基于微分求积法的高超声速机翼蒙皮颤振研究

机翼蒙皮在高超声速气流中会发生颤振等气动弹性问题,破坏结构.引入微分求积方法,可以有效地分析机翼蒙皮的颤振问题.将机翼蒙皮等效成薄板,基于一阶活塞理论,根据克希霍夫假设及弹性理论建立蒙皮的气动弹性偏微分方程,采用微分求积法将偏微分方程离散为常微分方程,并根据频率重合理论对颤振问题进行求解.得到的颤振速度与有限元方法计算结果进行比较,误差为0 58％,验证了微分求积法在求解颤振偏微分方程时的有效性.分析了蒙皮面积、厚度、纵横比等不同参数对蒙皮颤振速度的影响.结果表明,颤振速度随蒙皮面积的增大而减小,随纵横比、厚度的增大而增大.

Flutter analysis of hypersonic airfoil skin by differential quadrature method

Flutter analysis plays a vital role in the design of hypersonic airfoil skin.This research introduces the differential quadrature method into the aeroelastic problem of hypersonic skin.The aeroelastic model was presented based on the elasticity theory,and the hypersonic piston theory was used for the modeling of supersonic aerodynamic loads.The validity of the differential quadrature method was confirmed by comparing the FEM solutions for the natural frequencies and the flutter velocity of the airfoil skin,and the relative error is 0.58%.A detailed parametric study was carried out to study the influences of the thickness,area and aspect ratio on the hypersonic flutter behavior of airfoil skins.The result shows that,the flutter velocity increases with the aspect ratio and thickness increased,and decreases with the area increased.