Patent US5215824A successfully refreshed from Google Patents.
US5215824A
Expired / Lapsed
US
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RF-transparent spacecraft thermal control barrier
Assignee: Lockheed Martin Corp
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Filing: 1990-12-05
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Granted: 1993-06-01
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Expires: 2010-12-05
Abstract
Abstract An RF-transparent blanket provides thermal protection against solar and laser radiation. The blanket includes an outer layer of a transparent Kapton dielectric sheet with an outer surface coated with electrically conductive transparent indium-tin oxide to aid in suppressing electrostatic discharge. A second layer includes a transparent Kapton dielectric sheet with a coating of white silicone paint on the surface facing the first sheet. The outermost Kapton sheet protects the paint from long-term damage due to charged particle fluence and ultraviolet radiation. Further sheets of uncoated transparent Kapton, which may be embossed, are interposed between the second layer and a surface upon which an antenna is mounted to provide thermal insulation.
Inventors
- 👤 John G. Munro, III
- 👤 Paul V. Barcomb
- 👤 Roman Herschitz
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-07 15:52
CPC Classifications
B; B32; B32B; B32B27/00; B32B27/06; B32B27/08; B32B27/28; B32B27/281; B32B27/38; B32B3/00; B32B3/26; B32B3/28; H; H01; H01Q; H01Q1/00; H01Q1/002; H01Q1/27; H01Q1/28; H01Q1/288; B32B2307/00; B32B2307/40; B32B2307/412; B32B2379/00; B32B2379/08; B32B2605/00; B32B2605/18; Y; Y10; Y10T; Y10T428/00; Y10T428/24; Y10T428/24479; Y10T428/24612; Y10T428/24628; Y10T428/24661; Y10T428/24802; Y10T428/24893; Y10T428/24901; Y10T428/24942; Y10T428/2495; Y10T428/31504; Y10T428/31652; Y10T428/31663; Y10T428/31678; Y10T428/31681; Y10T428/31721
Claims Analysis
Total Claims: 14
Claim 1
Independent Claim
102 words
An RF-transparent thermal control barrier for protection of at least a portion of the outer surface of a spacecraft, comprising: a first layer of transparent polyimide film defining inner and outer surfaces; a second layer of transparent polyimide film defining inner and outer surfaces, said second layer of polyimide film being located closer to said outer surface of said spacecraft than said first layer of polyimide film; a transparent, electrically conductive coating affixed to said outer surface of said first layer of polyimide film; and a layer of white paint affixed to said outer surface of said second layer of polyimide film.
Claim 2
Dependent Claim
102 words
An RF-transparent thermal control barrier for protection of at least a portion of the outer surface of a spacecraft, comprising: a first layer of transparent polyimide film defining inner and outer surfaces; a second layer of transparent polyimide film defining inner and outer surfaces, said second layer of polyimide film being located closer to said outer surface of said spacecraft than said first layer of polyimide film; a transparent, electrically conductive coating affixed to said outer surface of said first layer of polyimide film; and a layer of white paint affixed to said outer surface of said second layer of polyimide film.
Claim 3
Dependent Claim
15 words
A barrier according to claim 1, wherein said transparent, electrically conductive coating comprises indium-tin oxide.
Claim 4
Dependent Claim
17 words
A barrier according to claim 2, wherein the thickness of said coating is less than 100 Å.
Claim 5
Dependent Claim
18 words
A barrier according to claim 1, wherein said layer of white paint comprises a layer of silicone paint.
Claim 6
Dependent Claim
28 words
A barrier according to claim 4, further comprising an adhesive-primer interposed between said layer of silicone paint and said outer surface of said second layer of polyimide film.
Claim 7
Dependent Claim
20 words
A barrier according to claim 1, wherein said first layer of polyimide film has a thickness of about 0.002 inch.
Claim 8
Dependent Claim
36 words
A barrier according to claim 1 further comprising at least one further layer of transparent polyimide film, said further layer being located between said second layer of polyimide film and said outer surface of said spacecraft.
Claim 9
Dependent Claim
20 words
A barrier according to claim 7 wherein said further layer of polyimide film has a thickness of about 0.002 inch.
Claim 10
Dependent Claim
22 words
A barrier according to claim 7 wherein said further layer of polyimide film defines a pattern of raised regions over its surface.
Claim 11
Dependent Claim
32 words
A barrier according to claim 7 further comprising a fourth layer of transparent polyimide film adjacent said further layer, said fourth layer also defining a pattern of raised regions over its surface.
Claim 12
Dependent Claim
166 words
An RF-transparent thermal control blanket for protection f portions of the outer surface of a spacecraft, comprising: an outer layer of transparent polyimide film having a thickness of about 0.002 inch, and defining inner and outer surfaces; a second layer of transparent polyimide film having a thickness of about 0.002 inch, and defining inner and outer surfaces, said second layer of polyimide film being located closer to said outer surface of said spacecraft than said inner surface of said outer layer of polyimide film; a transparent, electrically conductive coating having a thickness of less than 100 Å affixed to said outer surface of said outer layer of polyimide film; a layer of adhesive affixed to said outer surface of said second layer of polyimide film; a layer of white silicone paint affixed to said layer of adhesive; and at least one further layer of polyimide film sheet interposed between said inner surface of said second layer of polyimide film and said outer surface of said spacecraft.
Claim 13
Dependent Claim
166 words
An RF-transparent thermal control blanket for protection f portions of the outer surface of a spacecraft, comprising: an outer layer of transparent polyimide film having a thickness of about 0.002 inch, and defining inner and outer surfaces; a second layer of transparent polyimide film having a thickness of about 0.002 inch, and defining inner and outer surfaces, said second layer of polyimide film being located closer to said outer surface of said spacecraft than said inner surface of said outer layer of polyimide film; a transparent, electrically conductive coating having a thickness of less than 100 Å affixed to said outer surface of said outer layer of polyimide film; a layer of adhesive affixed to said outer surface of said second layer of polyimide film; a layer of white silicone paint affixed to said layer of adhesive; and at least one further layer of polyimide film sheet interposed between said inner surface of said second layer of polyimide film and said outer surface of said spacecraft.
Claim 14
Dependent Claim
16 words
A blanket according to claim 11 wherein said further layer of polyimide film sheet is embossed.
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) | 1996-05-31 | 1996-11-30 | 1997-06-01 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2000-05-31 | 2000-11-30 | 2001-06-01 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2004-05-31 | 2004-11-30 | 2005-06-01 | $7700.00 | Window Closed / Lapsed |