充气式机翼弯矩预测公式的建立与实验验证

The establishment and experiment verification of the bending moment prediction formula of inflatable wing structure

基于对充气机翼翼尖加载时机翼发生纯弯曲变形过程中功能转换关系的分析,建立了充气机翼发生纯弯曲变形时的弯矩预测公式,该式表明:机翼翼尖处加载载荷越大、长度越长,机翼翼尖变形量越大,并且翼尖变形量与翼尖加载质量、机翼长度呈线性对应关系;充气压强、翼型截面积越大,翼尖变形量越小,并且翼尖变形量与充气压强和翼型截面积呈反比例函数关系。为验证理论分析结果的正确性,本文进行了NACA0012翼型充气机翼的翼尖载荷实验。实验结果表明:理论计算值与实验数据之间的误差都在10%以内(理论计算值略小);并且在小压强、大加载时由于机翼弯曲最明显、机翼伸长量最大,误差也最大,但总体上理论计算结果与实验结果基本一致。

Based on the principle of energy conservation,a bending moment prediction formula of the inflatable wing structure is established when the pure bending deformation occurs in the inflatable wing under a concentrated load at the tip of the wing.The formula shows that: the greater the load at the wing tip is,the longer the length of the wing is,and the larger the wing tip deforms,and they relate each other linearly.To verify the theoretical analysis results,an inflatable wing of NACA0012 airfoil tip static load experiment is conducted.The results show that: the error between the experimental data and the theoretical calculation is within 10%,and under the greater load and smaller pressure the Wing tip deformation is more obvious.The theoretical analysis results presented in this paper is well consistent with the experimental results.