# US 6,194,081 B1 · Beta titanium-composite laminate

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 6,194,081 B1
- Document ID: US6194081B1
- Status: Granted
- Kind: B1
- Application number: 09/247,647
- Filed: 1999-02-09
- Granted: 2001-02-27
- Earliest claimed: 1993-10-18
- Assignees: Ticomp, Inc.
- Inventors: William R. Kingston
- Web page: https://patentgrep.com/patent/US6194081B1

## CPC

- B32B 38/0036: {Heat treatment (for heating or cooling of layers during lamination B32B37/06, B32B37/08)}
- A63B 53/10: Non-metallic shafts
- 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 15/08: of synthetic resin
- A63B 59/50: Substantially rod-shaped bats for hitting a ball in the air, e.g. for baseball
- A63B 2102/18: Baseball, rounders or similar games
- A63B 2209/02: with reinforcing fibres, e.g. carbon, polyamide fibres
- B32B 2038/0016: {Abrading}
- B32B 2038/0076: {Curing, vulcanising, cross-linking}
- B32B 2305/08: Reinforcements
- B32B 2311/00: Metals, their alloys or their compounds
- B32B 2311/18: Titanium
- Y10T 428/12444: Embodying fibers interengaged or between layers [e.g., paper, etc.]
- Y10T 428/12569: Synthetic resin
- Y10T 428/12625: Free carbon containing component
- Y10T 428/12806: Refractory [Group IVB, VB, or VIB] metal-base component
- Y10T 428/12875: Platinum group metal-base component
- Y10T 428/249945: Carbon or carbonaceous fiber
- Y10T 428/31522: Next to metal
- Y10T 428/31529: Next to metal
- B32B: LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- A63B: APPARATUS FOR PHYSICAL TRAINING, GYMNASTICS, SWIMMING, CLIMBING, OR FENCING; BALL GAMES; TRAINING EQUIPMENT (apparatus for passive exercising, massage A61H)
- Y10T: TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION

## Abstract

A method of preparing a beta titanium-composite laminate comprising providing a first layer of beta titanium alloy having a yield strength to modulus of elasticity ratio and adhering a first layer of composite having a strength to modulus of elasticity ratio to the layer of beta titanium alloy, thereby forming a beta titanium-composite laminate, where the yield strength to modulus of elasticity ratio of the first layer of beta titanium alloy matches the strength to modulus of elasticity ratio of the first layer of composite such that the first layer of beta titanium alloy will reach its stress limit and the first layer of composite will reach its stress limits at about the same total strain. Also, a beta titanium-composite laminate comprising a first layer of beta titanium alloy having a yield strength to modulus of elasticity ratio, and a first layer of composite having a strength to modulus of elasticity ratio adhered to the first layer of beta titanium alloy, where the yield strength to modulus of elasticity ratio of the first layer of beta titanium alloy matches the strength to modulus of elasticity ratio of the first layer of composite such that the first layer of beta titanium alloy will reach its stress limit and the first layer of composite will reach its stress limits at about the same total strain. Further, a structure such as an airplane part including a beta titanium-composite laminate according to the present invention.

## Claims

### Claim 1

A method of preparing a beta titanium-composite laminate comprising:
(a) providing a first layer of beta titanium alloy having a yield strength to modulus of elasticity ratio;
(b) providing a first layer of composite having a yield strength to modulus of elasticity ratio; and
(c) adhering the first layer of beta titanium alloy to the first layer of composite, thereby forming a beta titanium-composite laminate;
where the yield strength to modulus of elasticity ratio of the first layer of beta titanium alloy matches the strength to modulus of elasticity ratio of the first layer of composite such that the first layer of beta titanium alloy will reach its stress limit and the first layer of composite will reach its stress limits at about the same total strain.

### Claim 2 (depends on 1)

The method of claim 1, where the beta titanium alloy provided is selected from the group consisting of (Ti-15V-3Cr-3Sn-3Al) and (Ti-15Mo-3Al-3Nb).

### Claim 3 (depends on 1)

The method of claim 1, where the composite provided is a carbon fiber/epoxy composite.

### Claim 4 (depends on 1)

The method of claim 1, where the composite provided is an S2-glass/epoxy composite.

### Claim 5 (depends on 1)

The method of claim 1, where adhering comprises applying an adhesive to the beta titanium alloy.

### Claim 6 (depends on 1)

The method of claim 1, where adhering comprises bonding the composite by heating the composite.

### Claim 7 (depends on 1)

The method of claim 1, where the yield strength to modulus of elasticity ratio of the first layer of beta titanium alloy is between about 5% of the strength to modulus of elasticity ratio of the first layer of composite.

### Claim 8 (depends on 1)

The method of claim 1, additionally comprising cold reducing the beta titanium alloy before adhering.

### Claim 9 (depends on 1)

The method of claim 1, additionally comprising heating the beta titanium alloy at a temperature for a time to produce an aged beta titanium alloy before adhering.

### Claim 10 (depends on 9)

The method of claim 9, where the temperature is approximately 950° F. and the time is approximately 8 hours.

### Claim 11 (depends on 1)

The method of claim 1, additionally comprising cold reducing the beta titanium alloy and then aging the beta titanium alloy before adhering.

