US4500589A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Laminate of aluminum sheet material and aramid fibers
Assignee: Delft University of Technology
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Filing: 1983-09-20
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Granted: 1985-02-19
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Expires: 2003-09-20
Abstract
Abstract The invention relates to a laminate composed of two, three, four or more aluminum-containing metal sheets. The metal sheets, which may for instance be of an aluminum alloy, are bonded together by means of adhesive layers. In the adhesive layers, which are of a thermohardening material, there are embedded poly-paraphenylene terephthalamide threads. These threads are provided in the form of yarns made up of endless filaments and lie in a practically straight line in the adhesive which substantially consists of a thermohardening material. The adhesive layers contain the threads in an amount of 20 to 80% by weight.
Inventors
- 👤 Jacobus Schijve
- 👤 Laurens B. Vogelesang
- 👤 Roelof Marissen
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 05:33
CPC Classifications
B; B32; B32B; B32B15/00; B32B15/20; B29; B29C; B29C70/00; B29C70/04; B29C70/06; B29C70/08; B29C70/088; B32B15/04; B32B15/08; B32B15/14; B32B5/00; B32B5/02; B32B5/04; B32B7/00; B32B7/04; B32B7/12; B64; B64C; B64C1/00; B64C1/06; B64C1/12; B29K; B29K2277/00; B29K2277/10; B29K2705/00; B29K2705/02; B32B2262/00; B32B2262/02; B32B2262/0261; B32B2262/0269; B32B2307/00; B32B2307/50; B32B2307/51; B32B2307/54; B32B2311/00; B32B2311/24; B32B2605/00; B32B2605/18; B64C2001/0054; B64C2001/0081; Y; Y02; Y02T; Y02T50/00; Y02T50/40; Y10; Y10S; Y10S428/00; Y10S428/902; Y10S428/91; Y10T; Y10T428/00; Y10T428/24; Y10T428/24942; Y10T428/2495; Y10T428/24967; Y10T428/24975; Y10T428/31504; Y10T428/31511; Y10T428/31515; Y10T428/31522; Y10T428/31529; Y10T428/31551; Y10T428/31605; Y10T428/31678; Y10T428/31681; Y10T428/31725; Y10T442/00; Y10T442/30; Y10T442/3382; Y10T442/3415; Y10T442/3423
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
186 words
A fiber-reinforced laminate adapted for use as a structural component of an aircraft, comprising: at least two sheets of an aluminum alloy, each of said sheets having a thickness of less than 1 mm and a tensile strength of greater than 350 N/mm 2 ; an adhesive layer located between each adjacent pair of said sheets, said adhesive layer comprising a thermohardening material disposed between the sheets to bond an adjacent pair of the sheets together; aromatic polyamide fibers disposed in each said adhesive layer to reinforce the laminate, said fibers comprising polyparaphenylene terephthalamide yarns made up of endless filaments formed from a material having a modulus of elasticity in the range of 5×10 4 to 25×10 4 N/mm 2 and an elongation at breakage of at least 2%, said yarns being disposed in substantially straight parallel lines in the adhesive layer and being present in an amount of 20 to 80% by weight based on the combined weight of the thermohardening material and the yarns, the thickness of each of the sheets being greater than the thickness of each said adhesive layer containing said fibers.
Claim 2
Dependent Claim
186 words
A fiber-reinforced laminate adapted for use as a structural component of an aircraft, comprising: at least two sheets of an aluminum alloy, each of said sheets having a thickness of less than 1 mm and a tensile strength of greater than 350 N/mm 2 ; an adhesive layer located between each adjacent pair of said sheets, said adhesive layer comprising a thermohardening material disposed between the sheets to bond an adjacent pair of the sheets together; aromatic polyamide fibers disposed in each said adhesive layer to reinforce the laminate, said fibers comprising polyparaphenylene terephthalamide yarns made up of endless filaments formed from a material having a modulus of elasticity in the range of 5×10 4 to 25×10 4 N/mm 2 and an elongation at breakage of at least 2%, said yarns being disposed in substantially straight parallel lines in the adhesive layer and being present in an amount of 20 to 80% by weight based on the combined weight of the thermohardening material and the yarns, the thickness of each of the sheets being greater than the thickness of each said adhesive layer containing said fibers.
Claim 3
Dependent Claim
24 words
A laminate as claimed in claim 1, wherein the thickness of each of the sheets is in the range of 0.3 to 0.7 mm.
Claim 4
Dependent Claim
17 words
A laminate as claimed in claim 1, wherein the yarns are arranged in one or more groups.
Claim 5
Dependent Claim
18 words
A laminate as claimed in claim 1, wherein the yarns are in the form of a woven fabric.
Claim 6
Dependent Claim
36 words
A laminate as claimed in claim 4, wherein the woven fabric has 7 to 11 yarns per cm., each of said yarns having a linear density in the range of decitex 1200-2000 and containing 750-1250 filaments.
Claim 7
Dependent Claim
33 words
A laminate as claimed in claim 5, wherein the woven fabric has 9 yarns per cm., each of said yarns having a linear density of approximately decitex 1610 and containing approximately 1100 filaments.
Claim 8
Dependent Claim
15 words
A laminate as claimed in claim 1, wherein the laminate includes at least three sheets.
Claim 9
Dependent Claim
19 words
A laminate as claimed in claim 1, wherein each of the sheets comprises a sheet of an aluminum-copper alloy.
Claim 10
Dependent Claim
21 words
A laminate as claimed in claim 8, wherein the aluminum-copper alloy is of the type AA (USA) No. 2024-T 3 .
Claim 11
Dependent Claim
19 words
A laminate as claimed in claim 1, wherein each of the sheets comprises a sheet of an aluminum-zinc alloy.
Claim 12
Dependent Claim
21 words
A laminate as claimed in claim 10, wherein the aluminum-zinc alloy is of the type AA (USA) No. 7075-T 6 .
Claim 13
Dependent Claim
38 words
A laminate as claimed in claim 1, wherein the yarns are present in each said adhesive layer in an amount of 45 to 55% by weight based on the combined weight of the adhesive layer and the yarns.
Claim 14
Dependent Claim
27 words
A laminate as claimed in claim 1, wherein the filaments have a modulus of elasticity in the range of 10×10 4 to 15×10 4 N/mm 2 .
Claim 15
Dependent Claim
81 words
A laminate as claimed in claim 1, further characterized in that the crack propagation rate of the laminate in millimeters per cycle of varying load is at least two times less than the crack propagation rate seen when the laminate is not reinforced with fibers, and in that the number of varying load cycles before breakage is at least two times greater than the number of varying load cycles prior to breakage seen when the laminate is not reinforced with fibers.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1988-02-19 | 1988-08-20 | 1989-02-19 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-02-19 | 1992-08-20 | 1993-02-19 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-02-19 | 1996-08-20 | 1997-02-19 | $7700.00 | Window Closed / Lapsed |