Flexible double-sided vacuum plate carrier

Abstract

The present invention relates to a flexible double-sided vacuum plate carrier. A composite panel tooling system may include a forming platform having a corrugated surface configured to support a laminate of composite material to form a corrugated composite part. The system may further include a flexible carrier removably disposed on the corrugated surface and including a frame, wherein the frame is configured to receive a set of double-sided vacuum grippers within a set of holes defined within the frame, and wherein each double-sided vacuum gripper of the set of double-sided vacuum grippers is configured to be connected to a pneumatic system to induce a vacuum on a first side of each vacuum gripper to grip the corrugated surface, and to induce a vacuum on a second side of each vacuum gripper to grip the surface of the corrugated composite part after the corrugated composite part has been formed.

Description

Technical Field

[0001] The present disclosure generally relates to the field of composite layup mandrel tools and, in particular, to a flexible double-sided vacuum panel carrier for holding a molded part to a layup mandrel tool. Background Art

[0002] Manufacturing composite components involves several steps such as laying plies on a layup mandrel, curing the plies, inspecting and scanning the cured plies, machining the newly formed part for assembly, and assembling the parts. During each operation, the parts must be placed at a certain location in the production shop. Having separate tools and areas for post-curing operations such as inspecting and scanning the new parts greatly increases the floor space required in the production area for manufacturing composite parts. A larger tooling footprint increases the cost of producing the finished product, especially when the parts are large, such as in the field of aircraft or other large transportation vehicles.

[0003] Assembling parts, especially in the field of aircraft, may require precise dimensions and accuracy. For example, a typical aircraft component may require a root mean square of 0.002 inches overall accuracy. Achieving such accuracy can be difficult with composite parts because once removed from the layup mandrel, the parts can experience some flexure and / or deformation. During assembly, a post-curing scan operation is typically used to obtain information about the surface of the composite panel and the stringers to be attached to the panel. The scan can be used to determine the amount of sacrificial shimming required at the panel-to-rib interface. Shimming requires additional time and resources to assemble the parts, which can also increase the production-related costs. In addition to having to perform shimming, post-curing flexure and deformation also reduce the accuracy of the machined portions of the part, such as drilling. Summary of the Invention

[0004] A flexible carrier tool is described that can be applied between a layup mandrel and a cured composite part. The flexible carrier tool can secure the composite part to the layup mandrel to prevent flexure or deformation during post-curing operations. By converting the layup mandrel tool into a post-curing tool, the utility of the existing tool can be increased and the excessive floor space in the factory can be reduced. In addition, compared to typical post-curing operations, flexure and deformation can be reduced, resulting in no shimming or reduced shimming and improved machining accuracy.

[0005] In one embodiment, a composite panel tooling system includes a forming platform having a contoured surface configured to support a laminate of composite material to form a contoured composite part. The system further includes a flexible carrier removably disposed on the contoured surface and including a frame, wherein the frame is configured to receive a set of double-sided vacuum grippers within a set of holes defined within the frame, and wherein each double-sided vacuum gripper of the set of double-sided vacuum grippers is configured to be connected to a pneumatic system to induce a vacuum on a first side of each vacuum gripper to grip the contoured surface and to induce a vacuum on a second side of each vacuum gripper to grip the surface of the contoured composite part after the contoured composite part has been formed.

[0006] In some embodiments, the frame includes a pair of side members and a set of intercostal members spanning between the pair of side members. In some embodiments, the positions of the intercostal members correspond to predetermined joint positions along the contoured composite part. In some embodiments, the set of holes includes a plurality of holes defined within the pair of side members and within the set of intercostal members. In some embodiments, the set of holes is evenly spaced along the pair of side members and the set of intercostal members. In some embodiments, the frame substantially spans the contoured surface. In some embodiments, each double-sided vacuum gripper of the set of double-sided vacuum grippers includes a first vacuum circuit on a first side and a second vacuum circuit on a second side, wherein the first vacuum circuit is isolated from the second vacuum circuit. In some embodiments, the contoured composite part is a part of an aircraft.

[0007] In one embodiment, a method of composite panel tooling includes supporting a laminate of composite material on a forming platform having a contoured surface to form a contoured composite part. The method further includes positioning a flexible carrier on the contoured surface, the flexible carrier including a frame. The method also includes receiving a set of double-sided vacuum grippers within a set of holes defined within the frame. The method includes connecting each double-sided vacuum gripper of the set of double-sided vacuum grippers to a pneumatic system. The method further includes inducing a vacuum on a first side of each vacuum gripper to grip the contoured surface and, after the contoured composite part has been formed, inducing a vacuum on a second side of each vacuum gripper to grip the surface of the contoured composite part.

