Patent US2821713A successfully refreshed from Google Patents.
Patent US3048966A successfully refreshed from Google Patents.
US3048966A
Expired / Lapsed
US
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Rocket propulsion method
Assignee: Safran Aircraft Engines SAS
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Filing: 1959-04-23
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Granted: 1962-08-14
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Expires: 1979-04-23
Abstract
No abstract record available.
Inventors
- 👤 Feraud Roger Adrien
- 👤 Alder Robert Oscar
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-03 11:54
CPC Classifications
C; C06; C06B; C06B27/00; F; F02; F02K; F02K9/00; F02K9/42; F02K9/425
Claims Analysis
Total Claims: 2
Claim 1
Independent Claim
137 words
A METHOD OF CARRYING OUT COMBUSTION IN A ROCKET PROPULSION CHAMBER OF GENERALLY CIRCULAR CROSS SECTION, COMPRISING THE CONCURRENT STEPS OF: SUPPLYING AT LEAST ONE OXIDIZER TO SAID CHAMBER, INJECTING INTO A CENTRAL PORTION OF SAID CHAMBER A METAL IN LIQUID STATE SELECTED FROM THE GROUP CONSISTING OF BERYLLIUM, LITHIUM, BORON, ALUMINUM AND MAGNESIUM, TO PERFORM A COMBUSTION OF SAID METAL WITH SAID OXIDIZER OF SUCH NATURE AS MIGHT SUBJECT THE ROCKET CHAMBER WALL TO EXCESSIVE THERMAL STRESS, AND INJECTING INTO A PERIPHERAL PORTION OF SAID CHAMBER, AROUND SAID CENTRAL PORTION THEREOF, A FUEL OF SUBSTANTIALLY LOWER CALORIFIC VALUE THAN THAT OF THE METAL OF LEAST CALORIFIC VALUE BELONGING TO SAID GROUP, TO PERFORM A COMBUSTION OF SAID FUEL WITH SAID OXIDIZER OF SUCH NATURE AS WILL PROTECT SAID ROCKET CHAMBER WALL FROM SAID EXCESSIVE THERMAL STRESS.
Claim 2
Independent Claim
137 words
A METHOD OF CARRYING OUT COMBUSTION IN A ROCKET PROPULSION CHAMBER OF GENERALLY CIRCULAR CROSS SECTION, COMPRISING THE CONCURRENT STEPS OF: SUPPLYING AT LEAST ONE OXIDIZER TO SAID CHAMBER, INJECTING INTO A CENTRAL PORTION OF SAID CHAMBER A METAL IN LIQUID STATE SELECTED FROM THE GROUP CONSISTING OF BERYLLIUM, LITHIUM, BORON, ALUMINUM AND MAGNESIUM, TO PERFORM A COMBUSTION OF SAID METAL WITH SAID OXIDIZER OF SUCH NATURE AS MIGHT SUBJECT THE ROCKET CHAMBER WALL TO EXCESSIVE THERMAL STRESS, AND INJECTING INTO A PERIPHERAL PORTION OF SAID CHAMBER, AROUND SAID CENTRAL PORTION THEREOF, A FUEL OF SUBSTANTIALLY LOWER CALORIFIC VALUE THAN THAT OF THE METAL OF LEAST CALORIFIC VALUE BELONGING TO SAID GROUP, TO PERFORM A COMBUSTION OF SAID FUEL WITH SAID OXIDIZER OF SUCH NATURE AS WILL PROTECT SAID ROCKET CHAMBER WALL FROM SAID EXCESSIVE THERMAL STRESS.
References Cited (Backward Citations)
US1506322A
Cited
US2771739A
Cited
US2406926A
Cited
US2393201A
Cited
US2729936A
Cited
US2769304A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1965-08-13 | 1966-02-12 | 1966-08-14 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1969-08-13 | 1970-02-12 | 1970-08-14 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1973-08-13 | 1974-02-12 | 1974-08-14 | $7700.00 | Window Closed / Lapsed |