基于多控制面的二元机翼扭转变形抑制研究  

Suppression of twist deformation of two-dimensional wing based on multi-control surfaces

作　　者：马斌麟 苏新兵[1] 冯浩洋 王宁[1] 

机构地区：[1]空军工程大学航空航天工程学院 [2]中国人民解放军93427部队

出　　处：《飞行力学》2017年第4期19-23,28,共6页Flight Dynamics

基　　金：国家自然科学基金资助(11402301);陕西省自然科学基础研究项目(2015JM1005)

摘　　要：针对前掠机翼的扭转发散,以加装前、后缘控制面且刚心靠后的二元机翼为模型,基于CFD/CSD松耦合静气弹数值计算方法,提出了一种基于多控制面的二元机翼扭转变形抑制方法。计算结果表明,前缘控制面单独上偏时,气动特性较差,扭转变形特性较好;后缘控制面单独下偏时,气动特性较好,扭转变形特性较差;前、后缘控制面联合偏转时,融合了两者单独偏转时各自的优势,在尽量减少气动性能损失的基础上降低了扭转变形峰值。该研究可为多控制面在前掠翼扭转发散主动抑制中的应用提供参考。In view of divergence of forward swept wing,the model used in this paper is based on two-dimensional wing which has leading-and trailing-edge control surfaces and the location of elastic axis at the back. Based on the CFD/CSD loose coupling static aeroelastic numerical calculation method,a method for suppression of twist of two-dimensional wing based on multiple control surfaces is proposed. The calculation results indicated that,when the leading-edge control surface deflect clockwise,the aerodynamic characteristics was bad while torsional deformation characteristics was good,and the situation was contrary when the trailing-edge control surface deflect clockwise. For joint deflection of leading-edge and trailing-edge control surface deflect synergistically,the peak of torsional deformation was reduced on the basis of minimizing losses of aerodynamic characteristics. The study can provide reference for the suppression of divergence of forward swept wing based on multiple control surfaces.

关 键 词：多控制面 二元机翼 静气动弹性 扭转变形 抑制 

分 类 号：V211.47[航空宇航科学与技术—航空宇航推进理论与工程] V215.3