Title:
PLY STACKING FOR SOLID LAMINATE STIFFENED PANEL
Document Type and Number:
Japanese Patent JP2021075040
Kind Code:
A
Abstract:
To provide a composite panel for a fuselage, a wing, a tail, an empennage, etc. of an aircraft, such as a solid laminate stringer that connects to a supporting framework, the composite panel being resistant to damage caused by stresses and strains placed during use.SOLUTION: A composite panel 100 includes a plurality of segments 104, 106, 108, 110, where each segment includes a plurality of reinforcement plies such as carbon fiber plies. Collimated fiber bands (e.g., carbon fibers) within each reinforcement ply are oriented in a single direction, which can be, for example, 0°, 45°, 90° and -45°. Each segment can include a stack of reinforcement plies, where the collimated fiber bands of each reinforcement ply are oriented in one of these directions.SELECTED DRAWING: Figure 1
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Inventors:
CHENG JIANGTIAN
Application Number:
JP2020141392A
Publication Date:
May 20, 2021
Filing Date:
August 25, 2020
Export Citation:
Assignee:
BOEING CO
International Classes:
B32B5/02; B29C70/10; B32B5/26; B64C1/00; B64C1/06
Attorney, Agent or Firm:
Sonoda/Kobayashi Patent Business Corporation