[0008] In some embodiments, the frame includes a pair of side members and a set of intercostal members spanning between the pair of side members. In some embodiments, the method further includes forming joints at positions along the corrugated composite part corresponding to the positions of the intercostal members. In some embodiments, the set of holes includes a plurality of holes defined within the pair of side members and a plurality of holes defined within the set of intercostal members. In some embodiments, the set of holes is evenly spaced along the pair of side members and the set of intercostal members. In some embodiments, the frame substantially spans the corrugated surface. In some embodiments, each of the set of double-sided vacuum grippers includes a first vacuum circuit on a first side and a second vacuum circuit on a second side, wherein the first vacuum circuit is isolated from the second vacuum circuit. In some embodiments, the corrugated composite part is a part of an aircraft. In some embodiments, the method includes performing an assembly operation on the corrugated composite part when the corrugated composite part is gripped by the vacuum gripper.

[0009] In one embodiment, the flexible carrier includes a frame having a pair of side members and a set of intercostal members spanning between the pair of side members, wherein the frame is configured to accommodate a set of double-sided vacuum grippers within a set of holes defined within the frame, and wherein each of the set of double-sided vacuum grippers is configured to be connected to a pneumatic system to induce a vacuum on a first side of each vacuum gripper to grip the corrugated surface of a forming platform, and to induce a vacuum on a second side of each vacuum gripper to grip the surface of the composite part after the composite part has been formed. In some embodiments, the frame is cut from a single carbon skateboard. BRIEF DESCRIPTION OF THE DRAWINGS

[0010] Figure 1 An embodiment of a composite panel tooling system and an embodiment of a flexible carrier are shown.

[0011] Figure 2 An embodiment of a composite part assembly and an embodiment of a flexible carrier are shown.

[0012] Figure 3 An embodiment of a flexible carrier is shown.

[0013] Figure 4 An embodiment of a flexible carrier with mounted double-sided vacuum grippers is shown.

[0014] Figure 5 An embodiment of a double-sided vacuum gripper is shown.

[0015] Figure 6 An embodiment of a flexible carrier between a forming platform and a composite part assembly is shown.

[0016] Figure 7A A skateboard for forming a flexible carrier is shown.

[0017] Figure 7B Shows a frame cut from a skateboard.

[0018] Figure 7C Shows a flexible carrier formed by adding a vacuum gripper to the frame.

[0019] Figure 8 Shows an embodiment of a method for processing a composite panel tool.

[0020] Although the present disclosure is susceptible to various modifications and alternative forms, specific embodiments thereof have been shown by way of example in the drawings and will be described in detail herein. However, it should be understood that the present disclosure is not intended to be limited to the particular forms disclosed. On the contrary, it is intended to cover all modifications, equivalents, and alternative forms falling within the scope of the present disclosure. Detailed Description

[0021] Reference Figure 1 , which shows an embodiment of a composite panel tooling system 100. The system 100 may include a forming platform 102 and a flexible carrier 110. Figure 1 The specific example in is directed to a tooling system for forming a stabilizer of an aircraft. However, the described systems and methods may be applied to the formation of any composite part for any vehicle, and are not limited to any particular application.

[0022] The forming platform 102 may have a corrugated surface 104 configured to support a laminate of composite material. It may be supported by a truss system 120 that ensures the proper shape of the corrugated surface. The truss system 120 may also raise the height of the forming platform 102 to provide access for workers to prepare the laminate. In addition to other systems, various access points 122 may also be positioned within the support truss system 120 to provide vacuum access to ensure uniformity of the entire formed part.

[0023] The flexible carrier 110 may be removably disposed on the corrugated surface 104. By flexing, the flexible carrier 110 can conform to the corrugated surface 104 and may be configured to pneumatically grip the corrugated surface 104. For example, the flexible carrier 110 may include at least one double-sided vacuum gripper 402. When one side of the at least one double-sided gripper 402 can grip the corrugated surface 104, the other side can grip the formed and cured part, thereby fixing the part to the corrugated surface 104. In fact, the flexible carrier 110 may include a plurality of vacuum grippers to hold the part evenly. In addition, as Figure 1As shown, the flexible carrier 110 can substantially span the corrugated surface 104 to secure the part along its entire length. As used herein, the term "substantially" means that the flexible carrier spans the entire corrugated surface 104 minus a small boundary at the edges where there is no significant flexure in the formed and cured laminate. The flexible carrier 110 is further described herein.

