US4458595A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Ablative liner
Assignee: United States Department of the Navy
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Filing: 1982-06-07
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Granted: 1984-07-10
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Expires: 2002-06-07
Abstract
Abstract An improved rocket motor has a first layer of silicone rubber and a second layer of an ablative lining placed between the rocket motor casing and the propellant grain. The ablative lining layer contains chopped novoloid fibers 14 microns in diameter and nominally 1 mm in length interspersed throughout a polymeric composition.
Inventors
- 👤 Howard W. Gerrish, Jr.
- 👤 Ronald F. Vetter
- 👤 George F. Sieg
- 👤 Harold L. Bennett
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-10-27 16:02
CPC Classifications
C; C08; C08G; C08G18/00; C08G18/06; C08G18/28; C08G18/65; C08G18/66; C08G18/6666; C08G18/667; C08G18/6681; F; F02; F02K; F02K9/00; F02K9/08; F02K9/32; F02K9/34; F02K9/346
Claims Analysis
Total Claims: 7
Claim 1
Independent Claim
97 words
An improved end burning rocket motor having reduced propellant grain coning and diminished carcinogenic by-products comprising: a tubular shaped casing having an inner surface, a silicone rubber layer on said surface; an ablative lining on said layer made from a mixture of about 74.5 percent by weight polypropylene glycol, about 1.0 percent by weight N-Mono(hydroxyethyl)-N,N',N'-tris(2-hydroxypropyl)ethylenediamine, about 10.38 percent by weight toluene-2,4-diisocyanate, about 0.62 percent by weight N-phenyl-N'-cyclohexyl-p-phenylenediamine, about 10.0 percent by weight TiO 2 , about 2.0 percent by weight novoloid fibers, and about 1.5 percent by weight ferric acetylacetonate; and propellant grain bonded to said lining.
Claim 2
Dependent Claim
97 words
An improved end burning rocket motor having reduced propellant grain coning and diminished carcinogenic by-products comprising: a tubular shaped casing having an inner surface, a silicone rubber layer on said surface; an ablative lining on said layer made from a mixture of about 74.5 percent by weight polypropylene glycol, about 1.0 percent by weight N-Mono(hydroxyethyl)-N,N',N'-tris(2-hydroxypropyl)ethylenediamine, about 10.38 percent by weight toluene-2,4-diisocyanate, about 0.62 percent by weight N-phenyl-N'-cyclohexyl-p-phenylenediamine, about 10.0 percent by weight TiO 2 , about 2.0 percent by weight novoloid fibers, and about 1.5 percent by weight ferric acetylacetonate; and propellant grain bonded to said lining.
Claim 3
Dependent Claim
22 words
An improved rocket motor according to claim 1 wherein said fibers are nominal length of 1 mm and diameter of 14 microns.
Claim 4
Independent Claim
97 words
A method of producing a rocket motor having reduced propellant grain coning and diminished carcinogenic by-products comprising: coating the inner surface of a rocket motor casing with a layer of silicone rubber; applying a mixture of about 74.5 percent by weight polypropylene glycol, about 1.0 percent by weight N-mono(hydroxyethyl)-N,N',N'-tris(2-hydroxypropyl)ethylenediamine, about 10.38 percent by weight toluene-2,4-diisocyanate, about 0.62 percent by weight N-phenyl-N'-cyclohexyl-p-phenylenediamine, about 10.0 percent by weight TiO 2 , and 2.0 percent by weight novoloid fibers; and about 1.5 percent by weight ferric acetylacetonate on said layer; and pouring a propellant grain in remainder of said casing.
Claim 5
Independent Claim
97 words
A method of producing a rocket motor having reduced propellant grain coning and diminished carcinogenic by-products comprising: coating the inner surface of a rocket motor casing with a layer of silicone rubber; applying a mixture of about 74.5 percent by weight polypropylene glycol, about 1.0 percent by weight N-mono(hydroxyethyl)-N,N',N'-tris(2-hydroxypropyl)ethylenediamine, about 10.38 percent by weight toluene-2,4-diisocyanate, about 0.62 percent by weight N-phenyl-N'-cyclohexyl-p-phenylenediamine, about 10.0 percent by weight TiO 2 , and 2.0 percent by weight novoloid fibers; and about 1.5 percent by weight ferric acetylacetonate on said layer; and pouring a propellant grain in remainder of said casing.
Claim 6
Dependent Claim
25 words
A method of producing a rocket motor according to claim 3 wherein said step of applying a mixture includes the sling lining of said mixture.
Claim 7
Dependent Claim
25 words
A method of producing a rocket motor according to claim 3 wherein said step of applying a mixture includes the spin lining of said mixture.
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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) | 1987-07-10 | 1988-01-09 | 1988-07-10 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1991-07-10 | 1992-01-09 | 1992-07-10 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1995-07-10 | 1996-01-09 | 1996-07-10 | $7700.00 | Window Closed / Lapsed |