US4599255A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Composite structures having conductive surfaces
Assignee: Boeing Co
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Filing: 1983-08-26
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Granted: 1986-07-08
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Expires: 2003-08-26
Abstract
Abstract A fiberglass fabric wherein a selected number and pattern of yarns have been coated with an aluminum coating is preimpregnated with epoxy or other resin system and laid up as an integral part of a composite structure of the type having a honeycomb core and a plurality of fiberglass plies. Multiple plies of fiberglass fabric which include the yarns coated with an aluminum coating may be utilized in edgeband fastener areas for increased electrical continuity without loss of mechanical strength of composite parts.
Inventors
- 👤 Jeanne M. Anglin
- 👤 Richard R. Edwards
- 👤 John E. Thomas
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-04 11:24
CPC Classifications
B; B29; B29C; B29C70/00; B29C70/88; B29C70/882; B29C70/885; B29D; B29D24/00; B29D24/002; B29D24/005; B29D24/007; B32; B32B; B32B3/00; B32B3/10; B32B3/12; B64; B64C; B64C1/00; B64C1/06; B29K; B29K2105/00; B29K2105/06; B29K2105/08; B29K2105/0809; B29K2705/00; B29K2705/02; B29K2709/00; B29K2709/08; B29K2995/00; B29K2995/0003; B29K2995/0005; B29L; B29L2031/00; B29L2031/30; B29L2031/3076; B64C2001/0054; B64C2001/0072; Y; Y02; Y02T; Y02T50/00; Y02T50/40; Y10; Y10T; Y10T428/00; Y10T428/23; Y10T428/234; Y10T428/236; Y10T428/24; Y10T428/24149; Y10T428/24273; Y10T428/24322
Claims Analysis
Total Claims: 6
Claim 1
Independent Claim
68 words
A conductive composite structural member for use in an aircraft structure comprising in combination: a fiberglass honeycomb core having inner and outer fiberglass plies; a fiberglass fabric including a plurality of electrically non-conductive fibers having electrically non-conductive surface portions interwoven with a plurality of electrically non-conductive fibers having electrically conductive surface portions; and, said fiberglass fabric disposed against a surface portion of said inner or outer fiberglass plies.
Claim 2
Dependent Claim
68 words
A conductive composite structural member for use in an aircraft structure comprising in combination: a fiberglass honeycomb core having inner and outer fiberglass plies; a fiberglass fabric including a plurality of electrically non-conductive fibers having electrically non-conductive surface portions interwoven with a plurality of electrically non-conductive fibers having electrically conductive surface portions; and, said fiberglass fabric disposed against a surface portion of said inner or outer fiberglass plies.
Claim 3
Dependent Claim
59 words
An integral composite structure for aircraft having P-static bleed protection comprising: a honeycomb core sandwich having inner and outer fiberglass plies; and, an outer surface of said inner or outer fiberglass plies including a P-static bleed protection layer of fiberglass fabric having a plurality of interwoven strands, said plurality of interwoven strands including interwoven strands having an aluminum coating.
Claim 4
Dependent Claim
59 words
An integral composite structure for aircraft having P-static bleed protection comprising: a honeycomb core sandwich having inner and outer fiberglass plies; and, an outer surface of said inner or outer fiberglass plies including a P-static bleed protection layer of fiberglass fabric having a plurality of interwoven strands, said plurality of interwoven strands including interwoven strands having an aluminum coating.
Claim 5
Dependent Claim
78 words
An integral composite structure for aircraft including: a plurality of fiberglass plies; said plurality of fiberglass plies having an edgeband fastener area surrounding an aperture passing therethrough; a plurality of layers of fiberglass fabric, each of said layers of fabric including interwoven strands of non-conductive polymeric material having aluminum coatings; and said plurality of fiberglass plies and said plurality of layers of fiberglass fabric forming an integrally disposed sandwich structure in said edgeband fastener area surrounding said aperture.
Claim 6
Dependent Claim
78 words
An integral composite structure for aircraft including: a plurality of fiberglass plies; said plurality of fiberglass plies having an edgeband fastener area surrounding an aperture passing therethrough; a plurality of layers of fiberglass fabric, each of said layers of fabric including interwoven strands of non-conductive polymeric material having aluminum coatings; and said plurality of fiberglass plies and said plurality of layers of fiberglass fabric forming an integrally disposed sandwich structure in said edgeband fastener area surrounding said aperture.
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1989-07-07 | 1990-01-06 | 1990-07-08 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1993-07-07 | 1994-01-06 | 1994-07-08 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1997-07-07 | 1998-01-06 | 1998-07-08 | $7700.00 | Window Closed / Lapsed |