Patent US3749317A successfully refreshed from Google Patents.
US3749317A
Expired / Lapsed
US
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Thrust vector control system
Assignee: McDonnell Douglas Corp
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Filing: 1971-03-01
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Granted: 1973-07-31
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Expires: 1991-03-01
Abstract
Abstract Deflection of a supersonic jet stream engine exhaust by a shock wave resulting from insertion of a small obstruction or a gas stream into the jet stream. This provides flight path deflection of the vehicle powered by the engine.
Inventors
- 👤 I Osofsky
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-08 17:48
CPC Classifications
F; F02; F02K; F02K9/00; F02K9/80; F02K9/82; F02K9/90
Claims Analysis
Total Claims: 4
Claim 1
Independent Claim
129 words
A thrust vector control system for a rocket engine having an exhaust nozzle including a throat and an exit end, said system comprising: a plurality of shock wave generators spaced about the periphery of said nozzle, each of said generators adapted to insert into the exhaust stream within said nozzle a means for generating a shock wave for deflecting the thrust of said exhaust to thus exert a lateral force on said nozzle, said shock wave generators being explosive actuated cylinders having inwardly directed pistons therein, deflection pins driven by said pistons for penetration through the walls of said nozzle and into the jet exhaust stream through said nozzle, said deflection pins being vane-shaped and angularly directed near said exit to provide for roll stabilization of said rocket engine.
Claim 2
Dependent Claim
129 words
A thrust vector control system for a rocket engine having an exhaust nozzle including a throat and an exit end, said system comprising: a plurality of shock wave generators spaced about the periphery of said nozzle, each of said generators adapted to insert into the exhaust stream within said nozzle a means for generating a shock wave for deflecting the thrust of said exhaust to thus exert a lateral force on said nozzle, said shock wave generators being explosive actuated cylinders having inwardly directed pistons therein, deflection pins driven by said pistons for penetration through the walls of said nozzle and into the jet exhaust stream through said nozzle, said deflection pins being vane-shaped and angularly directed near said exit to provide for roll stabilization of said rocket engine.
Claim 3
Dependent Claim
88 words
A thrust vector control system for a rocket engine having an exhaust nozzle including a throat and an exit end, said system comprising: a plurality of individual unitized, self-contained shock wave gas generators spaced about the periphery of said nozzle for generating gases from selected generators into said exhaust stream, a plurality of fixed vanes positioned near said nozzle exit, said generators being mounted on each side of said vanes whereby selected ones of said generators may be energized to effect desired roll control of said rocket engine.
Claim 4
Dependent Claim
88 words
A thrust vector control system for a rocket engine having an exhaust nozzle including a throat and an exit end, said system comprising: a plurality of individual unitized, self-contained shock wave gas generators spaced about the periphery of said nozzle for generating gases from selected generators into said exhaust stream, a plurality of fixed vanes positioned near said nozzle exit, said generators being mounted on each side of said vanes whereby selected ones of said generators may be energized to effect desired roll control of said rocket engine.
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) | 1976-07-30 | 1977-01-29 | 1977-07-31 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1980-07-30 | 1981-01-29 | 1981-07-31 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1984-07-30 | 1985-01-29 | 1985-07-31 | $7700.00 | Window Closed / Lapsed |