构造法在机翼气动载荷转换中的应用

Application of construction method in aerodynamic load conversion of wings

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.

As to the discreteness of the wing aerodynamic pressure distribution data, three kinds of pressure field curved surface functions around any point are constructed. Taking the finite element as the integration area, the concentrated aerodynamic load of the element is calculated and distributed on the node in the finite element. Combined with the measured pressure test data of an aircraft, the aerodynamic cumulative internal forces obtained by the construction function methods are compared, and the results show that, the aerodynamic cumulative internal forces calculated by constructing continuous pressure curved surface function are in line with the characteristics of the actual aerodynamic forces, which can meet the engineering requirement.