| 摘要 |
<P>PROBLEM TO BE SOLVED: To provide a frame of a fuselage structure of an aircraft, which reduces weight, materials and works, while meeting specifications necessary for aircraft applications. <P>SOLUTION: The curved composite aircraft frame 36 includes a multi-ply composite laminate having a generally Z-shaped cross section. At least certain of the laminate plies include unidirectional reinforcing fibers that are substantially tangent at substantially all points along the curvature of the frame. <P>COPYRIGHT: (C)2012,JPO&INPIT |
