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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 analysis of the functional transformation during the pure bending deformation of the wing when the wingtip is loaded, the formula of bending moment prediction of the inflated wing with pure bending deformation is established. The formula shows that the larger the load at wing tip, The longer the length, the greater the wing tip deformation, and the wing tip deformation and wing tip load quality, wing length linear relationship; inflation pressure, the larger the airfoil cross-sectional area, the smaller the tip deformation, and the wing The amount of tip deformation is inversely proportional to the inflation pressure and airfoil cross-sectional area. In order to verify the correctness of the theoretical analysis results, the wing tip loads of the NACA0012 airfoil were tested in this paper. The experimental results show that the error between the theoretical calculation and the experimental data is within 10% (theoretical calculation is slightly smaller); and in the case of small pressure and large load, the wing bending is the most obvious and the wing elongation is the largest. The error Also the largest, but the overall theoretical calculation results and experimental results are basically the same.