Patent US2827915A successfully refreshed from Google Patents.
Patent US3755713A successfully refreshed from Google Patents.
US3755713A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Electrically conductive surface for aircraft
Assignee: Boeing Co
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Filing: 1972-07-25
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Granted: 1973-08-28
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Expires: 1992-07-25
Abstract
Abstract The invention is directed to the method of controlling electrostatic charge on aircraft and vulnerability to lightning strikes and relates to the use of a knitted wire mesh material applied over a glass fiber composite panel or plastic aerodynamic surface of an aircraft to form a permanent integral part of the surface and wherein the mesh is of the same material as the remainder of the aircraft in order to prevent corrosion. In the case of an aluminum aircraft, the mesh is also made of aluminum and therefore is electrochemically compatible and eliminates the problems generally associated with the use of electrochemically dissimilar materials.
Inventors
- 👤 J Paszkowski
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-24 13:54
CPC Classifications
B; B29; B29C; B29C70/00; B29C70/88; B29C70/882; B29C70/885; B64; B64D; B64D45/00; B64D45/02; H; H05; H05F; H05F3/00; H05F3/02; Y; Y10; Y10T; Y10T442/00; Y10T442/10; Y10T442/102; Y10T442/109; Y10T442/121
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
96 words
A panel contoured to form an external aerodynamic surface of an aircraft and for protecting the aircraft from becoming electrostatically charged and vulnerable relative to lightning strikes, said panel comprising: a layer of electrically nonconducting fiber reinforced plastic material; and a knitted mesh of electricAlly conductive wire material that is electrochemically compatible with the metal structure of the aircraft to which it is to be fastened; said knitted mesh being completely embedded in the adhesive resin of the fiber reinforced plastic material so as to be integral therewith and forming therewith an aerodynamically smooth exterior surface.
Claim 2
Dependent Claim
96 words
A panel contoured to form an external aerodynamic surface of an aircraft and for protecting the aircraft from becoming electrostatically charged and vulnerable relative to lightning strikes, said panel comprising: a layer of electrically nonconducting fiber reinforced plastic material; and a knitted mesh of electricAlly conductive wire material that is electrochemically compatible with the metal structure of the aircraft to which it is to be fastened; said knitted mesh being completely embedded in the adhesive resin of the fiber reinforced plastic material so as to be integral therewith and forming therewith an aerodynamically smooth exterior surface.
Claim 3
Dependent Claim
119 words
A lightning protective layer for an electrically non-conductive external aerodynamic surface of an aircraft comprising: a knitted mesh of electrically conductive wire from a material that is electrochemically compatible with the metal structure of the aircraft to which it is to be fastened; said knitted mesh being stretch formed over the outer aerodynamic surface of the electrically non-conductive material and adhesively bonded thereto; means for fastening the knitted wire mesh to the metal structure of the aircraft through an electrical connection to provide a path for draining off the electrostatic charge from the electrically non-conductive material; and said knitted wire mesh forming a lightning protective layer and surface barrier for limiting the depth of penetration of the lightning stroke.
Claim 4
Dependent Claim
119 words
A lightning protective layer for an electrically non-conductive external aerodynamic surface of an aircraft comprising: a knitted mesh of electrically conductive wire from a material that is electrochemically compatible with the metal structure of the aircraft to which it is to be fastened; said knitted mesh being stretch formed over the outer aerodynamic surface of the electrically non-conductive material and adhesively bonded thereto; means for fastening the knitted wire mesh to the metal structure of the aircraft through an electrical connection to provide a path for draining off the electrostatic charge from the electrically non-conductive material; and said knitted wire mesh forming a lightning protective layer and surface barrier for limiting the depth of penetration of the lightning stroke.
Claim 5
Independent Claim
137 words
The method of protecting an electrically non-conductive panel on the aerodynamic surface of an aircraft from damage due to a lightning strike comprising: applying an adhesive resin over the exterior aerodynamic surface of the electrically non-conductive panel; stretching a knitted mesh of electrically conductive wire material that is electrochemically compatible with the metal structure of the aircraft to which it is to be fastened over the panel so that the knitted wire mesh is completely embedded in the adhesive resin; curing the adhesive resin so as to integrally bond the knitted wire mesh to the panel with the exterior surface being aerodynamically smooth with respect to the airflow; and fastening the knitted wire mesh composite panel through an electrical connection to provide a path for draining off the electrical charge to the metal structure of the aircraft.
Claim 6
Independent Claim
137 words
The method of protecting an electrically non-conductive panel on the aerodynamic surface of an aircraft from damage due to a lightning strike comprising: applying an adhesive resin over the exterior aerodynamic surface of the electrically non-conductive panel; stretching a knitted mesh of electrically conductive wire material that is electrochemically compatible with the metal structure of the aircraft to which it is to be fastened over the panel so that the knitted wire mesh is completely embedded in the adhesive resin; curing the adhesive resin so as to integrally bond the knitted wire mesh to the panel with the exterior surface being aerodynamically smooth with respect to the airflow; and fastening the knitted wire mesh composite panel through an electrical connection to provide a path for draining off the electrical charge to the metal structure of the aircraft.
References Cited (Backward Citations)
US2982494A
Cited
US3498572A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1976-08-27 | 1977-02-26 | 1977-08-28 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-08-27 | 1981-02-26 | 1981-08-28 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-08-27 | 1985-02-26 | 1985-08-28 | $7700.00 | Window Closed / Lapsed |