Method and system for manufacturing a cured composite structure

Patent metadata

Field	Value
Publication number	US-11214021-B2
Application number	US-202016811262-A
Country	US
Kind code	B2
Filing date	Mar 6, 2020
Priority date	Mar 6, 2020
Publication date	Jan 4, 2022
Grant date	Jan 4, 2022

Abstract

A method for manufacturing a cured composite structure from first stringers, second stringers and a panel comprising a first side and a second side, the method includes, for each first stringer, supporting the first stringer on the first side of the panel using a substantially rigid mandrel positioned within a first cavity defined between the first stringer and the first side of the panel, for each second stringer, supporting the second stringer on the second side of the panel using a flexible mandrel positioned within a second cavity defined between the second stringer and the second side of the panel, and co-curing the first stringers, the panel, and the second stringers while each of the one or more first stringers are supported by the respective substantially rigid mandrel and each of the one or more second stringers are supported by the respective flexible mandrel.

First claim

What is claimed is:

1. A method for manufacturing a cured composite structure from one or more first stringers, one or more second stringers and a panel, the panel comprising a first side and a second side opposed from the first side, the method comprising:
for each first stringer of the one or more first stringers, supporting the first stringer on the first side of the panel using a rigid tool and a substantially rigid mandrel such that the substantially rigid mandrel is positioned within a first cavity defined between the first stringer and the first side of the panel and the first stringer and the substantially rigid mandrel are at least partially received in a trough defined by the rigid tool;
for each second stringer of the one or more second stringers, supporting the second stringer on the second side of the panel using a flexible mandrel such that the flexible mandrel is positioned within a second cavity defined between the second stringer and the second side of the panel; and
co-curing the one or more first stringers, the panel, and the one or more second stringers while the one or more first stringers are supported by the substantially rigid mandrels and the one or more second stringers are supported by the flexible mandrels.

2. The method of claim 1 wherein the first side of the panel is substantially planar.

3. The method of claim 1 wherein the second side of the panel is contoured.

4. The method of claim 1 wherein the one or more first stringers are elongated and define a first path of elongation, and wherein the one or more second stringers are elongated and define a second path of elongation.

5. The method of claim 4 wherein the first path of elongation intersects the second path of elongation.

6. The method of claim 5 wherein the first path of elongation is at an angle relative to the second path of elongation, and wherein the angle is between about 80 degrees and about 100 degrees.

7. The method of claim 4 wherein a projection of the first path of elongation onto an imaginary view plane, and a projection of the second path of elongation onto the imaginary view plane intersect at an angle, wherein the angle is between about 80 degrees and about 100 degrees.

8. The method of claim 1 further comprising removing the substantially rigid mandrel and the flexible mandrel from the cured composite structure.

9. The method of claim 1 wherein the substantially rigid mandrel has a coefficient of thermal expansion between about 86 μm/(m·K) and about 160 μm/(m·K).

10. The method of claim 1 wherein during the co-curing the substantially rigid mandrel expands by a first volume, the first cavity expands by a second volume, and wherein the first volume is substantially the same as the second volume.

11. The method of claim 1 wherein during the co-curing the substantially rigid mandrel expands by a first volume, the first cavity expands by a second volume, and wherein the first volume is between about 95 percent and about 105 percent of the second volume.

12. The method of claim 1 further comprising:
supporting a first plurality of stringers on the first side of the panel, wherein the first plurality of stringers comprises the one or more first stringers; and
supporting a second plurality of stringers on the second side of the panel, wherein the second plurality of stringers comprises the one or more second stringers.

13. The method of claim 1 wherein the rigid tool comprises a planar surface.

14. The method of claim 1 wherein the substantially rigid mandrel has a tensile modulus of at least about 35 MPa.

15. A method for manufacturing a cured composite structure using a rigid tool that defines one or more troughs therein, one or more first stringers, one or more second stringers, and a panel, the panel comprising a first side and a second side opposed from the first side, the method comprising:
for each first stringer of the one or more first stringers, (i) positioning the first stringer on the rigid tool such that the first stringer is at least partially within a trough of the one or more troughs and (ii) positioning a substantially rigid mandrel on the first stringer such that the substantially rigid mandrel is at least partially within the trough;
positioning the panel over the one or more first stringers and over the substantially rigid mandrel such that the first side of the panel faces toward the one or more first stringers and toward the substantially rigid mandrel, and the second side of the panel faces away from the one or more first stringers and away from the substantially rigid mandrel; and
for each second stringer of the one or more second stringers, (i) positioning a flexible mandrel on the second side of the panel and (ii) positioning the second stringer over the flexible mandrel.

16. The method of claim 15 , wherein the first side of the panel is substantially planar and wherein the second side of the panel is contoured.

17. The method of claim 15 further comprising bagging the one or more first stringers, the substantially rigid mandrel, the panel, the flexible mandrel, and the one or more second stringers in a vacuum bag.

18. The method of claim 17 further comprising at least partially vacuuming the vacuum bag.

19. The method of claim 18 further comprising co-curing the one or more first stringers, the panel, and the one or more second stringers.

20. A system for manufacturing a cured composite structure comprising a panel having a first side and a second side opposed from the first side, one or more first stringers connected to the first side, and one or more second stringers connected to the second side, the system comprising:
a rigid tool that defines one or more troughs therein;
one or more substantially rigid mandrels, each substantially rigid mandrel positioned within a first cavity defined between a first stringer of the one or more first stringers and the first side of the panel, wherein the one or more first stringers and the one or more substantially rigid mandrels are at least partially received in the one or more troughs of the rigid tool;
one or more flexible mandrels, each flexible mandrel positioned within a second cavity defined between a second stringer of the one or more second stringers and the second side of the panel; and
a curing oven configured to receive therein the panel, the one or more first stringers, the one or more second stringers, the one or more substantially rigid mandrels, and the one or more flexible mandrels.

21. The system of claim 20 wherein the first side of the panel is substantially planar.

22. The system of claim 21 wherein the second side of the panel is contoured.

23. The system of claim 20 wherein the one or more first stringers are elongated and define a first path of elongation, and wherein the one or more second stringers are elongated and define a second path of elongation.

Assignees

• Boeing Co

Inventors

• Heath Richard E
• Prause Richard A
• Modin Andrew E

Classifications

• B29L2031/3076

  Aircrafts (blades, propellers B29L2031/08) · CPC title

• B29C70/543

  Fixing the position or configuration of fibrous reinforcements before or during moulding (for non-woven fabrics D04H3/08) · CPC title

• B29C70/44 Primary

  using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding · CPC title

• B29D99/0014 Primary

  provided with ridges or ribs, e.g. joined ribs · CPC title

• B64F5/00

  Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for · CPC title