# US 2014/0227479 A1 · Composite laminate including beta-reinforcing fibers

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- Number: US 2014/0227479 A1
- Document ID: US20140227479A1
- Status: Published application
- Kind: A1
- Application number: 14/252,764
- Filed: 2014-04-14
- Published: 2014-08-14
- Earliest claimed: 2005-03-31
- Assignees: The Boeing Company
- Applicants: The Boeing Company
- Inventors: Max U. Kismarton
- Web page: https://patentgrep.com/patent/US20140227479A1

## CPC

- B32B 5/12: characterised by the relative arrangement of fibres or filaments of {different layers, e.g. the fibres or filaments being parallel or perpendicular to each other}
- B29C 65/562: {using extra joining elements, i.e. which are not integral with the parts to be joined (using plastic snap elements B29C65/58; using plastic rivets B29C65/601)}
- B29C 65/564: {hidden in the joint, e.g. dowels or Z-pins (B29C65/603 takes precedence)}
- B29C 66/112: {Single lapped joints}
- B29C 66/1122: {Single lap to lap joints, i.e. overlap joints (B29C66/45, B29C66/472, B29C66/52272 take precedence)}
- B29C 66/131: {Single flanged joints, i.e. one of the parts to be joined being rigid and flanged in the joint area}
- B29C 66/474: {said single elements being substantially non-flat}
- B29C 66/524: {Joining profiled elements}
- B29C 66/721: {Fibre-reinforced materials (B29C66/729 takes precedence)}
- B29C 66/72141: {Fibres of continuous length}
- B29C 70/202: {arranged in parallel planes or structures of fibres crossing at substantial angles, e.g. cross-moulding compound [XMC] (B29C70/207 takes precedence)}
- B29C 70/207: {arranged in parallel planes of fibres crossing at substantial angles}
- B29C 70/228: {the structure being stacked in parallel layers with fibres of adjacent layers crossing at substantial angles}
- B29C 70/30: Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B32B 1/00: Layered products having a non-planar shape
- B32B 5/26: another layer {next to it} also being fibrous or filamentary {(relative arrangement of fibres or filaments of different layers B32B5/12)}
- B32B 5/28: impregnated with or embedded in a plastic substance {(not used)}
- B64C 1/064: {Stringers; Longerons}
- B64C 1/12: Construction or attachment of skin panels
- B64C 3/182: {Stringers, longerons}
- B64C 3/26: Construction, shape, or attachment of separate skins, e.g. panels
- B29C 66/7212: {characterised by the composition of the fibres}
- B29K 2101/00: Use of unspecified macromolecular compounds as moulding material {(use of unspecified rubbers B29K2021/00)}
- B29K 2307/00: Use of elements other than metals as reinforcement
- B29K 2707/04: Carbon
- B29L 2031/3076: {Aircrafts (blades, propellers B29L2031/08)}
- B32B 2250/20: All layers being fibrous or filamentary
- B32B 2260/023: Two or more layers
- B32B 2260/046: Synthetic resin
- B32B 2262/106: Carbon fibres, e.g. graphite fibres
- B64C 2001/0072: {from composite materials}
- Y02T 50/40: Weight reduction
- Y10T 428/24124: Fibers
- B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B29C: SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING (making preforms B29B11/00; making laminated products by combining previously unconnected layers which become one product whose layers will remain together B32B37/00 - B32B41/00)
- B64C: AEROPLANES; HELICOPTERS
- B29K: INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR {MOULDS, } REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29L: INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A composite laminate comprises a plurality of plies of reinforcing fibers. At least some of the plies have reinforcing fibers oriented at ±α with respect to an axis of primary loading, where α is between 2 and 12 degrees. At least some of the plies have reinforcing fibers oriented at ±β with respect to the axis of primary loading, where β is between 50 and 85 degrees.

## Claims

### Claim 1

A composite laminate comprising a plurality of plies of reinforcing fibers;
at least some of the plies having reinforcing fibers oriented at ±α with respect to an axis of primary loading, where α is between 2 and 12 degrees; at least some of the plies having reinforcing fibers oriented at ±β with respect to the axis of primary loading, where β is between 50 and 85 degrees.

### Claim 2 (depends on 1)

The laminate of claim 1, wherein α is between 2 and 8 degrees.

### Claim 3 (depends on 1)

The laminate of claim 1, wherein α is between 3 and 5 degrees.

### Claim 4 (depends on 1)

The laminate of claim 1, wherein the reinforcing fibers oriented at ±α constitute at least 50% of the total number of fibers.

### Claim 5 (depends on 1)

The laminate of claim 1, further comprising a polymer matrix, wherein the fibers include carbon fibers in a polymer matrix.

### Claim 6 (depends on 1)

The laminate of claim 1, wherein all fibers in the laminate consist of the fibers oriented at ±α and ±β; and wherein 20-30% of the total fibers are oriented at ±β to reach bearing strength levels similar to traditional 0/+45/−45/90 degree hard laminates.

### Claim 7 (depends on 1)

A system comprising the laminate of claim 1.

### Claim 8

A composite beam comprising plies of α-reinforcing fibers oriented at ±α with respect to an axis of primary loading, where α is between 2 and 12 degrees; and plies having β-reinforcing fibers oriented at ±β with respect to the axis of primary loading, where β is between 50 and 85 degrees.

### Claim 9 (depends on 8)

The beam of claim 8, including a base and a web, at least one of the base and web including the plies of the α-reinforcing and the plies of the β-reinforcing fibers, at least 50% of the reinforcing fibers being the α-reinforcing fibers.

### Claim 10 (depends on 8)

The beam of claim 8, wherein the base has fastener apertures, whereby the α-reinforcing fibers in the base are oriented at ±α degrees to suppress or delay splitting caused by the fastener apertures.

### Claim 11 (depends on 8)

The beam of claim 8, wherein α is between 2 and 8 degrees.

### Claim 12 (depends on 8)

The beam of claim 8, wherein α is between 3 and 5 degrees.

### Claim 13 (depends on 9)

The beam of claim 9, wherein the β-reinforcing fibers are biased towards outer surfaces of the webs to increase stiffness in buckling and transverse bending.

### Claim 14 (depends on 8)

The beam of claim 8, further comprising a polymer matrix; wherein the α-reinforcing and the β-reinforcing fibers include carbon fibers embedded in the polymer matrix.

### Claim 15 (depends on 8)

A system comprising the beam of claim 8.

### Claim 16

A system comprising a beam including a base and a web, the web including plies of reinforcing fibers for providing strength in tension and compression along an axis of primary loading, the web also including plies of reinforcing fibers oriented at ±β degrees with respect to the axis of primary loading, where β is between 50 and 85 degrees, wherein the fibers oriented at ±β degrees are biased towards outer surfaces of the web to increase stiffness in buckling and transverse loading.

### Claim 17 (depends on 16)

The system of claim 16, wherein the reinforcing fibers for providing strength in tension and compression are oriented at ±α with respect to the axis of primary loading, where α is between 2 and 12 degrees.

### Claim 18 (depends on 16)

The system of claim 16, wherein the reinforcing fibers are carbon fibers embedded in a polymer matrix.

### Claim 19 (depends on 16)

The system of claim 16, wherein the reinforcing fibers oriented at ±β degrees are biased towards an outer surface of the web to increase stiffness in buckling and transverse bending.

### Claim 20 (depends on 16)

The system of claim 16, wherein α is between 3 and 5 degrees.