Patent US3677010A successfully refreshed from Google Patents.
US3677010A
Expired / Lapsed
US
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Rocket motor and method
Assignee: United States Department of the Army
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Filing: 1964-03-11
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Granted: 1972-07-18
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Expires: 1984-03-11
Abstract
Abstract 7. The method of operating a solid-fueled rocket motor to vary the total impulse achieved, said motor comprising, in combination, a substantially cylindrical outside wall which forms a chamber, said wall being tapered at the rearward end of said chamber to form a converging-diverging nozzle, said wall also closing the forward end of said chamber except for an opening to receive a tube whereby fluid can be introduced into said chamber; a solid rocket propellant grain rigidly disposed in said chamber, said grain comprising a plurality of concentric layers of propellant, the propellant layer nearest the center of the grain having disposed therein a perforation passing from end to end therethrough along the center axis of said grain, said layers consisting essentially of a cured intimate mixture of polymeric binder, fuel particles, and an oxidizer therefor, said layers being completely separated from each other by a liner, said liner consisting essentially of a cured polymeric material incapable of supporting its own combustion, said method comprising: A. IGNITING AND BURNING THE INNERMOST LAYER OF PROPELLANT, THEREBY EXPOSING THE ADJACENT LINER; B. INTRODUCING INTO THE FORWARD END OF SAID CHAMBER THROUGH SAID OPENING AN OXIDIZER FLUID WHICH IS HYPERGOLIC WITH SAID LINER WHEREBY THE LINER IGNITES, BURNS, AND IN TURN IGNITES THE ADJACENT LAYER OF PROPELLANT; AND C. REPEATING STEPS (A) AND (B) UNTIL AS MANY PROPELLANT LAYERS AS DESIRED HAVE BEEN CONSUMED.
Inventors
- 👤 Robert H Fink
- 👤 Eugene J Palm
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-01 19:38
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/08; F02K9/10; F02K9/14; F02K9/32; F02K9/34; F02K9/72; F02K9/94; F02K9/95
Claims Analysis
Total Claims: 13
Claim 1
Independent Claim
106 words
A solid-fueled rocket propellant grain, said grain comprising in combination: a. a plurality of concentric layers of propellant, the propellant layer nearest the center of the grain having disposed therein a perforation passing from end to end therethrough along the center axis of said grain, said propellant layers consisting essentially of a cured, intimate mixture of a polymeric binder, fuel particles, and an oxidizer therefor; and b. a liner disposed between each of said layers in rigid relationship therewith to completely separate the adjacent surfaces of said layers from each other, said liner consisting essentially of a cured polymeric material incapable of supporting its own combustion.
Claim 2
Dependent Claim
106 words
A solid-fueled rocket propellant grain, said grain comprising in combination: a. a plurality of concentric layers of propellant, the propellant layer nearest the center of the grain having disposed therein a perforation passing from end to end therethrough along the center axis of said grain, said propellant layers consisting essentially of a cured, intimate mixture of a polymeric binder, fuel particles, and an oxidizer therefor; and b. a liner disposed between each of said layers in rigid relationship therewith to completely separate the adjacent surfaces of said layers from each other, said liner consisting essentially of a cured polymeric material incapable of supporting its own combustion.
Claim 3
Dependent Claim
20 words
The solid rocket propellant grain according to claim 1 wherein said liner is up to about 0.75 inch in thickness.
Claim 4
Dependent Claim
34 words
A solid rocket propellant grain according to claim 2 wherein said liner is a member selected from the group consisting of the polydienes, the polysulfides, the polyepoxides, polyurethanes, polylactams, polystyrenes, polyethylenes, polypropylenes, and polybutylenes.
