Laminated composite structures with interlaminar corrugations to improve impact damage resistance

Patent metadata

Field	Value
Publication number	US-11801656-B2
Application number	US-202117156508-A
Country	US
Kind code	B2
Filing date	Jan 22, 2021
Priority date	Feb 15, 2018
Publication date	Oct 31, 2023
Grant date	Oct 31, 2023

Abstract

There is provided a laminated composite structure having improved impact damage resistance and improved strength. The laminated composite structure has a plurality of stacked layers of a composite material. The plurality of stacked layers have one or more interlaminar corrugations formed within the plurality of stacked layers. Each interlaminar corrugation has a substantially sinusoidal shaped profile, and has a depth and a length dependent on a size of the laminated composite structure formed. The laminated composite structure with the one or more interlaminar corrugations has improved strength and improved impact damage resistance at an exposed edge of the laminated composite structure, when the exposed edge is subjected to an impact force.

First claim

What is claimed is:

1. A laminated composite structure having improved impact damage resistance and improved strength, the laminated composite structure comprising:
a plurality of stacked layers comprised of a composite material, the plurality of stacked layers having interlaminar corrugations formed within the plurality of stacked layers of the laminated composite structure, each interlaminar corrugation having a substantially sinusoidal shaped profile, and having a depth in a range of from 0.01 inch to 0.35 inch, and a length in a range of from 0.20 inch to 0.60 inch, wherein the layers of the plurality of stacked layers are directly adjacent to each other with the interlaminar corrugations nested within each other,
wherein the laminated composite structure is selected from the group consisting of a laminated composite blade stringer, a laminated composite skin panel, a laminated composite spar, a laminated composite flight control surface, or a laminated composite test coupon, and,
wherein the laminated composite structure with the interlaminar corrugations has improved strength and improved impact damage resistance at an exposed edge of the laminated composite structure when the exposed edge is subjected to an impact force, as compared to a same laminated composite structure not having the interlaminar corrugations.

2. The laminated composite structure of claim 1 wherein the depth of each interlaminar corrugation is in a range of from 0.01 inch to 0.024 inch.

3. The laminated composite structure of claim 1 wherein the length of each interlaminar corrugation is in a range of from 0.35 inch to 0.55 inch.

4. The laminated composite structure of claim 1 wherein the exposed edge is covered with an edge covering to provide protection to the exposed edge by absorbing and distributing the impact force and by inhibiting separation of the plurality of stacked layers.

5. The laminated composite structure of claim 1 wherein each interlaminar corrugation has a predetermined ratio of the length to the depth.

6. The laminated composite structure of claim 1 wherein the composite material comprises at least one member selected from the group consisting of fiber reinforced plastic, carbon fiber reinforced plastic (CFRP), thermoplastic composite material, bismaleimide (BMI) prepreg, carbon fiber reinforced polyetheretherketone (PEEK), carbon fiber reinforced polyetherketoneketone (PEKK), carbon fiber reinforced polyethyleneimine (PEI), polyethylene terephthalate (PET), polytrimethylene terephthalate (PTT), polypropylene (PP), polyethylene (PE), polyamide (PA), polyphenylene sulfide (PPS), aramid, co-polyester, fiberglass, ceramic, a nonwoven fabric material, and a woven fabric material.

7. The laminated composite structure of claim 1 wherein the laminated composite structure is the laminated composite blade stringer, and further wherein the interlaminar corrugations are transverse to a web of the laminated composite blade stringer.