### Claim 12 (depends on 1)

The method of claim 1, additionally comprising coating the surface of the beta titanium alloy with a metal selected from the group consisting of platinum and the functional equivalent of platinum as a coating material, to produce a coated titanium alloy before adhering.

### Claim 13 (depends on 1)

The method of claim 1, additionally comprising abrading the surface of the beta titanium alloy before adhering.

### Claim 14 (depends on 1)

The method of claim 1, additionally comprising, after adhering, providing a second layer of beta titanium alloy having a yield strength to modulus of elasticity ratio and adhering the second layer of beta titanium alloy to the beta titanium-composite laminate, where the yield strength to modulus of elasticity ratio of the second layer of beta titanium alloy matches the strength to modulus of elasticity ratio of the first layer of composite such that the second layer of beta titanium alloy will reach its stress limit and the first layer of composite will reach its stress limits at about the same total strain.

### Claim 15 (depends on 1)

The method of claim 1, additionally comprising, after adhering, providing a second layer of composite having a strength to modulus of elasticity ratio and adhering the second layer of composite to the beta titanium-composite laminate, where the strength to modulus of elasticity ratio of the second layer of composite matches the yield strength to modulus of elasticity ratio of the first layer of beta titanium alloy such that the second layer of composite will reach its stress limit and the first layer of beta titanium alloy will reach its stress limits at about the same total strain.

### Claim 16 (depends on 1)

A method of making an airplane part, comprising:
(a) preparing a beta titanium-composite laminate according to the method of claim 1; and
(b) incorporating the beta titanium-composite laminate into an airplane part.

### Claim 17 (depends on 16)

The method of making an airplane part of claim 16, where the airplane part is selected from the group consisting of airplane skin, a spar, a plate and a tube.

### Claim 18 (depends on 16)

A method of making an airplane, comprising:
(a) preparing an airplane part according to the method of claim 16; and
(b) incorporating the part into an airplane.

### Claim 19 (depends on 1)

A method of making an airplane, comprising:
(a) providing a beta titanium-composite laminate according to the method of claim 1;
(b) utilizing the beta titanium-composite laminate to produce an airplane part; and
(c) incorporating the part into an airplane part.

### Claim 20 (depends on 19)

The method of making an airplane of claim 19, where the air plane part produced is selected from the group consisting of airplane skin, a spar, a plate and a tube.

### Claim 21 (depends on 1)

A beta titanium-composite laminate produced according to claim 1.

### Claim 22

A beta titanium-composite laminate comprising a first layer of beta titanium alloy having a yield strength to modulus of elasticity ratio, and a first layer of composite having a strength to modulus of elasticity ratio adhered to the first layer of beta titanium alloy;
where the yield strength to modulus of elasticity ratio of the first layer of beta titanium alloy matches the strength to modulus of elasticity ratio of the first layer of composite such that the first layer of beta titanium alloy will reach its stress limit and the first layer of composite will reach its stress limits at about the same total strain.

### Claim 23 (depends on 22)

The beta titanium-composite laminate of claim 22, where the yield strength to modulus of elasticity ratio of the first layer of beta titanium alloy is between about 5% of the strength to modulus of elasticity ratio of the first layer of composite.

### Claim 24 (depends on 22)

The beta titanium-composite laminate of claim 22, additionally comprising a layer of platinum between the first layer of beta titanium alloy and the first layer of composite.

### Claim 25 (depends on 22)

The beta titanium-composite laminate of claim 22, additionally comprising a second layer of beta titanium alloy having a yield strength to modulus of elasticity ratio adhered to the first layer of composite;
where the yield strength to modulus of elasticity ratio of the second layer of beta titanium alloy matches the strength to modulus of elasticity ratio of the first layer of composite such that the second layer of beta titanium alloy will reach its stress limit and the first layer of composite will reach its stress limits at about the same total strain.

### Claim 26 (depends on 25)

The beta titanium-composite laminate of claim 25, where the yield strength to modulus of elasticity ratio of the second layer of beta titanium alloy is between about 5% of the strength to modulus of elasticity ratio of the first layer of composite.

### Claim 27 (depends on 25)

The beta titanium-composite laminate of claim 25, additionally comprising a layer of platinum between the second layer of beta titanium alloy and the first layer of composite.

### Claim 28 (depends on 25)

The beta titanium-composite laminate of claim 25, additionally comprising a second layer of composite having a yield strength to modulus of elasticity ratio adhered to the first layer of beta titanium alloy;
where the yield strength to modulus of elasticity ratio of the second layer of composite matches the strength to modulus of elasticity ratio of the first layer of beta titanium alloy such that the second layer of composite will reach its stress limit and the first layer of beta titanium alloy will reach its stress limits at about the same total strain.

### Claim 29 (depends on 25)

The beta titanium-composite laminate of claim 25, additionally comprising a layer of platinum between the first layer of beta titanium alloy and the second layer of composite.

### Claim 30 (depends on 22)

An airplane part comprising the beta titanium-composite laminate of claim 22.

### Claim 31 (depends on 22)

An airplane comprising the beta titanium-composite laminate of claim 22.

### Claim 32 (depends on 25)

An airplane part comprising the beta titanium-composite laminate of claim 25.

### Claim 33 (depends on 25)

An airplane comprising the beta titanium-composite laminate of claim 25.