CAJ | 학술논문

针对大展弦比机翼的柔性大、变形大的特点，基于非定常涡格法求解机翼的非定常气动力，考虑了大展弦比机翼的几何非线性效应，提出了计算大展弦比机翼非线性颤振分析的新方法。以某平板机翼为例：计算了机翼静气动弹性变形、振动特性和颤振特性随着攻角增大的变化规律；比较了颤振结果线性解与非线性解的差别。相关的分析结果表明：大展弦比机翼颤振分析需同时考虑几何非线性效应和气动网格变形。
침대대전현비궤익적유성대、변형대적특점，기우비정상와격법구해궤익적비정상기동력，고필료대전현비궤익적궤하비선성효응，제출료계산대전현비궤익비선성전진분석적신방법。이모평판궤익위례：계산료궤익정기동탄성변형、진동특성화전진특성수착공각증대적변화규률；비교료전진결과선성해여비선성해적차별。상관적분석결과표명：대전현비궤익전진분석수동시고필궤하비선성효응화기동망격변형。
Large deformation and flexibility are significant for high-aspect-ratio wings. In this paper, unsteady vor-tex-lattice method is used to solve for the unsteady aerodynamic force. It considered the effect of structural geometric nonlinearity on the high-aspect-ratio wing in the structure calculation. It presents a new method for calculating the nonlinear flutter analysis of high-aspect-ratio wing. As the angle of attack increases, the characteristics of static aeroelasticity, vibration and flutter are calculated around a flat board wing. Additionally, we compare numerically the linear solution with the nonlinear one. The results and their analysis prove preliminarily that high-aspect-ratio wing flutter must consider both geometrically nonlinear and grid deformation.