Hybrid rocket system with moveable combustion control member
원문보기
IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0086191
(2006-12-07)
|
등록번호 |
US-8387361
(2013-03-05)
|
우선권정보 |
AU-2005906887 (2005-12-08) |
국제출원번호 |
PCT/AU2006/001861
(2006-12-07)
|
§371/§102 date |
20080606
(20080606)
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국제공개번호 |
WO2007/065220
(2007-06-14)
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발명자
/ 주소 |
|
출원인 / 주소 |
- Rocketone Aerospace Pty Ltd.
|
인용정보 |
피인용 횟수 :
1 인용 특허 :
1 |
초록
▼
The present invention describes a hybrid rocket motor that includes a first solid reactant and at least one thrust nozzle and at least one moveable combustion control member within the hybrid rocket motor that restricts the contact of a first fluid reactant in the combustion chamber. In this way, it
The present invention describes a hybrid rocket motor that includes a first solid reactant and at least one thrust nozzle and at least one moveable combustion control member within the hybrid rocket motor that restricts the contact of a first fluid reactant in the combustion chamber. In this way, it is then possible to regulate the exposure of the solid reactant to the fluid reactant and thus control thrust.
대표청구항
▼
1. A hybrid rocket motor comprising: a container having a first fluid and/or gel reactant, a combustion chamber containing at least a first solid reactant therein and having at least one thrust nozzle at one end;a conduit in fluid communication between the container and the combustion chamber;at lea
1. A hybrid rocket motor comprising: a container having a first fluid and/or gel reactant, a combustion chamber containing at least a first solid reactant therein and having at least one thrust nozzle at one end;a conduit in fluid communication between the container and the combustion chamber;at least one moveable combustion control member comprising an extensible or movable port sleeve located within the hybrid rocket motor and attached to a partitioning portion that defines an empty space receiving the first fluid reactant, the extensible/movable port sleeve restricting contact of the first fluid reactant to the first solid reactant in the combustion chamber such that it is then possible to regulate the exposure of the first solid reactant to the first fluid reactant;actuators controlled by a microprocessor to achieve a desired mass flow rate of the first fluid reactant and an extensible/movable position of the port sleeve;the partitioning portion prohibiting the first fluid reactant in the empty space from reacting with the solid reactant adjacent the empty space; anda flight computer using flight control algorithms to achieve control of the first fluid reactant and position of the extensible/moveable port sleeve,wherein: the first solid reactant has an aperture there through that defines a port and the moveable combustion control member is adapted to be located substantially in the port in a first position, andthe moveable combustion control member can be removed from the port to expose the first solid reactant to the first fluid reactant, upon a release of the first fluid reactant into the combustion chamber. 2. The hybrid rocket motor as in claim 1, wherein the moveable combustion control member is an elongate member that can be moved in and out of the port to regulate exposure of the first solid reactant to the first fluid reactant. 3. The hybrid rocket motor as in claim 1, wherein the conduit in fluid communication between the container and the combustion chamber has a valve located between for controlling the delivery of the first fluid reactant. 4. The hybrid rocket motor as in claim 3, wherein the combustion chamber further includes at least a second solid reactant, separated from the first solid reactant by at least one separation member,and wherein the moveable combustion control member, when restricting contact of the first fluid reactant to the second solid reactant in the combustion chamber, allows contact of the first fluid reactant with the first solid reactant. 5. The hybrid rocket motor of claim 4, wherein the at least one separation member is in a fixed position. 6. The hybrid rocket motor as in claim 4, wherein the combustion chamber is defined by the solid reactant. 7. The hybrid rocket motor as in claim 4, wherein the at least one thrust nozzle is moveable. 8. The hybrid rocket motor as in claim 3, wherein flow of the first fluid and/or gel reactant is controlled by the moveable combustion control member; and an automated combustion control member located between the container and the empty space which controls the flow of the first fluid and/or gel reactant into the empty space. 9. The hybrid rocket motor as in claim 8, wherein the automated combustion control member includes an injector face and a selector plate. 10. The hybrid rocket motor as in claim 9, wherein the injector face has at least two apertures there through. 11. The hybrid rocket motor as in claim 10, wherein the at least two apertures of the injector face are of different diameters with respect to each other. 12. The hybrid rocket motor as in claim 11, wherein the at least two apertures on the injector face are spaced evenly. 13. The hybrid rocket motor as in claim 12, wherein the selector plate includes at least one aperture there through. 14. The hybrid rocket motor as in claim 13, wherein the at least one thrust nozzle is moveable and automated to control the thrust direction. 15. The hybrid rocket motor as in claim 14, wherein the selector plate is moveable relative to the injector face so that a desired aperture size may be selected by aligning the aperture in the selector plate with one of the apertures in the injector face. 16. The hybrid rocket motor as in claim 15, wherein the selector plate can pivot about a central axis of rotation. 17. The hybrid rocket motor as in claim 16, wherein the selector plate has a gear about its periphery. 18. The hybrid rocket motor as in claim 17, wherein the selector plate is operated remotely. 19. The hybrid rocket motor as in claim 18, wherein at least one aperture on the selector plate is aligned with an uppermost portion of an injector face so as to allow fluid connection there through. 20. A hybrid rocket motor comprising: a container having a first fluid and/or gel reactant, a combustion chamber containing at least a first solid reactant therein and having at least one thrust nozzle at one end;a conduit in fluid communication between the container and the combustion chamber;at least one moveable combustion control member comprising a port sleeve located within the hybrid rocket motor, the movable combustion control member restricting contact of the first fluid reactant to the first solid reactant in the combustion chamber such that it is then possible to regulate the exposure of the first solid reactant to the first fluid reactant;the movable combustion member further comprising a partitioning portion that defines an empty space receiving the first fluid reactant, the partition portion prohibiting the first fluid reactant in the empty space from reacting with the solid reactant adjacent the empty space; anda flight computer using flight control algorithms to achieve control of the first fluid reactant and position of the extensible/moveable port sleeve,wherein: the first solid reactant has an aperture there through that defines a port and the moveable combustion control member is adapted to be located substantially in the port in a first position, andthe moveable combustion control member can be removed from the port to expose the first solid reactant to the first fluid reactant, upon a release of the first fluid reactant into the combustion chamber to permit consumption of the first solid reactant without consuming the partitioning portion.
이 특허에 인용된 특허 (1)
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Kline Korey R. ; Smith Kevin W. ; Bales Thomas O., Integral solid booster and hybrid thrust sustaining system and projectile incorporating the same.
이 특허를 인용한 특허 (1)
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Figus, Christophe, Anaerobic hybrid propulsion device with fuel present in the form of divided solids.
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