US5212944A
Expired / Lapsed
US
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Carbon and silicone polymer ablative liner material
Assignee: Northrop Grumman Corp
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Filing: 1990-10-23
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Granted: 1993-05-25
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Expires: 2010-10-23
Abstract
Abstract A polymeric ablative liner material based on carbon and silicone polymers and particulate fillers which is tailored to control the endothermic chemical reaction and thereby optimize the ablation process to provide maximum cooling and remaining char. The ablative liner material includes hydrocarbon polymers and has a molar ratio of carbon to silicon within the range of about 2 to 8. This composition optimizes the generation of gases for transpirational cooling, the cooling resulting from the endothermic chemical reaction, and the amount of stable char that remains after the ablation process is completed.
Inventors
- 👤 Jon W. Martin
- 👤 Richard A. Griese
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-26 02:41
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/97; F02K9/974; C; C08; C08K; C08K3/00; C08K3/34; C08K3/36; C08L; C08L23/00; C08L23/02; C08L23/04; C08L23/06; C08L23/16; C08L83/00; C08L83/04; C08L9/00; F02K9/08; F02K9/32; F02K9/34; F02K9/346; C08G; C08G77/00; C08G77/04; C08G77/60; C08L2205/00; C08L2205/03; Y; Y10; Y10S; Y10S239/00; Y10S239/19
Claims Analysis
Total Claims: 21
Claim 1
Independent Claim
95 words
A method for protecting a surface from heat, comprising the step of forming an ablative liner material on the surface, the ablative liner material including: a carbon polymer having a backbone of carbon atoms; and a silicone polymer; wherein the carbon and silicone polymers are selected to provide a molar ratio of carbon to silicon in the range of approximately 2 to 8, thus controlling the endothermic reaction during the ablation process to optimize the generation of gases for transpirational cooling and the amount of stable char that remains after the ablation process is complete.
Claim 2
Independent Claim
95 words
A method for protecting a surface from heat, comprising the step of forming an ablative liner material on the surface, the ablative liner material including: a carbon polymer having a backbone of carbon atoms; and a silicone polymer; wherein the carbon and silicone polymers are selected to provide a molar ratio of carbon to silicon in the range of approximately 2 to 8, thus controlling the endothermic reaction during the ablation process to optimize the generation of gases for transpirational cooling and the amount of stable char that remains after the ablation process is complete.
Claim 3
Dependent Claim
34 words
The method as set forth in claim 1, wherein the carbon polymer is a hydrocarbon polymer selected from the group consisting of ethylene-propylene-diene hydrocarbon rubber (EPDM), 1,2 polybutadiene resin, 1,4-polybutadiene resin, ethylene-propylene, and polyethylene.
Claim 4
Dependent Claim
15 words
The method as set forth in claim 1, wherein the silicone polymer is a siloxane.
Claim 5
Dependent Claim
16 words
The method as set forth in claim 1 wherein the silicone polymer is a silicone rubber.
Claim 6
Dependent Claim
19 words
The method as set forth in claim 1, wherein the liner material further includes one or more carbon fillers.
Claim 7
Dependent Claim
19 words
The method as set forth in claim 1, wherein the liner material further includes one or more silicon fillers.
Claim 8
Dependent Claim
81 words
An ablative liner material for protecting a surface from heat, comprising: a carbon polymer having a backbone of carbon atoms; and a silicone polymer; wherein the carbon and silicone polymers are selected to provide a molar ratio of carbon to silicon in the range of approximately 2 to 8, thus controlling the endothermic reaction during the ablation process to optimize the generation of gases for transpirational cooling and the amount of stable char that remains after the ablation process is complete.
Claim 9
Dependent Claim
81 words
An ablative liner material for protecting a surface from heat, comprising: a carbon polymer having a backbone of carbon atoms; and a silicone polymer; wherein the carbon and silicone polymers are selected to provide a molar ratio of carbon to silicon in the range of approximately 2 to 8, thus controlling the endothermic reaction during the ablation process to optimize the generation of gases for transpirational cooling and the amount of stable char that remains after the ablation process is complete.
Claim 10
Dependent Claim
36 words
The ablative liner material as set forth in claim 7, wherein the carbon polymer is a hydrocarbon polymer selected from the group consisting of ethylene-propylene-diene hydrocarbon rubber (EPDM), 1,2 polybutadiene resin, 1,4-polybutadiene resin, ethylene-propylene, and polyethylene.
Claim 11
Dependent Claim
17 words
The ablative liner material as set forth in claim 7, wherein the silicone polymer is a siloxane.
Claim 12
Dependent Claim
18 words
The ablative liner material as set forth in claim 7, wherein the silicone polymer is a silicone rubber.
Claim 13
Dependent Claim
18 words
The ablative liner material as set forth in claim 7, and further including one or more carbon fillers.
Claim 14
Dependent Claim
18 words
The ablative liner material as set forth in claim 7, and further including one or more silicon fillers.
Claim 15
Dependent Claim
89 words
A rocket engine having a combustion chamber and expansion nozzle lined with an ablative material, the ablative material comprising: a carbon polymer having a backbone of carbon atoms; and a silicone polymer; wherein the carbon and silicone polymers are selected to provide a molar ratio of carbon to silicon in the range of approximately 2 to 8, thus controlling the endothermic reaction during the ablation process to optimize the generation of gases for transpirational cooling and the amount of stable char that remains after the ablation process is complete.
Claim 16
Dependent Claim
89 words
A rocket engine having a combustion chamber and expansion nozzle lined with an ablative material, the ablative material comprising: a carbon polymer having a backbone of carbon atoms; and a silicone polymer; wherein the carbon and silicone polymers are selected to provide a molar ratio of carbon to silicon in the range of approximately 2 to 8, thus controlling the endothermic reaction during the ablation process to optimize the generation of gases for transpirational cooling and the amount of stable char that remains after the ablation process is complete.
Claim 17
Dependent Claim
35 words
The rocket engine as set forth in claim 13, wherein the carbon polymer is a hydrocarbon polymer selected from the group consisting of ethylene-propylene-diene hydrocarbon rubber (EPDM), 1,2 polybutadiene resin, 1,4-polybutadiene resin, ethylene-propylene, and polyethylene.
Claim 18
Dependent Claim
16 words
The rocket engine as set forth in claim 13, wherein the silicone polymer is a siloxane.
Claim 19
Dependent Claim
17 words
The rocket engine as set forth in claim 13, wherein the silicone polymer is a silicone rubber.
Claim 20
Dependent Claim
17 words
The rocket engine as set forth in claim 13, and further including one or more carbon fillers.
Claim 21
Dependent Claim
17 words
The rocket engine as set forth in claim 13, and further including one or more silicon fillers.
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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) | 1996-05-24 | 1996-11-23 | 1997-05-25 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2000-05-24 | 2000-11-23 | 2001-05-25 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2004-05-24 | 2004-11-23 | 2005-05-25 | $7700.00 | Window Closed / Lapsed |