多控制面对鸭翼-前掠翼布局飞行器静气动弹性的影响  

Influence of Multi-Control Surface on Aeroelasticity of Canard-Forward-Swept Aircraft

作　　者：姜文 苏新兵[1] 张钧奕 赵希玮 王振[1] JIANG Wen;SU Xinbing;ZHANG Junyi;ZHAO Xiwei;WANG Zhen(Aeronautics Engineering College,Air Force Engineering University,Xi’an 710038,China)

机构地区：[1]空军工程大学航空工程学院,西安710038

出　　处：《空军工程大学学报（自然科学版）》2020年第6期7-12,共6页Journal of Air Force Engineering University(Natural Science Edition)

基　　金：陕西省自然科学基础研究计划项目(2019JM-451)。

摘　　要：针对机翼前、后缘控制面对鸭翼-前掠翼布局飞行器静气动弹性的影响,通过CFD/CSD松耦合计算方法求解三维不定常N-S方程和线弹性静力学方程,得到了前、后缘控制面单独偏转和协同偏转状态下弹性前掠翼的气动特性和弹性特性。研究结果表明:弹性机翼相比于刚性机翼有更好的升力特性和大迎角失速特性;控制面偏转方式的变化也会对气动特性和弹性特性产生影响,当控制面单独偏转时,前缘控制面下偏和后缘控制面下偏均能增大弹性机翼的升力系数,最大升力系数增量分别为2.60%和8.69%;当控制面协同偏转时,同向偏转时的升力增幅比单独偏转时更大,最大升力增量为11.96%,反向偏转的升阻比特性较好,并可在小迎角范围内降低弹性变形和扭转。In view of the influence of the front and rear edges of the wing on the static aeroelasticity of the canard-forward-swept wing configuration aircraft,through three-dimensional unsteady N-S equations and linear elastic statics equations solved by the CFD/CSD loosely coupled calculation method,the aerodynamic and elastic characteristics of the elastic forward-swept wing are obtained under condition of the state of independent deflection and coordinated deflection of the leading and rear edges control surface.The results show that the elastic wing is characterized by better lift characteristics and high angle of attack stall characteristics compared with the rigid wing,and the changes of the control surface deflection method also affect the aerodynamic and elastic characteristics.When the control surface is deflected alone,both of the downward deflection of the leading edge control surface and the downward deflection of the trailing edge control surface can increase the lift coefficient of the elastic wing,and the maximum lift coefficient increments are2.60%and 8.69%respectively.When the control surfaces are deflected in coordination,the lift coefficient in deflecting in the same direction is greater than that of single deflection,and the maximum lift increment is 11.96%.The lift-drag ratio of reverse deflection is better,and the elastic deformation and torsion can be reduced in the range of small angle of attack.

关 键 词：鸭翼-前掠翼布局 控制面偏转 弹性变形 CFD/CSD松耦合 

分 类 号：V224[航空宇航科学与技术—飞行器设计]