机翼重量分配方法在轻型飞机中的应用

Methods of Wing Mass Distribution in Light Aircraft Design

针对目前飞机初始设计阶段的机翼重量估算公式变量较多,条件限制因素较复杂的情况,提出了一种按照机翼重量分配来估算重量的方法。把机翼重量分配到:承弯结构、承剪结构、分布气动载荷结构、起落架影响结构、前后缘结构、襟副翼机构,燃油影响结构、以及其它附属结构。此方法已经在大型飞机的机翼重量估算上取得了良好的效果。通过与一系列常用机翼重量估算公式的对比分析,并且利用已知的10种轻型飞机完成了算例,结果证明此方法有很强的适应性。

As the fact of excessive variables and complicated resistances in traditional wing weight prospect in light aircrafts design, a method of light aircraft wing mass estimation formulas base on wing structure distribution has been presented. The wing structure contains parts as follows：bending structure, shear structure, aerodynamic load distributing structure, landing gear mount affected structure, fuel tank mount affected structure, landing gear mount affected structure, leading edge structure trailing edge structure ,flap structure, aileron structure, wing-body joint structure and other miscellaneous structure. The method has been proved to be highly precise in fighter and large transporter wing weight estimation. After comparing with other four weight estimation formulas by using 10 known aircrafts＇ date,we are so glad to find an identical result.