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针对机翼气动压力分布数据的离散性,构造任意点附近区域3种形式的压力场曲面函数,以有限元单元为积分区域积分得到该单元内的集中气动载荷,并将其按照最小变形能原理分配到有限元的节点之上.结合某型飞机的测压试验数据比较3种构造函数法求得的气动累积内力,结果表明构造连续的压力曲面函数求得的气动累积内力符合实际气动力的分布特性,满足实际工程需求.
According to the discreteness of the aerodynamic pressure distribution data of the wing, three types of pressure field surface functions in the vicinity of the arbitrary point are constructed, and the concentrated aerodynamic load is obtained by integrating the finite element element as the integral area. According to the principle of minimum deformation energy Which are assigned to the nodes of the finite element.According to the pressure test data of a certain type of aircraft, the aerodynamic accumulated internal forces obtained from the three constructive methods are compared. The results show that the cumulative internal forces of aerodynamics calculated by the continuous pressure surface functions are in accordance with the actual aerodynamic forces Distribution characteristics to meet the needs of the actual project.