IP Library Granted Patent US 10,105,938
Granted Patent B2
US 10,105,938 · App. 14/557,074 · Granted Oct 23, 2018

Self-stiffened composite panel and method of producing same

Inventors: Dominique Guittard (Toulouse, FR); Mathieu Lannuzel (Saint Herblain, FR); Philippe Blot (Nantes, FR); Gilles Bezard (Pornichet, FR)
Assignee: Airbus Operations (S.A.S.)
B32B37/1284B29C33/306B29C33/3828B29C33/485B29C70/443B29C70/543B29C70/86B29D99/0003B29D99/0014B64C1/064B64C3/182B29K2705/00B29L2031/3082B32B2260/00Y10T156/1028
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Quick Facts
Patent No.
US 10,105,938
App. No.
14/557,074
Granted
Oct 23, 2018
Kind
B2
Abstract

The disclosure proposes a method for producing a panel having an outer skin and stiffeners that have a connecting portion, and at least one projecting portion, the method comprising a step of draping layers of fibers over at least one insert such that each layer of fibers has a connecting portion and a portion that projects downwardly from the connecting portion, a step of draping a layer of fibers that forms the outer skin, and a step of bonding the layers of fibers together. The disclosure also provides a device for implementing the method.

Claims (9)

1. A method for producing a self-stiffened composite panel having an outer skin and stiffeners, each stiffener having a portion for connecting the stiffener to the outer skin, and at least one portion that projects from the connecting portion, the method comprising:

draping layers of fibers, that are intended to form the stiffeners, over at least one insert having a complementary shape to a final shape of the stiffeners, such that each layer of fibers that is intended to form a stiffener has a connecting portion and a free lower end portion that projects vertically downwardly from the connecting portion;

draping a layer of fibers that is intended to form the outer skin over the connecting portion of the layers of fibers that are intended to form the stiffeners; and

simultaneously bonding all the layers of fibers together by a matrix using the at least one insert as a mold element;

wherein, during draping, the layers of fibers are not impregnated with matrix and bonding together comprises a phase of injecting the matrix and then a phase of hardening the matrix, and wherein injecting the matrix comprises injecting the matrix from a bottom upwards from the free lower end portion.

2. The method according to claim 1 , wherein draping layers of fibers over the at least one insert is followed by positioning each insert covered by the layer of fibers on a molding support.

3. The method according to claim 2 , comprising a positioning step comprising positioning the inserts covered by the layers of fibers in a manner adjacent to one another.

4. The method according to claim 1 , wherein the bonding together comprises positioning at least one of a demolding fabric, an air draining felt, a smoothing metal sheet and a vacuum bag on the layer of fibers that is intended to form the outer skin prior to the phase of injecting the matrix.

5. The method according to claim 1 , wherein the panel comprises metal accessories fixed to the stiffeners and/or to the outer skin, and wherein the method comprises fitting the accessories at a same time as draping the layers of fibers that are intended to form the stiffeners.

Assignments (1)
ASSIGNMENT OF ASSIGNOR'S INTEREST Recorded Feb 24, 2015
From: GUITTARD, DOMINIQUE; LANNUZEL, MATHIEU; BLOT, PHILIPPE; BEZARD, GILLES
To: AIRBUS OPERATIONS (S.A.S.)
Reel/Frame 035019/0331 →
Priority Claims (1)
FR 12 54925 · May 29, 2012 · national
Continuity (2)
Continuation PCTFR2013051159 · May 27, 2013
Related Publication 20150165744A1 · Jun 18, 2015
Cited By (2)
US 12,508,745 US 12,582,853