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在经典工程梁理论的基础上,结合张力薄膜的应力状态分析,提出充气机翼褶皱失稳的判据。计入表面薄膜褶皱引起的刚度退化效应,将机翼等效处理为一个变截面刚度的梁,建立了充气悬臂机翼的等效梁模型,并采用微分求积法进行充气机翼弯曲变形分析。计算结果与充气机翼的静力弯曲试验结果相吻合,验证了充气机翼弯曲变形分析方法的有效性。应用片条理论引入气动力模型,并与所建立的等效梁模型相耦合,建立充气机翼的静气动弹性耦合模型,并用迭代算法进行求解。考虑起皱和失稳两种判据,并计算获取了试验机翼的起皱动压和皱褶失稳动压形式,计算结果与风洞试验结果一致。根据所建立的充气机翼静气动弹性分析方法,可以预测充气机翼表面褶皱区的扩展和弯曲变形,进而绘制充气机翼的静气弹许用包线,为充气机翼的设计提供必要的安全边界参考依据。
Based on the classical engineering beam theory, combined with the stress state analysis of tension film, the criterion for the buckling instability of inflatable wing is proposed. Taking into account the degeneration effect caused by surface film folds, the wing is equivalently treated as a beam with variable cross-section stiffness. The equivalent beam model of the airfoil cantilever wing is established. The differential quadrature method is used to analyze the bending deformation of the inflatable wing . The calculated results are in good agreement with the static bending test of the inflated wing, which verifies the effectiveness of the method for analyzing the bending deformation of the inflatable wing. The aerodynamic model is introduced by using the slice theory and coupled with the established equivalent beam model to establish the static-aerodynamic elastic coupling model of the inflated wing, which is solved by an iterative algorithm. Considering both wrinkling and instability criteria, the wrinkling dynamic pressure and buckling dynamic pressure form of the test wing were calculated. The calculated results are consistent with the wind tunnel test results. According to the established static aerodynamic elasticity analysis of inflatable wing, it can predict the expansion and bending deformation of the inflatable wing surface wrinkle zone, and then draw the envelope of the inflatable wing of the static gas bomb, providing the necessary inflatable wing design Safety boundary reference basis.