[0024] Having separate tools and areas in the assembly shop for post-curing processes such as inspecting and scanning for defects in new parts greatly increases the floor space required for manufacturing composite parts. The flexible carrier 110 can enable the forming platform 102 to be reused in subsequent processes to hold the composite part, thereby reducing the total floor space required for production.

[0025] Reference Figure 2 , which shows an embodiment of the composite part assembly 200. The composite part assembly 200 can include a composite part 204 formed from a laminate 202 of composite material. In Figure 2 the example shown, the composite part 204 can be the lower outer skin of a control surface of an aircraft. The composite part assembly 200 can also include at least one additional part 208 attached to the composite part 204. For example, the at least one additional part 208 can be a spar or other lateral structure attached to the composite part 204. Although Figure 2 the composite part 204 is shown as part of an aircraft, the disclosed systems and methods are not limited to aircraft. Other applications are possible.

[0026] Figure 2 Also shown is a flexible carrier 110 removably disposed on the surface 206 of the composite part 204. At least one double-sided vacuum gripper 402 can be configured to secure the flexible carrier 110 against the surface 206 on one side and against Figure 1 the corrugated surface 104 on the other side.

[0027] Reference Figure 3 , which shows an embodiment of the flexible carrier 110. The flexible carrier 110 can include a frame 302. The frame 302 can include a set of holes 308, 310 defined therein. The holes 308, 310 can be configured to accommodate a set of double-sided vacuum grippers therein. The frame 302 can include a pair of side members 304 and a set of intercostal members 306 spanning between the pair of side members 304. The positions of the intercostal members 306 can correspond to predetermined joint positions associated with spars along the corrugated composite part. The frame 302 can be formed by cutting a single composite skate according to a pattern. Various cutting processes can be used, including but not limited to waterjet cutting processes.

[0028] To securely hold the parts, the set of holes 308, 310 can include a plurality of holes 310 defined within the pair of side members 304 and a plurality of holes 308 defined within the set of intercostal members 306. The set of holes 308, 310 can be evenly spaced along the pair of side members 304 and the set of intercostal members 306. The frame 302 can substantially span the corrugated surface 104 ( Figure 1 as shown) to securely hold the parts.

[0029] Reference Figure 4 shows an embodiment of the flexible carrier 110. Figure 4 Also shown is a set of double-sided vacuum grippers 404. Each vacuum gripper 402 can be deposited within a hole in the frame 302. The set of vacuum grippers 404 can be configured to grip the surfaces on both sides of the flexible carrier 110 when activated. For example, each double-sided vacuum gripper 402 can be configured to grip the corrugated surface 104 on one side (as Figure 1 shown), and the surface 206 of the composite part 204 on the other side (as Figure 2 shown).

[0030] Reference Figure 5 shows an embodiment of the double-sided vacuum gripper 402. The double-sided vacuum gripper 402 can be configured to be connected to a pneumatic system 520 to induce a vacuum on the first side 502 of the vacuum gripper 402 to grip the corrugated surface of the lamination tool, and to induce a vacuum on the second side 504 of the vacuum gripper 402 to grip the surface of the corrugated composite part. When the pneumatic system 520 is activated, a seal 506 can extend along the perimeter of the vacuum gripper 402 to create a vacuum relative to the surface. A channel 508 within the vacuum gripper 402 can be in fluid communication with a connection component 510 such as a valve. The pneumatic system 520 can be connected to the connection component 510 and, when activated, can cause a pressure differential to be generated, thereby creating a vacuum when the seal 506 is pressed against the surface. Similar channels can exist on the second side 504 of the vacuum gripper 402 and can be in fluid communication with a second connection component 522.

[0031] During operation, the double-sided vacuum gripper 402 can form a first vacuum circuit 512 on the first side 502 and a second vacuum circuit 514 on the second side 504. The first vacuum circuit 512 can be isolated from the second vacuum circuit 514 so that each of the vacuum circuits 512, 514 can be activated independently. In this way, the surfaces can be gripped and released independently.

