Wrinkle Reduction in Formed Composite Laminates

• US 20170368815A1
• Filed: 06/28/2016
• Published: 12/28/2017
• Est. Priority Date: 06/28/2016
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Blom-Schieber, Adriana Willempje
• Granted Patent: US 10,449,754 B2
• Time in Patent Office: Days
• CPC Class Codes: B29C 70/207 arranged in parallel planes of fibres crossing at substantial angles
• CPC Class Codes: B29C 70/34 and shaping or impregnating by compression , i.e. combined with compressing after the lay-up operation
• CPC Class Codes: B29D 99/0003 Producing profiled members, e.g. beams
• CPC Class Codes: B29L 2031/001 Profiled members, e.g. beams, sections
• CPC Class Codes: B32B 2305/08 Reinforcements
• CPC Class Codes: B32B 2307/514 Oriented
• CPC Class Codes: B32B 38/1866 conforming the layers or laminate to a convex or concave profile
• CPC Class Codes: B32B 5/26 another layer next to it also being fibrous or filamentary relative arrangement of fibres or filaments of different layers B32B5/12
• CPC Class Codes: B32B 7/03 with respect to the orientation of features direction of fibres or filaments B32B5/12
• CPC Class Codes: G06F 2113/24 Sheet material
• CPC Class Codes: G06F 2113/26 Composites
• CPC Class Codes: G06F 30/20 Design optimisation, verification or simulation optimisation, verification or simulation of circuit designs G06F30/30

Abstract

Wrinkling of a contoured composite laminate part during forming to contour is reduced by using laminate plies having off-angle reinforcing fibers that provide the part with primary axial strength along a major axis of loading.

Claims

1. A method of making a composite laminate part exhibiting reduced wrinkling, and having a desired contour along a major axis of loading:

laying up a substantially flat stack of fiber plies each having a unidirectional fiber orientation, wherein at least some of the plies provide the part with primary axial stiffness along the major axis of loading, including orienting the plies providing the primary axial stiffness at off-angles relative to the major axis of loading;

forming the stack to a desired cross sectional shape; and

,

forming the stack to the desired contour along the major axis of loading,

wherein during the forming, strain on the plies providing the primary axial stiffness is reduced by their off-angle orientation.

2. The method of claim 1, wherein the plies providing primary axial stiffness are oriented at off-angles within ranges of approximately +5°

to +30°

, and approximately −

5°

to −

30°

.

3. The method of claim 1, wherein laying up the flat stack includes orienting all of the plies in the stack at angles greater than approximately ±

5°

relative to the major axis of loading.

4. The method of claim 1, wherein orienting the plies is performed such that that fibers in the plies providing primary axial stiffness transition along their length during the forming of the desired contour from a compressive state to a neutral state, and from a neutral state to a tensile state.

5. The method of claim 1, further comprising:

calculating thickness values for the plies;

performing discrete ply thickness integer optimization;

filtering the results of calculating thickness values for the plies and the discrete ply thickness integer optimization; and

optimizing the shape and stacking sequence of the plies.

6. A method of making a contoured composite laminate part having a high aspect ratio, a major axis of loading and a plurality of zones along its length respectively having desired stiffnesses, comprising:

selecting a set of fiber angles for plies of unidirectional reinforcing fibers;

determining, for each of the fiber angles, a number of plies in each of the zones required to provide a desired set of in-plane laminate properties in the zone;

determining a shape and stacking sequence of the plies;

laying up the plies into a flat stack using the stacking sequence; and

forming the flat stack into the shape of the contoured composite laminate part.

7. The method of claim 6, wherein:

determining the fiber angles includes selecting a plurality of possible combinations of fiber angles, and

determining a number of plies in each of the zones required to provide a desired set of in-plane laminate properties in the zone is performed for each of the possible combinations of angles.

8. The method of claim 7, wherein:

determining the fiber angles includes eliminating certain of the possible combinations of fiber angles using a set of composite laminate design rules.

9. The method of claim 6, wherein the set of fiber angles include fiber orientations relative to the major axis of loading of θ

₁, θ

₂, θ

₃, where 0<

θ

₁<

θ

₂≦

θ

₃≦

90°

.

10. The method of claim 6, wherein:

θ

₂−

θ

₁≦

45°

, and

θ

₃−

θ

₂≦

45°

.

11. The method of claim 9, wherein θ

₁ is selected to be between approximately 5° and

30°

.

12. The method of claim 7, wherein:

determining the number of plies in each of the zones includes limiting the number of plies to a discrete value by performing discrete ply thickness integer optimization.

13. The method of claim 12, wherein determining the number of plies in each of the zones includes filtering the results of the discrete ply thickness integer optimization based on an allowed deviation of effective laminate properties from the desired set of in-plane laminate properties.

14. A method of making a composite laminate stiffener having a major axis of loading, and contoured both longitudinally and transversely, comprising:

laying up a substantially flat stack of fiber plies each having a unidirectional fiber orientation, wherein at least some of the plies provide the stiffener with primary axial stiffness along the major axis of loading, including orienting the plies providing the primary axial stiffness at off-angles relative to the major axis of loading;

forming the stack to desired transverse and longitudinal contours, wherein during the forming the fibers in plies providing the stiffener with primary axial stiffness transition along their lengths from a compression state, to a neutral state, and from the neutral state to a tensile state; and

wherein during the forming, strain on the plies providing the primary axial stiffness is reduced by their off-angle orientation.

