Glenn Alan Olson

US Patent:

44791631, Oct 23, 1984

Filed:

Sep 30, 1982

Appl. No.:

6/454206

Inventors:

Engbert T. Bannink - Auburn WA
Glenn O. Olson - Seattle WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H05F 102

US Classification:

361218

Abstract:

Method and structures for enhancing the conductivity of graphite composite materials for lightning protection and prevention of attachment of lightning to fasteners. The integral lightning protection system for composite aircraft skins, including skins with fasteners penetrating into fuel tanks, utilizes nickel-plated graphite fibers (24) which are woven into the outer layer of fabric of the structural component (10) requiring protection.

US Patent:

45020922, Feb 26, 1985

Filed:

Feb 24, 1983

Appl. No.:

6/469346

Inventors:

Engbert T. Bannink - Auburn WA
Glenn O. Olson - Seattle WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H05F 102

US Classification:

361218

Abstract:

Method and structures for enhancing the conductivity of graphite composite materials for lightning protection and prevention of attachment of lightning to fasteners. The integral lightning protection for composite aircraft skins, including skins with fasteners penetrating into fuel tanks, utilizes metal coated or plated graphite fibers which are woven into the outer layer of tape or fabric of the structural component requiring protection.

US Patent:

49125940, Mar 27, 1990

Filed:

Jul 22, 1988

Appl. No.:

7/224230

Inventors:

Engbert T. Bannink - Auburn WA
Glenn O. Olson - Seattle WA

Assignee:

The Boeing Company - Seattle WA

International Classification:

H05F 102

US Classification:

361218

Abstract:

An integral lightning protection system and method for its use with an aircraft graphite epoxy structure. If a repair is to be made to an aircraft composite structure, the hole to be repaired is first cleared of broken composite material and replaced with a bonded adhesive patch. Over the patch and conformal to the surface of the aircraft composite structure, a dielectric layer is placed, and over the dielectric layer, at least one metal-plated graphite fiber fabric ply is placed. Where fasteners are inserted through an aircraft composite panel, the heads of the fasteners are left flush with the outer surface of the composite material, and the composite material and fastener heads are adhesively covered by a dielectric cover. Thereafter, at least one metal-plated graphite fiber fabric ply is placed over the dielectric layer. Subsequently, either structure may be given a primer and paint coating.