[0032] Reference Figure 6 shows an embodiment of the flexible carrier 110 between the forming platform 102 and the composite part assembly 200. To show the flexible carrier 110, the composite part assembly 200 is shown as transparent. As Figure 6As shown, the position 612 of the intercostal member 306 of the flexible carrier 110 may correspond to a predetermined joint position 614 along the corrugated composite part 204. The joint position 614 may correspond to a joint 604 between the composite part 204 and the lateral part 602 within the composite part assembly 200.

[0033] By ensuring that the position 612 of the intercostal member 306 corresponds to the predetermined joint position 614, the flexible carrier 110 can provide support for forming the joint 604 by holding the composite part 204 against the corrugated surface 104 of the forming platform 102 at the precise location of each joint 604. This can prevent deformation and / or flexure of the composite part 204 during the manufacturing process when forming the joint 604. By reducing deformation and flexure, some post-curing processes and tooling can be eliminated. Additionally, by using the forming platform 102 as a support beneath the flexible carrier 110, additional tooling can be eliminated to reduce the tooling footprint.

[0034] Figures 7A-7B The formation of one embodiment of the flexible carrier 110 is shown. Refer Figure 7A , which shows the skateboard 702. The skateboard 702 may include a carbon composite material and may be a single carbon skateboard. It can be formed and cured on a corrugated surface that will later be used as the flexible carrier, such as the corrugated surface 104. In some embodiments, the skateboard 702 may include a flexible material to conform to the corrugated surface without being cured to hold any specific shape.

[0035] Refer Figure 7B , which shows the skateboard 702 after a cutting operation and defining the frame 703. The cutting operation may include a waterjet cutting operation performed by a waterjet cutting tool. Other types of cutters may also be used, including mechanical cutters, punches, templates, etc. The frame 703 may include side members 704, with intercostal members 706 positioned laterally between the side members 704. The frame 703 may correspond to Figure 3 the frame 302. Although the frame 703 includes two side members 704 and many intercostal members 706, in other embodiments, depending on the part being manufactured, other configurations are possible.

[0036] Refer Figure 7C , where a double-sided vacuum gripper 708 has been added to the frame 703 to form the flexible carrier 110. For example, the double-sided vacuum gripper 708 may correspond to the double-sided vacuum gripper 402 and may be used to grip the surfaces on both sides of the flexible carrier 110.

[0037] Refer Figure 8, which shows a method 800 for processing a composite panel tool. Method 800 may include supporting a stack of composite materials on a forming platform having a wavy surface at 802 to form a wavy composite part. For example, the stack 202 may be supported on the wavy surface 104 of the forming platform 102 to form the composite part 204.

[0038] Method 800 may further include positioning a flexible carrier on the wavy surface at 804, the flexible carrier including a frame. For example, the flexible carrier 110 may be positioned on the wavy surface 104.

[0039] Method 800 may also include receiving a set of double-sided vacuum grippers within a set of holes defined within the frame at 806. For example, the set of double-sided vacuum grippers 404 may be inserted into the set of holes 308, 310 defined within the frame 302.

[0040] Method 800 may include connecting each double-sided vacuum gripper of the set of double-sided vacuum grippers to a pneumatic system at 808. For example, each double-sided vacuum gripper 402 may be connected to the pneumatic system 520.

[0041] Method 800 may further include inducing a vacuum on a first side of each vacuum gripper at 810 to grip the wavy surface, and after the wavy composite part has been formed, inducing a vacuum on a second side of each vacuum gripper to grip the surface of the wavy composite part.

[0042] Method 800 may also include performing an assembly operation on the wavy composite part while the wavy composite part is gripped by the vacuum grippers at 812. For example, the vacuum grippers 402 may hold the composite part 204 while performing an assembly operation (such as drilling a pilot hole or attaching additional parts) on the composite part 204.

[0043] In addition, the present disclosure includes embodiments according to the following clauses:

[0044] Clause 1. A composite panel tool processing system (100), comprising:

[0045] A forming platform (102) having a wavy surface (104) configured to support a stack of composite materials (202) to form a wavy composite part (204);

[0046] A flexible carrier (110) removably disposed on a corrugated surface (104) and including a frame (302), wherein the frame (302) is configured to receive a set of double-sided vacuum grippers (404) in a set of holes (308, 310) defined within the frame (302), wherein each double-sided vacuum gripper (402) of the set of double-sided vacuum grippers (404) is configured to be connected to a pneumatic system (520) to induce a vacuum on a first side (502) of each double-sided vacuum gripper (402) to grip the corrugated surface (104), and after a corrugated composite part (204) has been formed, to induce a vacuum on a second side (504) of each double-sided vacuum gripper (402) to grip the surface (206) of the corrugated composite part (204).

