摘要
后掠机翼在飞行过程中受气动载荷影响,其机翼将产生弯曲和扭转变形,这种弹性变形严重影响飞机性能和飞行安全,不能将此种机翼当作传统的刚性机翼加以弹性修正的方法进行分析。针对这种弹性后掠机翼,应用发展的非结构动网格生成方法,以Euler方程为控制方程,耦合结构静平衡方程,采用结构影响系数法,对中等展弦比、大展弦比后掠机翼的气动力载荷和结构变形进行了求解,并对结果进行了分析。
The flight swept wing will produce bending and torsion deformation due to aerodynamic load effect The elastic deformation seriously affected aircraft performance and flight safety. The traditional elastic analysis method of regarding wing as a rigid wing with elastic correction analysis is not suited to the flexible wing. According to the elastic swept wing, coupled with structural static equilibrium equations, the Euler equation of improved dynamic unstructured grid is applied to calculate aerodynamic load and structural deformation about a high aspect-ratio backswept wing. And the computing results were analyzed.
出处
《科学技术与工程》
北大核心
2015年第17期232-236,共5页
Science Technology and Engineering
基金
陕西省教育厅科学研究项目(14JK1160)
陕西理工学院人才启动项目(SLGQD13(2)-21)
陕西省县域重点科技计划项目(2012XY-15)联合资助
关键词
弹簧近似
后掠机翼
静气动弹性
结构影响系数法
spring analogy swept wing static aeroelasticity structure influence coefficient method
