Braided structural composites have the potential to replace aerospace primary structure traditionally manufactured with preimpregnated fabrics and cured in autoclave. An improved braiding model was developed and applied to a complex fuselage frame technological demonstrator. Numerical case studies were performed in order to assess their effectiveness and to determine the best braiding parameters. A radial braiding machine was coupled to an industrial robot. The fuselage frame demonstrator mandrel was overbraided with carbon fiber yarns. Measured braid angles showed a greater difference than what was expected between the web and the flange faces. Yarn friction and interlacing forces caused the yarns to curve near the edges of the face, therefore causing the measured braid angles to vary along the face width. Moreover, discrepancies in the model’s outputs prevented the braid fell front to conform around the severe cross-section variations as well as causing yarn slip over the corners.

编织结构复合材料有可能取代传统上用预浸织物制造并在高压釜中固化的航空航天一级结构。开发了一种改进的编织模型，并将其应用于复杂的机身框架技术演示器。为了评估其有效性并确定最佳编织参数，进行了数字案例研究。径向编织机与工业机器人相连。机身框架演示器芯轴用碳纤维纱编织而成。测得的编织角显示出的幅值比腹板和法兰面之间的期望值差更大。纱线摩擦力和交织力导致纱线在表面边缘附近弯曲，因此导致测得的编织角沿表面宽度变化。而且，