Claim 5
Dependent Claim
160 words
A solid-fueled rocket motor, said motor comprising in combination: a. a substantially cylindrical outside wall which forms a chamber, said wall being tapered at the rearward end of said chamber to form a converging-diverging nozzle, said wall also closing the forward end of chamber except for an opening in communication with said chamber to receive a tube whereby fluid can be introduced into said chamber; and b. a solid rocket propellant grain rigidly disposed in said chamber, said grain comprising a plurality of concentric layers of propellant, the propellant layer nearest the center of the grain having disposed therein a perforation passing from end to end therethrough along the center axis of said grain, said propellant layers consisting essentially of a cured intimate mixture of a polymeric binder, fuel particles, and an oxidizer therefor, said layers being completely separated from each other by a liner, said liner consisting essentially of a cured polymeric material incapable of supporting its own combustion.
Claim 6
Dependent Claim
160 words
A solid-fueled rocket motor, said motor comprising in combination: a. a substantially cylindrical outside wall which forms a chamber, said wall being tapered at the rearward end of said chamber to form a converging-diverging nozzle, said wall also closing the forward end of chamber except for an opening in communication with said chamber to receive a tube whereby fluid can be introduced into said chamber; and b. a solid rocket propellant grain rigidly disposed in said chamber, said grain comprising a plurality of concentric layers of propellant, the propellant layer nearest the center of the grain having disposed therein a perforation passing from end to end therethrough along the center axis of said grain, said propellant layers consisting essentially of a cured intimate mixture of a polymeric binder, fuel particles, and an oxidizer therefor, said layers being completely separated from each other by a liner, said liner consisting essentially of a cured polymeric material incapable of supporting its own combustion.
Claim 7
Dependent Claim
19 words
The solid-fueled rocket motor according to claim 4 wherein said liner is up to about 0.75 inch in thickness.
Claim 8
Dependent Claim
33 words
The solid-fueled rocket motor according to claim 5 wherein said liner is a member selected from the group consisting of the polydienes, the polysulfides, the polyepoxides, polyurethanes, polylactams, polystyrenes, polyethylenes, polypropylenes, and polybutylenes.
Claim 9
Independent Claim
228 words
THE METHOD OF OPERATING A SOLID-FUELED ROCKET MOTOR TO VARY THE TOTAL IMPULSE ACHIEVED, SAID MOTOR COMPRISING, IN COMBINATION, A SUBSTANTIALLY CYLINDRICAL OUTSIDE WALL WHICH FORMS A CHAMBER, SAID WALL BEING TAPERED AT THE REARWARD END OF SAID CHAMBER TO FORM A CONVERGING-DIVERGING NOZZLE, SAID WALL ALSO CLOSING THE FORWARD END OF SAID CHAMBER EXCEPT FOR AN OPENING TO RECEIVE A TUBE WHEREBY FLUID CAN BE INTRODUCED INTO SAID CHAMBER; A SOLID ROCKET PROPELLANT GRAIN RIGIDLY DISPOSED IN SAID CHAMBER, SAID GRAIN COMPRISING A PLURALITY OF CONCENTRIC LAYERS OF PROPELLANT LAYER NEAREST THE CENTER OF THE GRAIN HAVING DISPOSED THEREIN A PERFOROATION PASSING FROM END TO END THERETHROUGH ALONG THE CENTER AXIS OF SAID GRAIN, SAID LAYERS CONSISTING ESSENTIALLY OF A CURED INTIMATE MIXTURE OF POLYMERIC BINDER, FUEL PARTICLES, AND AN OXIDIZER THEREOF, SAID LAYERS BEING COMPLETELY SEPARATED FROM EACH OTHER BY A LINER, SAID LINER CONSISTING ESSENTIALLY OF A CURED POLYMERIC MATERIAL INCAPABLE OF SUPPORTING ITS OWN COMBUSTION, SAID METHOD COMPRISING: A. IGNITING AND BURING THE INNERMOST LAYER OF PROPELLANT, THEEBY EXPOSING THE ADJACENT LINER; B. INTRODUCING INTO THE FORWARD END OF SAID CHAMBER THROUGH SAID OPENING AN OXIDIZER FLUID WHICH IS HYPERGOLIC WITH SAID LINER WHEREBY THE LINER IGNITES, BURNS, AND IN TURN IGNITES THE ADJACENT LAYER OF PROPELLANT; AND C. REPEATING STEPS (A) AND (B) UNTIL AS MANY PROPELLANT LAYERS AS DESIRED HAVE BEEN CONSUMED.