[0047] Clause 2. The system according to Clause 1, wherein the frame (302) includes a pair of side members (304) and a set of intercostal members (306) spanning between the pair of side members (304).

[0048] Clause 3. The system according to Clause 2, wherein the position (612) of each intercostal member of the set of intercostal members (306) corresponds to a predetermined joint position (614) along the corrugated composite part (204).

[0049] Clause 4. The system according to Clause 2, wherein the set of holes (308, 310) includes a plurality of holes (308, 310) defined within the pair of side members (304) and within the set of intercostal members (306).

[0050] Clause 5. The system according to Clause 2, wherein the set of holes (308, 310) is evenly spaced along the pair of side members (304) and the set of intercostal members (306).

[0051] Clause 6. The system according to Clause 1, wherein the frame (302) substantially spans the corrugated surface (104).

[0052] Clause 7. The system according to Clause 1, wherein each double-sided vacuum gripper (402) of the set of double-sided vacuum grippers (404) includes a first vacuum circuit on a first side (502) and a second vacuum circuit on a second side (504), wherein the first vacuum circuit is isolated from the second vacuum circuit.

[0053] Clause 8. The system according to Clause 1, wherein the corrugated composite part (204) is part of an aircraft.

[0054] Clause 9. A method for processing a composite panel tool, comprising:

[0055] Support a laminate (202) of composite material on a forming platform (102) having a corrugated surface (104) to form a corrugated composite part (204);

[0056] Position a flexible carrier (110) on the corrugated surface (104), the flexible carrier (110) including a frame (302);

[0057] Accommodate a set of double-sided vacuum grippers (404) within a set of holes (308, 310) defined within the frame (302);

[0058] Connect each double-sided vacuum gripper (402) of the set of double-sided vacuum grippers (404) to a pneumatic system (520);

[0059] Induce a vacuum on a first side (502) of each double-sided vacuum gripper (402) to grip the corrugated surface (104), and after the corrugated composite part (204) has been formed, induce a vacuum on a second side (504) of each double-sided vacuum gripper to grip the surface (206) of the corrugated composite part (204).

[0060] Clause 10. The method according to clause 9, wherein the frame (302) includes a pair of side members (304) and a set of intercostal members (306) spanning between the pair of side members (304).

[0061] Clause 11. The method according to clause 10, further comprising:

[0062] Form joints (604) at positions (612) along the corrugated composite part (204) corresponding to the position (614) of each intercostal member of the set of intercostal members (306).

[0063] Clause 12. The method according to clause 10, wherein the set of holes (308, 310) includes a plurality of holes (310) defined within the pair of side members and a plurality of holes (308) defined within the set of intercostal members (306).

[0064] Clause 13. The method according to clause 10, wherein the set of holes (308, 310) is evenly spaced along the pair of side members (304) and the set of intercostal members (306).

[0065] Clause 14. The method according to clause 9, wherein the frame (302) substantially spans the corrugated surface (104).

[0066] Clause 15. The method according to Clause 9, wherein each of the set of double-sided vacuum grippers (404) includes a first vacuum circuit on a first side (502) and a second vacuum circuit on a second side (504), wherein the first vacuum circuit is isolated from the second vacuum circuit.

[0067] Clause 16. The method according to Clause 9, wherein the corrugated composite part (204) is part of an aircraft.

[0068] Clause 17. The method according to Clause 9, further comprising:

[0069] Performing an assembly operation on the corrugated composite part (204) when the corrugated composite part (204) is held by the double-sided vacuum gripper (402).

[0070] Clause 18. A flexible carrier (110), comprising:

[0071] A frame (302) having a pair of side members (304) and a set of intercostal members (306) spanning between the pair of side members (304), wherein the frame (302) is configured to accommodate a set of double-sided vacuum grippers (404) within a set of holes (308, 310) defined within the frame (302),

[0072] wherein each of the set of double-sided vacuum grippers (404) is configured to be connected to a pneumatic system (520) to induce a vacuum on a first side (502) of each double-sided vacuum gripper (402) to hold the corrugated surface (104) of the forming platform (102), and after the composite part (204) has been formed, to induce a vacuum on a second side (504) of each double-sided vacuum gripper (402) to hold the surface (206) of the composite part (204).

