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为缩短有限元建模周期,提高三角形机翼结构分析、设计与优化的效率疲,首先,以其满足预定气动性能的几何外形为输入,定义了易用的有限元节点与单元的编号规则;基于可设计的机翼内部构型参数及可变的有限元尺寸参数的设置,引入了翼肋贯穿截止准则以满足任意输入的内部构型的初步判断;借助自定义形状矩阵完成了节点布置与单元生成,进一步通过有限元网格细化完成了开口设置、翼肋贯穿位置修正及桁条建模.然后,基于已建立的有限元网格实现了内外侧副翼翼肋位置的小幅调整及旋转舵面的角度调整,以满足不同飞行状态下结构分析需求.最后,应用PCL语言开发了参数化建模模块,实例表明了方法的有效性和模块可靠性.
In order to shorten the finite element modeling period and improve the efficiency of the analysis, design and optimization of the triangular wing structure, firstly, the numerical rules of the finite element nodes and elements are defined by taking the geometrical shape satisfying the predetermined aerodynamic performance as input. Based on the design of the internal wing configuration parameters and the variable finite element size parameters, the introduction of the intercept criterion of the ribbed ribs to meet the initial judgment of the internal configuration of arbitrary input is achieved. With the help of the custom shape matrix, Unit, and further through the finite element mesh refinement to complete the opening settings, ribbed through position correction and beam modeling.And then, based on the established finite element mesh to achieve a small adjustment of the inner and outer aileron rib position and rotation The angle of the rudder surface is adjusted to meet the requirements of structural analysis under different flight conditions.Finally, the parametric modeling module is developed with PCL language, and the example shows the effectiveness of the method and the module reliability.