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US 8,992,709 B2Granted
Sandwich structure having arrestment feature and method of making the same
AssigneeThe Boeing Company
InventorsCharles R. Saff, John H. Fogarty, Haozhong Gu, Terry D. Richardson, Kevin M Retz
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Abstract
A composite sandwich structure comprises a core sandwiched between composite laminate facesheets. The core includes a plurality of core sections spliced together at joints that incorporate integral features for arresting the propagation of irregularities in the facesheets.
Claims8
A method of making a composite sandwich structure, comprising:
- producing a core by forming a joint between a first core segment and a second core segment;
- forming an arrestment feature between the first core segment and the second core segment, the arrestment feature wrapping at least partially around two sides of at least one of the first core segment and the second core segment at about the joint;
- sandwiching the core between first and second facesheets, including joining the core to the first and second facesheets, and the first and second facesheets each extending across the joint and over the arrestment feature;
- wherein the arrestment feature wraps around two sides of the first core segment and two sides of the second core segment such that the first facesheet and the second facesheet are both in contact with portions of the arrestment feature;
- the arrestment feature comprises a first wrap and a second wrap, wherein the first wrap and the second wrap both are generally C-shaped in cross section;
- the first wrap covers three sides of the first core segment;
- the second wrap covers three sides of the second core segment;
- at least one of a first composite strap overlies the joint;
- the first composite strap is sandwiched between the first facesheet and both the first wrap and the second wrap;
- at least one of a second composite strap overlies the joint;
- and the second composite strap is sandwiched between the second facesheet and both the first wrap and the second wrap.
8 more elements
A method of making a composite sandwich structure for an aircraft, comprising:
- providing a plurality of core segments;
- wrapping three sides of each of the core segments along the edges of the core segments with a fiber reinforced composite resin wrap;
- assembling the wrapped core segments into a core, including forming joints between the core segments by arranging the core segments in edge-to-edge relationship and abutting the wraps on adjacent ones of the core segments;
- introducing a layer of adhesive between the wraps along each of the joints;
- forming a plurality of composite tear straps;
- placing one of the tear straps over the wraps along each of the joints;
- assembling the structure including sandwiching the core, the wraps and the tear straps between first and second facesheets that extend entirely across all the joints;
- and, curing the assembled structure;
- wherein the arrestment feature wraps around two sides of the first core segment and two sides of the second core segment such that the first facesheet and the second facesheet are both in contact with portions of the arrestment feature;
- the arrestment feature comprises a first wrap and a second wrap, wherein the first wrap and the second wrap both are generally C-shaped in cross section;
- the first wrap covers three sides of the first core segment;
- the second wrap covers three sides of the second core segment;
- at least one of a first composite strap overlies the joint;
- the first composite strap is sandwiched between the first facesheet and both the first wrap and the second wrap;
- at least one of a second composite strap overlies the joint;
- and the second composite strap is sandwiched between the second facesheet and both the first wrap and the second wrap.
13 more elements
Dependencies are inferred from the claim text.