Patent US3684215A successfully refreshed from Google Patents.
US3684215A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Missile
Assignee: Saab Bofors AB
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Filing: 1970-05-28
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Granted: 1972-08-15
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Expires: 1990-05-28
Abstract
Abstract The invention concerns a missile, in particular a guided missile, having stabilizing wings and a solid fuel propulsion motor. The fuel of the propulsion motor is divided into two separate fuel charges located axially spaced in the missile. The portion of the interior of the missile between the two fuel charges consists of an empty space, into which the fuel charges deliver their combustion gases and which is surrounded by an annular member forming the external shell of the missile between the two fuel charges and comprising the jet nozzles for the propulsion motor. The two fuel charges have such relative sizes and locations in the missile that their common gravity center coincides substantially with the total gravity center of the missile. The stabilizing wings are attached to the annular member comprising the jet nozzles and are located circumferentially between said jet nozzles.
Inventors
- 👤 Gunnar Jacobson
- 👤 Olof Bertil Olsson
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 00:51
CPC Classifications
F; F42; F42B; F42B10/00; F42B10/02; F42B10/14; F02; F02K; F02K9/00; F02K9/70; F42B15/00
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
203 words
A missile comprising: an elongate, substantially cylindrical external shell; A solid fuel propulsion motor including two separate fuel charges disposed axially spaced apart within said shell to define a space therein, said fuel charges delivering their combustion gases directly to said space between the fuel charges; said fuel charges having relative sizes and locations within said shell such that the common center of gravity thereof substantially coincides with the total center of gravity of the missile and relative rates of burning such that their common center of gravity remains substantially stationary relative the missile during the burning of the charges and said space between the fuel charges being located to coincide substantially with the location of said center of gravity; an annular member encircling said space and forming an annular portion of said shell between said two fuel charges; a plurality of open ended exhaust nozzles for the combustion gases generated by said fuel charges mounted equally circumferentially spaced on said annular member so their inlet ends communicate with said empty space and their outlet ends are located outside of the shell; a plurality of stabilizing wings; and mounting means on said annular member equally circumferentially spaced thereon and intermediate said exhaust nozzles.
Claim 2
Dependent Claim
203 words
A missile comprising: an elongate, substantially cylindrical external shell; A solid fuel propulsion motor including two separate fuel charges disposed axially spaced apart within said shell to define a space therein, said fuel charges delivering their combustion gases directly to said space between the fuel charges; said fuel charges having relative sizes and locations within said shell such that the common center of gravity thereof substantially coincides with the total center of gravity of the missile and relative rates of burning such that their common center of gravity remains substantially stationary relative the missile during the burning of the charges and said space between the fuel charges being located to coincide substantially with the location of said center of gravity; an annular member encircling said space and forming an annular portion of said shell between said two fuel charges; a plurality of open ended exhaust nozzles for the combustion gases generated by said fuel charges mounted equally circumferentially spaced on said annular member so their inlet ends communicate with said empty space and their outlet ends are located outside of the shell; a plurality of stabilizing wings; and mounting means on said annular member equally circumferentially spaced thereon and intermediate said exhaust nozzles.
Claim 3
Dependent Claim
35 words
A missile as claimed in claim 1 whErein said annular member has recessed wall portions protruding into said space, said exhaust nozzles and said mounting means for said stabilizing wings being located within said recesses.
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) | 1975-08-15 | 1976-02-14 | 1976-08-15 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1979-08-15 | 1980-02-14 | 1980-08-15 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1983-08-15 | 1984-02-14 | 1984-08-15 | $7700.00 | Window Closed / Lapsed |