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以氢动力超长航时无人机(UAV)为背景,针对其大展弦比轻质复合材料机翼,采用强耦合方法求解了几何非线性变形下的静气弹特性,对比了弹性机翼与刚性机翼的气动性能,并在此基础上,给出了一种刚性机翼的弹性气动力修正方法。结果表明:相比刚性机翼,弹性机翼巡航状态下的升阻比降低3.2%,滚转力矩导数和偏航力矩导数显著增大,对飞机的气动性能产生不利影响;基于刚性计算结果,对大展弦比机翼进行气动修正,是一种有效的大展弦比轻质机翼气动分析思路。
In this paper, based on the UAV, for the large aspect ratio lightweight composite wing, the strong-coupling method is used to solve the static-elastic characteristics under geometric nonlinear deformation. Comparing with the elastic machine Wing and rigid wing aerodynamic performance, and on this basis, gives a rigid wing elastic aerodynamic correction method. The results show that, compared with rigid wing, the drag-and-drag ratio decreases by 3.2% and the roll moment derivative and yaw moment derivative increase significantly, which has an adverse effect on the aerodynamic performance of the aircraft. Based on the rigid calculation results, Aerodynamic correction of a large aspect ratio wing is an effective aerodynamic analysis of a large aspect ratio lightweight wing.