考虑流固耦合效应的某飞行器力学性能分析  

Considering fluid-structure coupling effect of an aircraft mechanical properties analysis

作　　者：周强[1] 陈刚[1] 李跃明[1] 

机构地区：[1]西安交通大学机械结构强度与振动国家重点实验室710049西安

出　　处：《应用力学学报》2015年第2期209-214,350,共6页Chinese Journal of Applied Mechanics

基　　金：国家自然基金(11272005;10902082;91016008)

摘　　要：考虑流固耦合效应,研究了飞行器在服役状态下的力学特性。本文采用了一种基于CFD/CSD(Computational Fluid Dynamics/Computational Structure Dynamics)耦合的高精度通用静气弹求解器,该求解器可以同时分析飞行器结构的表面气动性能和结构的力学性能,对某一翼身组合体模型进行了静气弹分析,得出弹性飞行器和刚性飞行器的气动压力变化以及结构的应力分布。建模时流体和结构模型都使用翼身组合模型,且都考虑机身的影响。结果表明:发生静气弹变形后,飞行器的升力系数、阻力系数、力矩系数都相应下降;机翼翼根附近会产生较大的应力分布;当飞行器尤其是机翼表面受到弯矩、扭矩以及气动压力的共同作用时,翼根附近会出现复杂的应力分布状态。这说明在静气弹性分析中,机身的建模也是很有必要的。Analysis of a service aircraft stress by fluid-solid coupling method can truly reflect the aircraft aerodynamic and structural mechanical properties. To aim at this target, a generic multi-block static aero-elastic solver based on CFD/CSD(Computational Fluid Dynamics/Computational Structure Dynamics) coupling is employed. The solver can simultaneously analyze the aerodynamic properties of aircraft structures and the mechanical properties. A flexible wing-body model is used to analyze the aerodynamic effect of elastic and rigid aircraft. Then the aerodynamic and mechanical properties of rigid and elastic aircraft model can be got. A wing-body combination model is used in CFD/CSD modeling, and the influence of fuselage is taken into account. Analysis results show that aircraft lift, drag and moment coefficients all decrease after static aero-elastic deformation. Due to the fact that a large stress distribution is exist in the wing root, so it is necessary to consider the fuselage modeling in static aero-elastic analysis. The simultaneously action in aircraft wing surface by bending moment, torque and aerodynamic pressure leads to the complicated stress distributions near the wing root.

关 键 词：静气弹 CFD/CSD耦合 插值 有限元 

分 类 号：V215.3[航空宇航科学与技术—航空宇航推进理论与工程]