Claim 10
Independent Claim
228 words
THE METHOD OF OPERATING A SOLID-FUELED ROCKET MOTOR TO VARY THE TOTAL IMPULSE ACHIEVED, SAID MOTOR COMPRISING, IN COMBINATION, A SUBSTANTIALLY CYLINDRICAL OUTSIDE WALL WHICH FORMS A CHAMBER, SAID WALL BEING TAPERED AT THE REARWARD END OF SAID CHAMBER TO FORM A CONVERGING-DIVERGING NOZZLE, SAID WALL ALSO CLOSING THE FORWARD END OF SAID CHAMBER EXCEPT FOR AN OPENING TO RECEIVE A TUBE WHEREBY FLUID CAN BE INTRODUCED INTO SAID CHAMBER; A SOLID ROCKET PROPELLANT GRAIN RIGIDLY DISPOSED IN SAID CHAMBER, SAID GRAIN COMPRISING A PLURALITY OF CONCENTRIC LAYERS OF PROPELLANT LAYER NEAREST THE CENTER OF THE GRAIN HAVING DISPOSED THEREIN A PERFOROATION PASSING FROM END TO END THERETHROUGH ALONG THE CENTER AXIS OF SAID GRAIN, SAID LAYERS CONSISTING ESSENTIALLY OF A CURED INTIMATE MIXTURE OF POLYMERIC BINDER, FUEL PARTICLES, AND AN OXIDIZER THEREOF, SAID LAYERS BEING COMPLETELY SEPARATED FROM EACH OTHER BY A LINER, SAID LINER CONSISTING ESSENTIALLY OF A CURED POLYMERIC MATERIAL INCAPABLE OF SUPPORTING ITS OWN COMBUSTION, SAID METHOD COMPRISING: A. IGNITING AND BURING THE INNERMOST LAYER OF PROPELLANT, THEEBY EXPOSING THE ADJACENT LINER; B. INTRODUCING INTO THE FORWARD END OF SAID CHAMBER THROUGH SAID OPENING AN OXIDIZER FLUID WHICH IS HYPERGOLIC WITH SAID LINER WHEREBY THE LINER IGNITES, BURNS, AND IN TURN IGNITES THE ADJACENT LAYER OF PROPELLANT; AND C. REPEATING STEPS (A) AND (B) UNTIL AS MANY PROPELLANT LAYERS AS DESIRED HAVE BEEN CONSUMED.
Claim 11
Dependent Claim
17 words
The method according to claim 7 wherein said liner is up to about 0.75 inch in thickness.
Claim 12
Dependent Claim
31 words
The method according to claim 8 wherein said liner is a member selected from the group consisting of the polydienes, the polysulfides, the polyepoxides, polyurethanes, polylactams, polystyrenes, polyethylenes, polypropylenes, and polybutylenes.
Claim 13
Dependent Claim
38 words
The method according to claim 9 wherein said fluid oxidizer is a member selected from the group consisting of red fuming nitric acid, fluorine, chlorine trifluoride, perhalogenyl fluoride-halogen fluoride mixtures, perhalogenyl fluoride-fluorine mixtures, and perhalogenyl fluoride-chloryl fluoride mixtures.
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) | 1975-07-18 | 1976-01-17 | 1976-07-18 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-07-18 | 1980-01-17 | 1980-07-18 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-07-18 | 1984-01-17 | 1984-07-18 | $7700.00 | Window Closed / Lapsed |