复合材料整体壁板固化变形控制方法研究

Study on Control Method of Cure-Induced Deformation for Integrated Composite Panel

针对优化工艺参数和结构尺寸在整体壁板固化变形控制方面的局限性问题,提出了通过面板非对称铺层来控制整体壁板固化变形的方法。采用整体壁板和非对称层合板固化变形的特征,面板采用非对称铺层,并且使固化变形方向和筋条固化变形方向相反,可以有效地抵消筋条回弹和树脂收缩引起的固化翘曲变形。并根据上述方法对某复合材料机翼壁板进行固化变形控制方法设计,分别计算初始铺层顺序、优化桁条铺层顺序和蒙皮非对称铺层三种情况下机翼壁板的固化变形量。结果表明,优化桁条铺层顺序对减少机翼壁板固化变形效果不明显,而机翼壁板蒙皮采用非对称铺层能明显减小机翼壁板的固化变形,从而验证了提出方法的可行性和正确性。

Aiming at the limitations of optimizing process parameters and structure size in terms of cure-induced deformation for integrated composite panel, a method was proposed in this paper to control the cure-induced deforma- tion through asymmetric layer panel. Due to the features of cure-induced deformation of integrated composite panel and unsymmetrical laminate, the panel is asymmetric layer and its cure-induced deformation direction is opposite to that of the ribs, thus effectively offsetting cure-induced deformation caused by rebound ribs and resin shrinkage. With the use of this method, a method has been designed to control cure-induced deformation of the composite wing panel and the cure-induced deformation amount of the wing panel was calculated separately under the three circum- stances of initial stacking sequence, optimized stringer stacking sequence and skin unsymmetrical stacking. The re- suits show that the effect the optimized stringer sequence has on the cure-induced deformation of wing panel reduction is not significant,while the skin unsymmetrical stacking of wing panel skin can significantly reduce the cure-induced deformation of wing panel, and this proves the correctness and feasibility of the method proposed in this paper.