Composite structural member with progressive rigidity
AssigneeAirbus Operations GmbH
InventorsDenis Soula, Julien Guillemaut
Life of this patent
Estimating the term…
Abstract
A composite structural member with fiber reinforcement comprising a plurality of layers oriented relative to a longitudinal direction of said member in directions including 0°, 90° and +/−θ, the relative proportion of layers in one of these orientations being variable along a transverse direction of said member so as to spatially adjust the rigidity of the member according to a defined distribution of mechanical stresses along this transverse axis. The rigidity of the member is adapted locally to the stress system so as to dissipate the force flux over the entire volume of said member.
Claims9
A composite structural member for an aircraft with fiber reinforcement comprising:
- a plurality of layers of fibers oriented relative to a longitudinal direction of the composite structural member of the aircraft at angles including 0°, 90° and +/−θ, a relative proportion of fibers in at least one of these orientations is varied along a transverse axis of the composite structural member so as to spatially adjust rigidity of the composite structural member according to a defined distribution of mechanical stresses along this transverse axis,
- wherein at least one layer of fibers oriented at a +/−θ angle is formed of continuous fibers extending from one side of the composite structural member to another side over an entire surface of the composite structural member,
- wherein a thickness of the composite structural member is constant along the transverse axis, and
- wherein 0°<θ<90°.
Dependencies are inferred from the claim text.