[0073] Clause 19. The flexible carrier (110) according to Clause 18, wherein the frame (302) substantially spans the corrugated surface (104) of the forming platform (102).

[0074] Clause 20. The flexible carrier (110) according to Clause 18, wherein the frame (302) is cut from a single carbon skateboard.

[0075] Although various embodiments have been shown and described, the present disclosure is not limited thereto and will be understood to include all such modifications and variations as would be apparent to one of ordinary skill in the art.

Claims

1. A composite panel tooling system (100) comprising: A forming platform (102) having a corrugated surface (104) configured to support a laminate (202) of composite material to form a corrugated composite part (204); A flexible carrier (110) removably disposed on the corrugated surface (104) and including a frame (302), wherein the frame (302) is configured to receive a set of double-sided vacuum grippers (404) in a set of holes (308, 310) defined within the frame (302), wherein each double-sided vacuum gripper (402) of the set of double-sided vacuum grippers (404) is configured to be connected to a pneumatic system (520) to induce a vacuum on a first side (502) of each double-sided vacuum gripper (402) to grip the corrugated surface (104), and after the corrugated composite part (204) has been formed, to induce a vacuum on a second side (504) of each double-sided vacuum gripper (402) to grip the surface (206) of the corrugated composite part (204).

2. The system according to claim 1, wherein, The frame (302) includes a pair of side members (304) and a set of intercostal members (306) spanning between the pair of side members (304).

3. The system according to claim 2, wherein, The position (612) of each intercostal member of the set of intercostal members (306) corresponds to a predetermined joint position (614) along the corrugated composite part (204).

4. The system according to claim 2, wherein The set of holes (308, 310) includes a plurality of holes (308, 310) defined within the pair of side members (304) and within the set of intercostal members (306).

5. The system according to claim 2, wherein, The set of holes (308, 310) is evenly spaced along the pair of side members (304) and the set of intercostal members (306).

6. The system according to any one of claims 1 to 5, wherein The frame (302) spans the corrugated surface (104), wherein the corrugated composite part (204) is part of an aircraft.

7. The system according to any one of claims 1 to 5, wherein, Each double-sided vacuum gripper (402) of the set of double-sided vacuum grippers (404) includes a first vacuum circuit on the first side (502) and a second vacuum circuit on the second side (504), wherein the first vacuum circuit is isolated from the second vacuum circuit.

8. A method of composite panel tooling, comprising: Supporting a laminate (202) of composite material on a forming platform (102) having a corrugated surface (104) to form a corrugated composite part (204); Positioning a flexible carrier (110) on the corrugated surface (104), the flexible carrier (110) including a frame (302); Receiving a set of double-sided vacuum grippers (404) within a set of holes (308, 310) defined within the frame (302); Connecting each double-sided vacuum gripper (402) of the set of double-sided vacuum grippers (404) to a pneumatic system (520); Vacuum is induced on the first side (502) of each double-sided vacuum gripper (402) to grip the corrugated surface (104), and after the corrugated composite part (204) has been formed, vacuum is induced on the second side (504) of each double-sided vacuum gripper to grip the surface (206) of the corrugated composite part (204).

9. The method according to claim 8, wherein The frame (302) includes a pair of side members (304) and a set of intercostal members (306) spanning between the pair of side members (304).

10. The method according to claim 9, further comprising: Forming joints (604) at positions (612) along the corrugated composite part (204) corresponding to the positions (614) of each of the intercostal members of the set of intercostal members (306).

11. The method according to claim 9, wherein, The set of holes (308, 310) includes a plurality of holes (310) defined within the pair of side members and a plurality of holes (308) defined within the set of intercostal members (306).

12. The method according to claim 9, wherein, The set of holes (308, 310) is evenly spaced along the pair of side members (304) and the set of intercostal members (306).

13. The method according to any one of claims 8 to 12, wherein Positioning the frame (302) to span the corrugated surface (104), wherein the corrugated composite part (204) is part of an aircraft.

14. The method according to any one of claims 8 to 12, wherein Each double-sided vacuum gripper (402) of the set of double-sided vacuum grippers (404) includes a first vacuum circuit on the first side (502) and a second vacuum circuit on the second side (504), wherein the first vacuum circuit is isolated from the second vacuum circuit.

15. The method according to any one of claims 8 to 12, further comprising: Performing an assembly operation on the corrugated composite part (204) when the corrugated composite part (204) is gripped by the double-sided vacuum gripper (402).

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