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建立了一种基于高阶面元法与模态法的静气动弹性分析方法,并基于此方法对弹性机翼进行了静气动弹性分析.基于机翼几何实体模型建立了三维气动力模型,利用高阶面元法计算气动力,通过模态法实现气动与结构的耦合,以AGARD445.6机翼和一个小展弦比机翼为研究对象,分析了机翼结构弹性变形对气动力的影响.本文重点研究了机翼的气动力系数、翼根载荷、结构变形、不同展向位置的压力分布等参数的变化趋势,并将部分结果与风洞试验、基于风洞试验气动力所得弹性结果进行了对比.结果表明:高阶面元法计算所得气动力具有较高的精确性;基于高阶面元法与模态法的静气动弹性分析方法具有可行性、可靠性和高效性,可以提供较为全面的静气动弹性数据为飞机初步设计参考.
A static-dynamic analysis method based on higher-order panel method and modal method is established, and based on this method, the static aerodynamic elasticity is analyzed. Based on the geometric model of the wing, a three-dimensional aerodynamic model is established, The high-order surface element method is used to calculate the aerodynamic force, and the aerodynamic and structural coupling is realized by the modal method. Taking the AGARD445.6 wing and a small aspect ratio wing as the research objects, the effect of the wing structure elastic deformation on the aerodynamic force is analyzed In this paper, the change tendency of aerodynamic coefficient, wing root load, structural deformation and pressure distribution at different span locations are mainly studied, and some results are compared with wind tunnel tests based on the aerodynamic results obtained from wind tunnel tests The results show that the aerodynamic force calculated by the higher-order panel method has higher accuracy. The static-dynamic elasticity analysis method based on the higher-order panel method and modal method is feasible, reliable and efficient. Provide a more comprehensive static and dynamic data for the preliminary design of the aircraft reference.