U.S. patents available from 1976 to present.
U.S. patent applications available from 2005 to present.

Carbon-titanium composites

Patent 5733390 Issued on March 31, 1998. Estimated Expiration Date: Icon_subject December 7, 2015. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.

Patent References

3758234

3888661

Aluminum alloy-boron fiber composite
Patent #: 3936277
Issued on: 02/03/1976
Inventor: Jakway ,   et al.

Method of fabricating titanium alloy matrix composite materials
Patent #: 3991928
Issued on: 11/16/1976
Inventor: Friedrich ,   et al.

Hybrid composite laminate structures
Patent #: 4029838
Issued on: 06/14/1977
Inventor: Chamis, et al.

Selectively bonded composite tape
Patent #: 4115611
Issued on: 09/19/1978
Inventor: Stoltze ,   et al.

Assembly of metal-coated carbon fibers, process for production thereof, and method for use thereof
Patent #: 4132828
Issued on: 01/02/1979
Inventor: Nakamura ,   et al.

Titanium and titanium alloys ion plated with noble metals and their alloys
Patent #: 4137370
Issued on: 01/30/1979
Inventor: Fujishiro ,   et al.

Fibre-reinforced metal panels and production thereof
Patent #: 4141802
Issued on: 02/27/1979
Inventor: Duparque ,   et al.

Composite structure
Patent #: 4356678
Issued on: 11/02/1982
Inventor: Andrews ,   et al.

More ...

Inventor

Assignee

Application

No. 568530 filed on 12/07/1995

US Classes:

148/537, With coating step148/518, With electrocoating (e.g., electroplating, anodizing, sputtering, etc.)148/527, With metal next to or bonded to metal156/153, With abrading or grinding of lamina156/281, Combined; e.g., with cleaning, etc.156/330, Epoxy resin427/376.8, Metal base427/388.1Metal base

Examiners

Primary: Sheehan, John P.

Attorney, Agent or Firm

International Classes

C23C 016/00
C23C 028/02

Abstract

A method of combining a beta titanium alloy with advanced carbon composites, the combination having a matched yield strength and modules of elasticity ratio. When the combination is adhesively bonded both parts will approach maximum yield strength and fail at a similar amount of total strain. The titanium and carbon composites are combined by first abrading the titanium to be bonded, coating the titanium with platinum, aging the titanium, spraying primer on the coated titanium, applying adhesive to the primer side of the titanium and then applying the carbon to the adhesive. This allows the carbon composite to bond securely to the titanium. This composite uses the best properties of each component, the combination having a better set of properties than either part.

Other References

  • NASA CR-1859, "Analytical and Experimental Investigation of Aircraft Metal Structures Reinforced with Filamentary Composites--Phase I--Concept Development and Feasibility," S. Oken and R.R. June, 129 pages (1969-1970)
  • NASA CR-2039, "Analytical and Experimental Investigation of Aircraft Metal Structures Reinforced with Filamentary Composites--Phase II--Structural Fatigue, Thermal Cycling Creep, and Residual Strength," B. Blichfeldt and J.E. McCarty, 111 pages (1969-1970
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