Liquid propellant rocket engine with a propulsion chamber shutter
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0500035
(2009-07-09)
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등록번호 |
US-8347602
(2013-01-08)
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우선권정보 |
FR-08 54773 (2008-07-11) |
발명자
/ 주소 |
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출원인 / 주소 |
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대리인 / 주소 |
Weingarten, Schurgin, Gagnebin & Lebovici LLP
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인용정보 |
피인용 횟수 :
0 인용 특허 :
5 |
초록
▼
A liquid propellant rocket engine with a propulsion chamber shutter, the rocket engine comprises a combustion chamber, a propellant injector device placed at an upstream first end of the combustion chamber, a nozzle throat disposed at a downstream second end of the combustion chamber remote from the
A liquid propellant rocket engine with a propulsion chamber shutter, the rocket engine comprises a combustion chamber, a propellant injector device placed at an upstream first end of the combustion chamber, a nozzle throat disposed at a downstream second end of the combustion chamber remote from the upstream first end, and a diverging portion disposed downstream from the nozzle throat. A selective shutter device for the nozzle throat comprises an axially-symmetrical shutter member placed downstream from the nozzle throat, and axial rod for controlling the shutter member, a first short centering member for the control rod situated at the upstream first end of the combustion chamber level with the propellant injector device, a second short centering member for the control rod situated in the combustion chamber in the vicinity of the nozzle throat and upstream therefrom, and a system for returning the control rod of the selective shutter device for the nozzle throat to the closed position.
대표청구항
▼
1. A liquid propellant rocket engine with a propulsion chamber shutter, the engine comprising a combustion chamber, a propellant injector device disposed at an upstream first end of the combustion chamber, a nozzle throat disposed at a downstream second end of the combustion chamber remote from the
1. A liquid propellant rocket engine with a propulsion chamber shutter, the engine comprising a combustion chamber, a propellant injector device disposed at an upstream first end of the combustion chamber, a nozzle throat disposed at a downstream second end of the combustion chamber remote from the upstream first end, and a diverging portion disposed downstream from the nozzle throat, wherein the rocket engine includes a selective shutter device for the nozzle throat to define at least a closed position in which the nozzle throat is shut completely, and at least one open position in which a predetermined flow section is defined through the nozzle throat, and wherein the selective shutter device comprises an axially-symmetrical shutter member placed downstream from the nozzle throat, an axial rod for controlling the shutter member, a first short centering member for the control rod situated at an upstream first end of the combustion chamber level with the propellant injector device, a second short centering member for the control rod situated in the combustion chamber in the vicinity of the nozzle throat and upstream therefrom, and a system for returning the control rod of the selective shutter device for the nozzle throat to the closed position. 2. A rocket engine according to claim 1, wherein the second short centering member comprises a movable spider secured to the control rod. 3. A rocket engine according to claim 1, wherein the second short centering member comprises a stationary spider secured to the combustion chamber and provided with a central hole through which the control rod is slidably mounted. 4. A rocket engine according to claim 1, including a hydraulic control device actuated by the propellant and acting on an upstream end of the control rod to hold the selective shutter device for the nozzle throat in the open position. 5. A rocket engine according to claim 1, wherein the system for returning the control rod to the closed position comprises a rated spring. 6. A rocket engine according to claim 1, wherein the first short centering for the control rod comprises a sleeve incorporated in the propellant injector device. 7. A rocket engine according to claim 1, including a propellant injector device of annular type. 8. A rocket engine according to claim 1, wherein the axially-symmetrical shutter member is in the form of a spear-head or a nose-cone. 9. A rocket engine according to claim 1, wherein the axial symmetrical shutter member is made of composite material. 10. A rocket engine according to claim 1, wherein the combustion chamber is made of composite material. 11. A rocket engine according to claim 1, wherein the combustion chamber includes an internal protective coating placed between the upstream first end of the combustion chamber and the zone where the second short centering member for the control rod is situated. 12. A rocket engine according to claim 1, wherein the control rod for the selective shutter device for the nozzle throat automatically causes the selective shutter device to open when the pressure in the combustion chamber exceeds a predetermined value. 13. A rocket engine according to claim 1, that is applicable to a propulsion system that delivers thrust that can be modulated and re-ignited, that requires a minimum chamber pressure on ignition, the shutter member being placed in the nozzle throat shutting position during a re-ignition stage.
이 특허에 인용된 특허 (5)
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Sackheim, Robert L.; Hutt, John J.; Anderson, William E.; Dressler, Gordon A., Axisymmetric, throttleable non-gimballed rocket engine.
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Barr, Dustin C.; Lynch, Michael D., Pintle-controlled propulsion system with external ring actuator.
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Fujita,Toshiharu, Side thruster valve and side thruster device.
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Beardsley James D. (Ridgeley WV) Shipley John D. (Orlando FL), System for controlling the nozzle throat area of a rocket motor.
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Nyberg, Donald Gerrit; Groudle, Thomas Adrian; Smith, Richard Doyle, Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles.
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