[특허]Fuel tank with specialized tank outlet for spacecraft

EADS Space Transportation GmbH

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특허 상세정보

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Fuel tank with specialized tank outlet for spacecraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B67D-005/54 B67D-005/06
미국특허분류(USC)	137/154; 137/590; 244/172.2; 244/172.3
출원번호	UP-0641182 (2006-12-18)
등록번호	US-7621291 (2009-12-02)
우선권정보	DE-10 2005 062 092(2005-12-22)
발명자 / 주소	Behruzi, Kei Philipp Michaelis, Mark
출원인 / 주소	EADS Space Transportation GmbH
대리인 / 주소	Fasse, W. F.
인용정보	피인용 횟수 : 5 인용 특허 : 29

초록
▼

A fuel tank of a spacecraft stores a liquid fuel and a pressurized propellant gas that drives the fuel out of the tank though a fuel extraction arrangement including a reservoir or fuel collection container and a tank outlet. A spiraling or J-shaped or hook-shaped fuel collection channel and plural obliquely sloping fuel flow channels connect the fuel collection container to an outlet pipe of the tank outlet. The channels are configured, dimensioned, oriented and arranged to ensure that fuel will be retained in the outlet pipe without leaking back into the fuel tank, even when the tank is oriented horizontally and has a low tank filling level. These structures produce a capillary pumping effect and use the surface tension to separate the fuel from the propellant gas, and allow the inner space of the collection container to be completely filled with liquid fuel.

대표
청구항
▼

What is claimed is: 1. A fuel tank for a spacecraft, for storing a liquid fuel and a pressurized propellant gas, said fuel tank comprising: a tank wall enclosing a tank interior space adapted to store the liquid fuel and the propellant gas therein; and a fuel extraction arrangement that communicates out of said tank interior space through said tank wall, and that comprises a fuel collection container and an outlet pipe; wherein: said fuel collection container includes a fuel collection container body that defines therein a fuel reservoir space communicating with said tank interior space through fuel feed passages; said outlet pipe extends from said fuel collection container outwardly away from said tank interior space; and said fuel collection container body has therein a hook-shaped fuel collection channel that communicates with said fuel reservoir space, and plural fuel flow channels that communicate from said fuel collection channel into said outlet pipe, wherein said fuel collection channel has a hook shape on a plane perpendicular to a longitudinal axis of said outlet pipe, wherein said hook shape hooks around or passes through said longitudinal axis in said plane, and wherein said hook shape includes a straight-extending outer leg, a straight-extending inner leg, and a curved or angled hook portion extending between and connecting said outer leg and said inner leg. 2. The fuel tank according to claim 1, wherein said fuel collection container including said fuel collection channel, said fuel flow channels and said fuel reservoir space are configured, dimensioned and arranged to achieve a separation of the liquid fuel from the propellant gas due to a surface tension of the liquid fuel. 3. The fuel tank according to claim 1, wherein said fuel flow channels and said fuel feed passages are respective bored holes. 4. The fuel tank according to claim 1, wherein said fuel collection container body and said outlet pipe are monolithically integral with one another as a unitary one-piece component. 5. The fuel tank according to claim 1, wherein said fuel collection container excludes any sieve and excludes any screen. 6. The fuel tank according to claim 1, wherein said fuel collection channel tapers relatively narrower toward an inner end thereof adjoining said fuel flow channels and flares relatively wider toward an outer end thereof adjoining said fuel reservoir space. 7. The fuel tank according to claim 1, wherein said fuel collection container body further has a groove therein running along and open to said fuel collection channel. 8. The fuel tank according to claim 1, wherein said inner leg and said outer leg extend at an angle relative to one another, with said angle being in a range from 15° to 40° between said inner leg and said outer leg. 9. The fuel tank according to claim 1, wherein said hook shape of said fuel collection channel extends over an angular portion of said fuel collection container body in a range from 260° to 290°around said longitudinal axis. 10. The fuel tank according to claim 1, wherein said fuel reservoir space comprises an annular channel in said fuel collection container body. 11. The fuel tank according to claim 1, wherein said fuel feed passages are arranged in plural groups of plural adjacent fuel feed passages respectively. 12. The fuel tank according to claim 11, wherein there are four of said groups of fuel feed passages, and said groups are located at 90° angular offsets from one another around a central longitudinal axis of said outlet pipe. 13. The fuel tank according to claim 11, wherein an outer end of said fuel collection channel opens into said fuel reservoir space at an angular position between adjacent ones of said groups of fuel feed passages. 14. The fuel tank according to claim 1, wherein said fuel flow channels slope obliquely at an acute angle relative to a central longitudinal axis of said outlet pipe as said fuel flow channels extend from said fuel collection channel to said outlet pipe. 15. The fuel tank according to claim 1, wherein said fuel flow channels each respectively have a diameter of about 2 mm. 16. The fuel tank according to claim 1, wherein said fuel collection container further includes a disk-shaped cover plate arranged with said fuel reservoir space and said fuel feed passages bounded between said cover plate and said fuel collection container body. 17. The fuel tank according to claim 1, in combination with and containing an amount of said liquid fuel that corresponds to less than half of a volume of said tank interior space and that fills said tank interior space to a certain fill level, and in combination with and containing an amount of said propellant gas in said tank interior space above said certain fill level, wherein said fuel tank is arranged in a gravitational environment and is oriented in a horizontal orientation with a longitudinal axis of said outlet pipe extending horizontally, and wherein said certain fill level of said liquid fuel in said tank interior space is below and spaced away from said outlet pipe and said fuel collection container such that said fuel collection container is exposed to said propellant gas. 18. The fuel tank according to claim 17, wherein a retained amount of said liquid fuel is retained in and fills said outlet pipe, said fuel flow channels, and optionally at least a portion of said fuel collection channel, without flowing out of said fuel extraction arrangement back into said tank interior space. 19. The fuel tank according to claim 18, wherein none of said propellant gas penetrates into said fuel flow channels and said outlet pipe despite said horizontal orientation of said fuel tank.

이 특허에 인용된 특허 (29)

이 특허를 인용한 특허 피인용횟수: 5

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Fuel tank with specialized tank outlet for spacecraft

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Fuel tank with specialized tank outlet for spacecraft

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이 특허에 인용된 특허 (29)

이 특허를 인용한 특허 피인용횟수: 5

IPC 상위 출원인

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