Laminated composite structures with interlaminar corrugations to improve impact damage resistance, and system and method of forming the same

Patent metadata

Field	Value
Publication number	US-10933595-B2
Application number	US-201815898214-A
Country	US
Kind code	B2
Filing date	Feb 15, 2018
Priority date	Feb 15, 2018
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

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 system for forming a laminated composite structure having one or more interlaminar corrugations, and having improved impact damage resistance and improved strength, the system comprising:
a 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
one or more gap elements coupled between the first laminate and the second laminate, the one or more gap elements forming a gap area between the first laminate and the second laminate, the one or more gap elements and the first laminate and the second laminate comprising a same composite material; and

a pressurizing system coupled to the laminate assembly, to create a low pressure region in the gap area for forming the one or more interlaminar corrugations, during consolidation and curing of the laminate assembly, and to form the laminated composite structure having the one or more interlaminar corrugations formed within a plurality of stacked layers of the laminated composite structure, and each of the one or more interlaminar corrugations of the laminated composite structure having a substantially sinusoidal shaped profile,
wherein 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.

2. The system of claim 1 further comprising a first end plate and a second end plate, positioned, respectively, against opposite sides of the laminate assembly, to secure the laminate assembly within the pressurizing system, and to facilitate a flow direction of resin material and of fiber material, of the laminate assembly, into the gap area, during consolidation and curing of the laminate assembly.

3. The system of claim 1 wherein each of the one or more interlaminar corrugations has a depth and a length dependent on a size of the laminated composite structure formed.

4. The system of claim 3 wherein the depth of each interlaminar corrugation, of the laminated composite structure formed by the system, is in a range of from 0.01 inch to 0.35 inch, and wherein the length of each interlaminar corrugation, of the laminated composite structure formed by the system, is in a range of from 0.20 inch to 0.60 inch.

5. The system of claim 1 wherein the one or more gap elements of the laminate assembly comprise two laminated shims positioned opposite each other, along longitudinal edges of the first laminate, to control a depth and a length of the one or more interlaminar corrugations formed during consolidation and curing of the laminate assembly.

6. The system of claim 1 wherein the pressurizing system comprises a vacuum seal system having a vacuum bagging assembly and a vacuum pump assembly, the vacuum bagging assembly comprising a first film layer, a second film layer, a first breather material layer, a vacuum bag film, and a sealant material.

7. The system of claim 1 wherein the laminated composite structure comprises one of, a laminated composite test coupon, a laminated composite blade stringer, a laminated composite skin panel, a laminated composite spar, and a laminated composite flight control surface.

8. A method of forming a laminated composite structure having one or more interlaminar corrugations, and having improved impact damage resistance and improved strength, the method comprising the steps of:
coupling a first laminate to a first tool plate, the first tool plate having a first side and a second side, each having a planar profile;
coupling a second laminate to a second tool plate, the second tool plate having a first side and a second side, each having a planar profile;
coupling the first laminate to the second laminate, so that 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;
coupling one or more gap elements coupled between the first laminate and the second laminate to form a laminate assembly and to form a gap area between the first laminate and the second laminate, the one or more gap elements and the first laminate and the second laminate comprising a same composite material;
using a pressurizing system to consolidate the laminate assembly, and to create a low pressure region in the gap area for forming the one or more interlaminar corrugations; and
curing the laminate assembly to form the laminated composite structure having the one or more interlaminar corrugations formed within a plurality of stacked layers of the laminated composite structure, and each of the one or more interlaminar corrugations of the laminated composite structure having a substantially sinusoidal shaped profile, wherein the formed laminated composite structure has improved impact damage resistance and improved strength.

9. The method of claim 8 wherein before using the pressurizing system, positioning a first end plate and a second end plate, respectively, against opposite sides of the laminate assembly, to facilitate a flow direction of resin material and of fiber material, of the laminate assembly, into the gap area, during consolidation and curing of the laminate assembly.

10. The method of claim 8 wherein coupling the first laminate to the first tool plate further comprises aligning the first laminate over the first tool plate, so that a side end of the first laminate is aligned flush to a side of the first tool plate, and further wherein coupling the second laminate to the second tool plate further comprises aligning the second laminate over the second tool plate, so that a side end of the second laminate is aligned flush to a side of the second tool plate.

11. The method of claim 8 wherein coupling the one or more gap elements further comprises positioning and coupling two gap elements opposite each other, along longitudinal edges of the first laminate, to control a depth and a length of the one or more interlaminar corrugations formed during consolidation and curing of the laminate assembly.

12. The method of claim 8 wherein using the pressurizing system comprises coupling the pressurizing system to and around the laminate assembly, the pressurizing system comprising a vacuum seal system with a vacuum bag assembly and a vacuum pump assembly.

13. The method of claim 8 wherein curing the laminate assembly to form the laminated composite structure, further comprises curing the laminate assembly to form the laminated composite structure comprising one of, a laminated composite test coupon, a laminated composite blade stringer, a laminated composite skin panel, a laminated composite spar, and a laminated composite flight control surface.

14. A system for forming a laminated composite structure having one or more interlaminar corrugations, and having improved impact damage resistance and improved strength, the system comprising:
a 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

Assignees

• Boeing Co

Inventors

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

Classifications

• Y10T428/24628

  Nonplanar uniform thickness material · CPC title

• B64C2001/0072

  from composite materials · CPC title

• B64C3/182

  Stringers, longerons · CPC title

• B32B2605/18

  Aircraft · CPC title

• B32B2307/558

  Impact strength, toughness · CPC title