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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。
Considering the fluid-solid coupling effect, the mechanical properties of the aircraft under service are studied. In this paper, a high precision general static gas bomb solver based on CFD / CSD (Computational Fluid Dynamics / Computational Structure Dynamics) coupling is presented. The solver can simultaneously analyze the surface aerodynamic performance and the mechanical properties of the structure. The body-combination model has been subjected to the static gas bomb analysis, and the aerodynamic pressure changes of the flexible and rigid aircraft and the stress distribution of the structure have been obtained. Both the fluid and structural models are modeled using a wing-body combination model, both of which are considered the impact of the fuselage. The results show that the lift coefficient, drag coefficient and moment coefficient of the aircraft decrease after the static gas bomb deformation occurs. The larger stress distribution will occur in the vicinity of wing root. When the aircraft, especially the wing surface, is subjected to bending moment, torque and aerodynamic When pressure is combined, complex stress distribution occurs near the root of the wing. This shows that in the static elasticity analysis, the body modeling is also necessary.