US4877689A
Expired / Lapsed
US
⏱️ 0.0 years remaining
High temperature insulation barrier composite
Assignee: National Aeronautics and Space Administration
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Filing: 1988-09-30
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Granted: 1989-10-31
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Expires: 2008-09-30
Abstract
Abstract A composite material suitable for providing insulation for the nozzle structure of the Space Shuttle and other similar surfaces is disclosed which comprises an outer skin layer of nickel chromium and an interleaved inner region comprising a top layer of nickel chromium foil which acts as a primary convective shield, at least two layers of alumina batting adjacent to layers of silicon carbide fabric, and an additional layer of nickel chromium foil to be used as a secondary convective shield. The composite is particularly advantageous for use as nozzle insulation because of its ability to withstand high reentry temperatures, its flexibility, oxidation resistance, low conductivity, and light weight.
Inventors
- 👤 Joseph W. Onstott
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 19:26
CPC Classifications
B; B32; B32B; B32B5/00; B32B5/02; B32B15/00; B32B15/14; B32B15/02; B32B18/00; B64; B64G; B64G1/00; B64G1/22; B64G1/52; B64G1/58; B32B2262/00; B32B2262/10; B32B2262/105; B32B2305/00; B32B2305/38; B32B2307/00; B32B2307/30; B32B2307/304; B32B2311/00; B32B2311/22; B32B2605/00; B32B2605/18; Y; Y10; Y10T; Y10T428/00; Y10T428/12; Y10T428/12431; Y10T428/12438; Y10T428/12493; Y10T428/12535; Y10T428/12542; Y10T428/12549; Y10T428/12576; Y10T428/12611; Y10T428/12771; Y10T428/12806; Y10T428/12826; Y10T428/12847; Y10T428/12861; Y10T428/12944
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
123 words
A composite material suitable for use as a high temperature insulation barrier for outer surfaces of spacecraft and other hypervelocity vehicles comprising an outer skin layer of nickel chromium and of nickel chromium foil, a first layer of silicon carbide fabric under said top layer, a first layer of alumina batting under said first layer of silicon carbide, a second layer of silicon carbide fabric under said first layer of alumina, an additional layer of nickel chromium foil under said second layer of silicon carbide, a second layer of alumina batting under said additional layer of nickel chromium foil, and finally a third layer of silicon carbide fabric under said second layer of alumina an interleaved inner region comprised of a top layer
Claim 2
Dependent Claim
123 words
A composite material suitable for use as a high temperature insulation barrier for outer surfaces of spacecraft and other hypervelocity vehicles comprising an outer skin layer of nickel chromium and of nickel chromium foil, a first layer of silicon carbide fabric under said top layer, a first layer of alumina batting under said first layer of silicon carbide, a second layer of silicon carbide fabric under said first layer of alumina, an additional layer of nickel chromium foil under said second layer of silicon carbide, a second layer of alumina batting under said additional layer of nickel chromium foil, and finally a third layer of silicon carbide fabric under said second layer of alumina an interleaved inner region comprised of a top layer
Claim 3
Dependent Claim
17 words
A composite material according to claim 1 wherein the alumina batting is comprised of oriented fiber alumina.
Claim 4
Dependent Claim
23 words
A composite material according to claim 1 wherein the alumina batting layers have a thickness of from about 0.20 to about 0.30 inches.
Claim 5
Dependent Claim
23 words
A composite material according to claim 1 wherein the alumina batting layers have a thickness of from about 0.24 to about 0.26 inches.
Claim 6
Dependent Claim
32 words
A composite material according to claim 1 . wherein the layers of the interleaved inner region below the top nickel chromium foil layer have been sewn together with a heat resistant thread.
Claim 7
Dependent Claim
18 words
A composite material according to claim 5. wherein the heat resistant thread is comprised of an alumina-boria-silica composition.
Claim 8
Dependent Claim
27 words
A composite material according to claim 1 wherein the composite material is provided with means rendering it to the surface of a spacecraft or other hypervelocity vehicle.
Claim 9
Dependent Claim
23 words
A composite material according to claim 1 wherein the outer skin layer of nickel chromium is in the form of a mesh screen.
Claim 10
Dependent Claim
16 words
A composite material according to claim 1 wherein the layers of nickel chromium foil have perforations.
Claim 11
Dependent Claim
23 words
A composite material according to claim 9 wherein the perforations are approximately 0.010 inches in diameter and are disposed on 0.5 inch centers.
Claim 12
Dependent Claim
24 words
A composite material according to claim 1 wherein the silicon carbide fabric layers have a thickness of from about 010 to about 0.020 inches.
Claim 13
Dependent Claim
24 words
A composite material according to claim 1 wherein the silicon carbide fabric layers have a thickness of from about 0.014 to about 0.016 inches.
Claim 14
Dependent Claim
26 words
A composite material according to claim 1 wherein the outer skin layer of nickel chromium has a thickness of from about 0.015 to about 0.025 inches.
Claim 15
Dependent Claim
24 words
A composite material according to claim 1 wherein the nickel chromium foil layers have a thickness of from about 0.001 to about 0.003 inches.
References Cited (Backward Citations)
US4804571A
Cited
US4639399A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1992-10-30 | 1993-05-01 | 1993-10-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1996-10-30 | 1997-05-01 | 1997-10-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2000-10-30 | 2001-05-01 | 2001-10-31 | $7700.00 | Window Closed / Lapsed |