US4349859A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Shielded structural or containment member
Assignee: McDonnell Douglas Corp
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Filing: 1980-09-24
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Granted: 1982-09-14
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Expires: 2000-09-24
Abstract
Abstract A member suitable for use at the exterior surface of an aircraft for structural or containment purposes includes a nonmetallic base or core and a thin electrical shield over that surface of the base that is presented outwardly. Preferably the base is a composite consisting of graphite fibers and a cured resin in which the fibers are embedded. The shield is tin or a tin alloy that is bonded to the surface of the base, preferably by metal spraying techniques. An electrical discharge, such as lightning, that attaches to the member is dissipated through the shield without impairing the strength or containment capabilities of the base.
Inventors
- 👤 Laurence R. Sanders
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 14:31
CPC Classifications
B; B64; B64C; B64C1/00; B64C1/06; B64D; B64D45/00; B64D45/02; B64C2001/0054; B64C2001/0072; B64C2001/0081; Y; Y02; Y02T; Y02T50/00; Y02T50/40
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
128 words
In an aircraft, a structural or containment member that is exposed to the atmosphere at the exterior of the aircraft, said member comprising a base adapted to carry substantially all of any forces exerted on the member and being formed from a composite material that is a relatively poor conductor of electricity, the composite material including nonmetallic fibers and a resin matrix in which the fibers are embedded; and a thin metal shield adhered to and extended over that surface of the base that is presented outwardly with respect to the aircraft, the thin metal shield being exposed to the atmosphere at the exterior of the aircraft for dissipating an electrical charge that attaches to the member, the metal of the shield being tin or a tin alloy.
Claim 2
Dependent Claim
128 words
In an aircraft, a structural or containment member that is exposed to the atmosphere at the exterior of the aircraft, said member comprising a base adapted to carry substantially all of any forces exerted on the member and being formed from a composite material that is a relatively poor conductor of electricity, the composite material including nonmetallic fibers and a resin matrix in which the fibers are embedded; and a thin metal shield adhered to and extended over that surface of the base that is presented outwardly with respect to the aircraft, the thin metal shield being exposed to the atmosphere at the exterior of the aircraft for dissipating an electrical charge that attaches to the member, the metal of the shield being tin or a tin alloy.
Claim 3
Dependent Claim
11 words
The structure according to claim 1 wherein the fibers are graphite.
Claim 4
Dependent Claim
13 words
The structure according to claim 1 wherein matrix is a cured epoxy resin.
Claim 5
Dependent Claim
17 words
The structure according to claim 1 wherein the shield is between approximately 0.002 and 0.006 inches thick.
Claim 6
Dependent Claim
18 words
The structure according to claim 1 wherein the fibers are graphite and the matrix is cured epoxy resin.
Claim 7
Dependent Claim
91 words
A process for producing a structural or containment member for an aircraft, with the member being capable of withstanding electrical discharges without impairing its strength or its containment capabilities; said process comprising: laying nonmetallic fibers into a desired arrangement; embedding the fibers in a hard and rigid resin matrix to form a base that is capable of carrying substantially all of any force exerted on the member; and applying a thin coating of tin or tin alloy to that surface of the base that is normally presented outwardly on the aircraft.
Claim 8
Dependent Claim
91 words
A process for producing a structural or containment member for an aircraft, with the member being capable of withstanding electrical discharges without impairing its strength or its containment capabilities; said process comprising: laying nonmetallic fibers into a desired arrangement; embedding the fibers in a hard and rigid resin matrix to form a base that is capable of carrying substantially all of any force exerted on the member; and applying a thin coating of tin or tin alloy to that surface of the base that is normally presented outwardly on the aircraft.
Claim 9
Dependent Claim
35 words
The process according to claim 6 wherein the step of applying a thin coating of tin to the surface of the base comprises spraying the tin or tin alloy onto the surface of the base.
Claim 10
Dependent Claim
29 words
The process according to claim 7 wherein the surface of the base is clean and has a roughened texture before the tin or tin alloy is sprayed onto it.
Claim 11
Dependent Claim
18 words
The process according to claim 6 wherein the fibers are graphite and the matrix is a cured resin.
Claim 12
Dependent Claim
21 words
The process according to claim 7 wherein the tin is in a molten condition when it is sprayed onto the base.
Claim 13
Dependent Claim
27 words
A process according to claim 6 wherein the resin of the matrix for the base is cured before any of the tin coating is applied to it.
Claim 14
Dependent Claim
35 words
A process according to claim 11 wherein the step of applying a thin coating of tin to the surface of the base comprises spraying a tin or tin alloy onto the surface of the base.
References Cited (Backward Citations)
US3498572A
Cited
US3989984A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1985-09-13 | 1986-03-15 | 1986-09-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1989-09-13 | 1990-03-15 | 1990-09-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1993-09-13 | 1994-03-15 | 1994-09-14 | $7700.00 | Window Closed / Lapsed |