8. A laminated composite structure for an aircraft, the laminated composite structure having interlaminar corrugations and having improved impact damage resistance and improved strength, and the laminated composite structure comprising:
a plurality of stacked layers comprised of a composite material, the plurality of stacked layers having the interlaminar corrugations formed within the plurality of stacked layers of the laminated composite structure, each interlaminar corrugation having a substantially sinusoidal shaped profile, a length in a range of from 0.20 inch to 0.60 inch, wherein the layers of the plurality of stacked layers are directly adjacent to each other with the interlaminar corrugations nested within each other, and each laminar corrugation having a depth in a range of from 0.01 inch to 0.35 inch, wherein a size of the length and a size of the depth are controlled with positioning of one or more laminated shims along a laminate assembly during consolidation and curing of the laminate assembly to form the laminated composite structure,
wherein the laminated composite structure having the one or more interlaminar corrugations is selected from the group consisting of a laminated composite blade stringer, a laminated composite skin panel, a laminated composite spar, a laminated composite flight control surface, and a laminated composite test coupon, and,
wherein the laminated composite structure for the aircraft with the interlaminar corrugations has improved strength and improved impact damage resistance at an exposed edge of the laminated composite structure when the exposed edge is subjected to an impact force, as compared to a same laminated composite structure not having the interlaminar corrugations.

9. The laminated composite structure of claim 8 wherein the length of each interlaminar corrugation is in a range of from 0.35 inch to 0.55 inch.

10. The laminated composite structure of claim 8 wherein the laminated composite structure is the laminated composite blade stringer, and further wherein the interlaminar corrugations are transverse to a web of the laminated composite blade stringer.

11. The laminated composite structure of claim 8 wherein the composite material comprises at least one member selected from the group consisting of fiber reinforced plastic, carbon fiber reinforced plastic (CFRP), thermoplastic composite material, bismaleimide (BMI) prepreg, carbon fiber reinforced polyetheretherketone (PEEK), carbon fiber reinforced polyetherketoneketone (PEKK), carbon fiber reinforced polyethyleneimine (PEI), polyethylene terephthalate (PET), polytrimethylene terephthalate (PTT), polypropylene (PP), polyethylene (PE), polyamide (PA), polyphenylene sulfide (PPS), aramid, co-polyester, fiberglass, ceramic, a nonwoven fabric material, and a woven fabric material.

12. The laminated composite structure of claim 8 wherein the exposed edge is covered with an edge covering to provide protection to the exposed edge by absorbing and distributing the impact force and by inhibiting separation of the plurality of stacked layers.

13. The laminated composite structure of claim 8 wherein each of the interlaminar corrugations has a predetermined ratio of the length to the depth.

14. The laminated composite structure of claim 8 wherein the laminated composite structure with the interlaminar corrugations is formed using a pressurizing system coupled to a laminate assembly to create a low pressure region in a gap area for forming the interlaminar corrugations during consolidation and curing of the laminate assembly, the laminate assembly comprising:
a first laminate coupled to a second laminate, the first laminate coupled to a first tool plate and the second laminate coupled to a second tool plate, the first tool plate having a first side and a second side, each having a planar profile, and the second tool plate having a first side and a second side, each having a planar profile, and wherein the first laminate and the second laminate are positioned between the first tool plate and the second tool plate in a stacked configuration with the first tool plate separate from the second tool plate; and
two laminated shims positioned opposite each other, along longitudinal edges of the first laminate, the two laminated shims coupled between the first laminate and the second laminate, and forming the gap area between the first laminate and the second laminate, the two laminated shims and the first laminate and the second laminate comprising a same composite material.

15. A laminated composite blade stringer for an aircraft, the laminated composite blade stringer comprising:
a web comprising:
a first web portion

Assignees

• Boeing Co

Inventors

• Matsumoto Noah T
• Terrell Bernice E
• Lee Michael A
• Morris John D

Classifications

• B32B3/02 Primary

  characterised by features of form at particular places, e.g. in edge regions {(non-uniform thickness B32B3/263)} · CPC title

• B29C70/342

  using isostatic pressure · CPC title

• B29C70/549

  Details of caul plates, e.g. materials or shape · CPC title

• B32B3/26 Primary

  characterised by a particular shape of the outline of the cross-section of a continuous layer; characterised by a layer with cavities or internal voids {(foam layer B32B5/18; layer of synthetic resin characterised by fillers that create voids or cavities B32B27/205); characterised by an apertured layer} · CPC title

• B32B5/26

  another layer {next to it} also being fibrous or filamentary {(relative arrangement of fibres or filaments of different layers B32B5/12)} · CPC title