弹性前掠翼开裂式方向舵操纵特性分析

摘要

Aimed at the influence of elastic deformation on the control characteristics of split rudder for the forward swept wing (FSW) aircraft,the computational fluid dynamics/computational structural dynamics (CFD/CSD) loose coupling static aeroelastic numerical calculation method was adopted.The calculation and analysis on control characteristics of the split rudder with rigid and elastic wings were performed under the subsonic condition.The simulation had highlighted the influence of wing deformation on the control characteristics of the rudder.The calculation result shows that,when the right side split rudder opens,compared with rigid wing,the stall attack angle of the elastic wing advances about 2°,the attack angle of maximum lift-drag ratio advances about 1°,the yaw effect at small attack angle is enhanced,the " pits" phenomenon of right-roll moment and roll moment appears,and the trend of yaw at high angle of attack advances about 8° with more violent roll action;under the influence of sideslip,the decrease extent of the yawing moment with the increase of sideslip angle is larger than that of the rigid wing,and the roll moment has completely opposite resuunder the action of down moment proving by rudder,the increase extent of the yawing moment with the increase of sideslip angle is larger than that of the rigid wing.By comparison,the control characteristics of split rudder for the elastic FSW have a distinct difference with rigid FSW.%针对机翼弹性变形对前掠翼(FSW)飞行器开裂式方向舵操纵特性的影响,基于计算流体力学/计算结构力学(CFD/CSD)松耦合静气动弹性数值计算方法,计算了亚声速条件下刚性和弹性前掠机翼开裂式方向舵的操纵特性,并分析了机翼弯扭变形对方向舵操纵特性的影响.计算结果表明,右侧开裂式方向舵打开后,与刚性翼相比,弹性翼的失速迎角提前约2°,达到最大升阻比的迎角提前约1°,小迎角时偏航作用增强,出现右滚力矩和滚转力矩“凹坑”现象,大迎角时偏航规律趋势提前约8°,滚转作用加剧;侧滑角增大时,偏航力矩减小的幅度大于刚性翼,滚转力矩完全反效;舵偏角增大时,偏航力矩的增幅小于刚性翼.经比较,在弹性变形影响下,弹性前掠翼的开裂式方向舵操纵特性与刚性前掠翼有明显区别.