The invention discloses a method for inhibiting bending wrinkles of a flexible bearing corrugated structure, belongs to the field of deformable wings of morphing aircrafts, and relates to a method forinhibiting wrinkles of a flexible skin with a corrugated sandwich structure. According to the method, a corrugated core structure and a special-shaped silicone rubber panel are involved, and a skin panel is redesigned, so that the problem of the wrinkles in the bending deformation process of the skin is solved. According to the method, by changing a shape and a size of a convex part of the special-shaped silicone rubber panel, a wrinkle inhibition effect is further improved, and the method is suitable for variable-camber wing flexible skins with different corrugation configurations.
本发明公开了一种柔性承载波纹结构的弯曲褶皱抑制方法,属于变体飞行器可变形机翼领域,涉及一种具有波纹夹芯结构的柔性蒙皮褶皱抑制方法。本方法包括波纹芯子结构和异形硅橡胶面板,通过对蒙皮面板进行再设计,达到抑制蒙皮弯曲变形过程中的褶皱问题。本发明可通过改变异形硅橡胶面板凸起部分的形状、尺寸,进一步提高褶皱抑制效果,适用于具有不同波纹构型的变弯度机翼柔性蒙皮。
Method for inhibiting bending wrinkles of flexible bearing corrugated structure
一种柔性承载波纹结构的弯曲褶皱抑制方法
2020-12-22
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
Engineering Index Backfile | 1915
|Flexible skin based on dot matrix corrugated structure
Europäisches Patentamt | 2022
|Europäisches Patentamt | 2016
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