15. The method of claim 14, wherein the off-angle orientations of the plies providing the primary axial stiffness reduces the length to which the fibers of the plies are compressed and causes a portion of the compression is converted to shear deformation.

16. The method of claim 14, wherein the composite laminate stiffener is a stringer having a hat shape in cross-section, including a cap, a pair of webs and a pair of flanges, and wherein during forming:

the fibers in the plies at the cap are in the compression state,

the fibers in the plies in the webs are in the neutral state, and

the fibers in the flanges are in the tensile state.

17. The method of claim 14, wherein fibers in the plies providing the primary axial stiffness are shorter in length than the length of the composite laminate stiffener whereby transverse slip between the plies occurs during forming which reduces compression of the fibers.

18. The method of claim 14, wherein orienting the plies providing the primary axial stiffness at off-angles reduces the compression loading on the fibers in the plies during the forming.

19. The method of claim 14, wherein composite laminate stiffener is an existing stiffener design, and the method further comprises:

determining continuous ply thickness values for various ply angle combinations that match the stiffness and thickness of the existing stiffener design;

performing discrete ply thickness integer optimization, including calculating a number of plies with discrete ply thicknesses;

filtering the results of the ply thickness integer optimization, wherein a laminate design is selected that best reduces wrinkles during the forming; and

generating layup information, including determining ply shapes and the stacking sequence conforming to a desired set of stacking sequence and manufacturability rules.

20. The method of claim 14, wherein the composite laminate stiffener includes a plurality of zones along its length respectively having differing stiffness requirements, and the method further comprises:

selecting orientations of the plies and a number of plies per orientation for each of the zones; and

then, after selecting the orientations and the number of plies per orientation, selecting shapes of the plies in each of the zones.

21. A method of forming a composite laminate stiffener having a primary axis of loading, comprising:

laying up a flat composite laminate stack of plies of reinforcing fibers;

forming the composite laminate stack such that the fibers in at least some of the plies are subjected to compression loading; and

shortening a length over which the fibers are compressed.

22. The method of claim 21, wherein the compression loading causes axial strain in the fibers, and the method further comprises:

reducing the axial strain in the fibers on those portions of the plies subjected to compression during forming.

23. The method of claim 21 wherein orienting the fibers is performed such that the reinforcing fibers transition from a compressive state to a neutral state, and from a neutral state to a tensile state.

24. The method of claim 21, further comprising:

orientating the fibers at angles relative to the primary axis of loading such that friction between plies is reduced which allows slippage between the plies.

25. The method of claim 24, wherein the angles of the fibers in the plies subjected to compression during forming are between approximately +5°

and +30°

, and between approximately −

5° and

−

30°

.

26. A method of forming a composite laminate stiffener contoured along a primary axis of loading, comprising:

laying up a flat stack of plies of reinforcing fibers, some of the plies providing the stiffener with primary axial stiffness;

forming the flat stack to a desired contour along the primary axis of loading, wherein the forming places the fibers in the plies providing primary axial stiffness in compression and causes stretching of the fibers;

reducing the compression of the fibers in the plies providing primary axial stiffness by reducing a length over which the fibers are compressed during the forming; and

converting a portion of the stretching into shear deformation.

27. The method of claim 26, wherein reducing the compression of the fibers includes orienting the plies providing primary axial stiffness at off-angles relative to the primary axis of loading.

28. The method of claim 26, wherein reducing the compression includes:

relaxing the fibers in the plies providing primary axial stiffness such that a portion of the length of the fibers transitions from a compression state to a neutral state and then to a tensile state.

29. The method of claim 28, wherein reducing the compression includes:

providing for transverse slip between the plies during the forming.

30. The method of claim 29, wherein reducing the compression includes:

reducing loading on the fibers during the forming to thereby reduce strain on the fibers in the plies providing primary axial stiffness.

31. A composite laminate stiffener contoured along a major axis of loading, comprising:

a plurality of laminated plies of unidirectional reinforcing fibers held in a plastic matrix, wherein all of the plies have fiber orientations at off-angles relative to the major axis of loading.

32. The composite laminate stiffener of claim 31, wherein the plies have fiber orientations relative to the major axis of loading of θ

₁, θ

₂, θ

₃, and 0<

θ

₁<

θ

₂≦

θ

₃≦

90°

.

33. The composite laminate stiffener of claim 32, wherein θ

₁ is between approximately 5° and

30°

.

34. The composite laminate stiffener of claim 32, wherein the plies have fiber orientations relative to the major axis of loading of −

θ

₁, −

θ

₂, −

θ

₃, and 0<

−

θ

₁<

−

θ

₂≦

−

θ

₃≦

90°

.

35. The composite laminate stiffener of claim 34, wherein −

θ

₁ is between approximately −

5° and

−

30°

.

36. The composite laminate stiffener of claim 31, wherein the plurality of the plies vary in number along the major axis of loading and define zones along the composite laminate stiffener respectively having different stiffness properties.

37. The composite laminate stiffener of claim 31,

wherein:

some of the plies are continuous and other of the plies are discontinuous along the major axis of loading, and

the off-angles include balanced pairs of + and −

angles.