Tapered patch for predictable bonded rework of composite structures
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-001/06
B32B-003/10
B23P-019/04
B29C-073/14
B32B-019/04
B29C-073/10
B29C-073/16
출원번호
US-0902855
(2013-05-27)
등록번호
US-8802213
(2014-08-12)
발명자
/ 주소
Dan-Jumbo, Eugene A.
Keller, Russell L.
Westerman, Everett A.
출원인 / 주소
The Boeing Company
대리인 / 주소
Yee & Associates, P.C.
인용정보
피인용 횟수 :
4인용 특허 :
48
초록▼
A patch for reworking an inconsistent area in a composite structure includes a composite laminate patch adapted to cover the inconsistent area and bonded to the structure by a layer of adhesive. The patch includes a plurality of composite plies having a tapered cross section, and at least first and
A patch for reworking an inconsistent area in a composite structure includes a composite laminate patch adapted to cover the inconsistent area and bonded to the structure by a layer of adhesive. The patch includes a plurality of composite plies having a tapered cross section, and at least first and second regions respectively having differing fracture toughnesses.
대표청구항▼
1. A patch for reworking an inconsistent area in a composite structure, comprising: a composite laminate patch adapted to cover the inconsistent area and including a plurality of composite plies having a tapered cross section, the composite laminate patch including at least: a first bond joint contr
1. A patch for reworking an inconsistent area in a composite structure, comprising: a composite laminate patch adapted to cover the inconsistent area and including a plurality of composite plies having a tapered cross section, the composite laminate patch including at least: a first bond joint control region, and a second bond joint control region configured substantially surrounding the first bond joint control region and comprising a differing fracture toughness than the first bond joint control region, such that a first strain energy release rate of the first bond joint control region is distinct from a second strain energy release rate of the second bond joint control region, and such that the first bond joint control region and the second bond joint control region each comprise different resistances to delamination, each bond joint control region configured to present an indication of a condition of the composite laminate patch and comprising a corresponding first ply that is bonded, by a corresponding tailored adhesive, to a corresponding surface comprising at least one of: a second ply, and the composite structure. 2. The patch of claim 1, wherein the composite plies include at least first and second groups of plies respectively defining the first and second regions. 3. The patch of claim 2, wherein edges of the plies in each of the first and second groups form the tapered cross section. 4. The patch of claim 1, wherein: the laminate patch includes a third region having a third region fracture toughness different than the fracture toughnesses of the first and second regions, andthe composite plies include at least first, second and third groups of plies respectively defining the first, second and third regions. 5. The patch of claim 1, wherein the first and second regions respectively have generally circular outer perimeters and are substantially concentric. 6. The patch of claim 1, wherein the tailored adhesive has a thickness that tapers from the first region to the second region. 7. The patch of claim 1, wherein: the laminate patch includes first and second faces, and tapers outwardly from the first face to the second face, andthe second face is bonded to the composite structure by the tailored adhesive. 8. The patch of claim 1, further comprising the tapered cross section being bonded to the composite structure by the tailored adhesive. 9. The patch of claim 1, wherein the tailored adhesive includes at least first and second regions respectively bonding the first and second regions of the laminate patch to the composite structure, the first and second regions of the tailored adhesive having differing properties for releasing strain energy around the inconsistent area at different rates. 10. A patch for reworking an inconsistent area in a composite structure, comprising: a composite laminate patch adapted to cover the inconsistent area and including at least first and second groups of composite laminate plies, the first and second groups of plies respectively defining a first control region substantially surrounded by a second control region, each control region comprising differing interlaminar fracture toughnesses, the first group of plies having a first width, the second group of plies having a second width different than the first width; anda layer of adhesive for bonding the composite laminate patch to the composite structure, the layer comprising a thickness of the layer tailored across the layer such that a rate of strain energy release in a bond joint between the layer and the composite laminate patch compliments the respective interlaminar fracture toughness of each control region. 11. The patch of claim 10, wherein: the first width is less than second width,the first group of plies has a first face, andthe second group of plies has a second face opposite the first face and bonded to the composite structure by the adhesive layer. 12. The patch of claim 10, wherein each of the first and second groups of plies include tapered edges. 13. The patch of claim 10, wherein: the plies in the first and second groups each include reinforcing fibers having a fiber orientation and a layup orientation sequence, andthe layup sequence of the plies in the first group is different than the layup sequence of the plies in the second group. 14. The patch of claim 10, wherein a first number of plies in the first group is different than a second number of plies in the second group. 15. The patch of claim 10, wherein a first thickness of the plies in the first group is different than a second thickness of the plies in the second group. 16. The patch of claim 10, further comprising the thickness tapering from outer edges of the layer to a central area of the layer. 17. A bonded rework of an inconsistent area in a composite structure, comprising: a tapered edge on the composite structure surrounding the inconsistent area, the tapered edge comprising a first tapered surface and a second tapered surface respectively having a first scarf angle and a second scarf angle, the second scarf angle being steeper than the first scarf angle, the first scarf angle configured to carry a higher load than the second scarf angle and aid a prediction of performance of the bonded rework over time; and,a tapered composite laminate patch covering the inconsistent area, the patch comprising an edge comprising a first tapered portion and a second tapered portion respectively bonded to the first and second tapered surfaces and forming a scarf joint between the composite structure and the composite tapered laminate patch, the first tapered portion corresponding to a first boundary of a first control region, the first control region configured to reduce a peak probability of a crack in the first region from extending beyond the first control region, the second tapered portion corresponding to a second boundary of a second control region, the second control region configured to elevate a total fatigue threshold strain energy release rate of the bonded rework; andan adhesive layer configured to bond the tapered composite laminate patch to the tapered edge on the composite structure, the adhesive layer being sectioned corresponding to each control region of the tapered composite laminate patch such that each section of the adhesive layer comprises a respective tailored rate of release strain energy. 18. The rework of claim 17, wherein: the tapered edge on the composite structure includes a third tapered surface having a third scarf angle, andthe edge of the tapered patch includes a third portion bonded to the third tapered surface. 19. The rework of claim 17, wherein: the tapered laminate patch includes at least first and second groups of composite laminate plies respectively defining first and second regions having differing interlaminar fracture toughnesses. 20. A patch for reworking an inconsistent area in a composite aircraft structure, comprising: a composite laminate patch adapted to cover the inconsistent area and including first, second and third groups of composite plies respectively defining first, second and third regions of differing fracture toughness, the first, second and third groups of composite plies having edges respectively tapered at first, second and third angles, the first region configured to exhibit favorable in-plane adhesive stresses, the second region substantially contiguous and concentric about the first region and configured to indicate a need for reworking the inconsistent area, the third region substantially contiguous and concentric about the second region and configured for domination by in-plane shear and peeling moments;a first surface, a second surface, and a third surface formed on an edge of the composite structure surrounding the inconsistent area and respectively having scarf angles generally matching the first, second and third angles; and,a layer of adhesive configured to bond the edges of the plies to the first surface, the second surface, and the third surface of the edge on the composite structure; the layer comprising a first adhesive section, a second adhesive section, and a third adhesive section, corresponding to the first region, the second region, and the third region respectively, and each adhesive section tailored to at least one of: a desired thickness between the patch and the composite aircraft structure, a desired rate of release strain energy, and a desired fracture toughness.
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