氢动力无人机大展弦比机翼静气弹特性分析

摘要

Based on hydrogen-powered ultra-long endurance unmanned aerial vehicle (UAV),nonlinear static aeroelastic characteristics were analyzed by the strong-coupled method for its high-aspect-ratio light composite wing.The aerodynamic comparison of rigid and elastic (aeroelastic deformation) wing was investigated.And then,an aerodynamic correction method,based on the result of the rigid wing,was applied to the elastic wing.The results show that the lift-drag ratio of the elastic wing reduces by 3.2％ (compared to the rigid wing),and roll and yaw moments significantly increases to the disadvantage of aerodynamic performance.The aerodynamic correction based on rigid computation results is an efficient aerodynamic analysis strategy for highaspect-ratio light composite wing.%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.