected structure, leading edge structure, trailing edge structure, flap structure, aileron structure, wing-body joint structure and other miscellaneous structures. The fundamental wing box weight equations are sensitive to all the major design parameters such as aspect ratio, sweep angle, wing area, thickness／chord ratios, loading conditions, etc. They are explicit equations having a theoretical basis and are not simple statistical fits. Second, the parameter optimization method is used to fit a non-linear weight function model to data gathered from 8 present fighter wings. Several techniques are employed in order to minimize the number of required present fighter wings and to maintain good accuracy. Next, several analysis techniques are used to find regions of the design space where reasonable fighter wing designs could occur. 　　At last, the method of the wing functional structural weight distribution produced in this paper can be directly used for conventional-style fighter′s preliminary design.