[특허]Rocket stage having engine thrust frame integrated with tank

Astrium GmbH

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특허 상세정보

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Rocket stage having engine thrust frame integrated with tank

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-009/60 F02K-009/42
출원번호	US-0684729 (2012-11-26)
등록번호	US-9347400 (2016-05-24)
우선권정보	DE-10 2011 119 921 (2011-11-25)
발명자 / 주소	Jaeger, Markus Wisse, Menko Garcia, Jesus Gomez
출원인 / 주소	Astrium GmbH
대리인 / 주소	Fasse, W. F.
인용정보	피인용 횟수 : 1 인용 특허 : 8

초록
▼

A rocket stage for a spacecraft includes an engine, a tank for storing a fuel and an oxidizer for combustion in the engine, a rocket stage primary structure, and an engine thrust frame that connects and transmits forces between the engine and the primary structure. The engine thrust frame includes at least an internal part thereof arranged internally within the tank. This internal part of the engine thrust frame forms an imperforate partition that divides an interior space of the tank into at least two chambers for storing the fuel and the oxidizer separ...

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1. A rocket stage for a spacecraft, comprising: an engine;a tank for storing a fuel and an oxidizer for combustion in said engine;a first refillable liquid reservoir;a second refillable liquid reservoir;a rocket stage primary structure; andan engine thrust frame that connects, and transmits forces between, said engine and said primary structure;wherein said engine thrust frame includes at least an internal part thereof arranged internally within said tank,wherein said internal part forms an imperforate partition that divides an interior space of said tank into at least two chambers for storing said fuel and said oxidizer separately from one another,wherein said first refillable liquid reservoir is arranged in communication with a first one of said at least two chambers and said second refillable liquid reservoir is arranged in communication with a second one of said at least two chambers, andwherein said second refillable liquid reservoir is arranged concentrically with said first refillable liquid reservoir at an end of said tank adjoining said engine and, said first refillable liquid reservoir and said second refillable liquid reservoir are bounded and separated from one another by said internal part of said engine thrust frame. 2. The rocket stage according to claim 1, wherein said primary structure is arranged at an opposite end of said tank relative to said end of said tank adjoining said engine. 3. The rocket stage according to claim 1, wherein no part of said engine thrust frame extends externally around said tank from said engine to said primary structure for transmitting forces between said engine and said primary structure. 4. The rocket stage according to claim 1, wherein said internal part is an entirety of said engine thrust frame, and all of said engine thrust frame is arranged internally within said tank. 5. The rocket stage according to claim 1, wherein said engine thrust frame further includes a first external part thereof arranged externally outside of said tank, and wherein said first external part is configured as a conical ring and connects said internal part for force transmission to said primary structure. 6. The rocket stage according to claim 1, wherein said engine thrust frame further includes a second external part thereof arranged externally outside of said tank, and wherein said second external part is configured as a conical ring or a cone and connects said internal part for force transmission to said engine. 7. The rocket stage according to claim 1, wherein said engine thrust frame further includes an external part thereof arranged externally outside of said tank, and wherein said external part is connected directly to or extends continuous with said internal part whereby said engine thrust frame penetrates through a tank wall of said tank. 8. The rocket stage according to claim 1, wherein said engine thrust frame further includes an external part thereof arranged externally outside of said tank, and wherein said external part is discontinuous from said internal part with a tank wall of said tank interposed therebetween, whereby said external part and said internal part are aligned with one another and connected on opposite sides of said tank wall for force transmission therebetween through a thickness of said tank wall. 9. The rocket stage according to claim 1, wherein said primary structure has a cylindrical configuration and is connected to said internal part of said engine thrust frame or to said tank adjoining said internal part for force transmission between said internal part and said primary structure, without a conical attachment ring interposed between said primary structure and said internal part or said tank. 10. The rocket stage according to claim 1, further comprising propellant guide plates that are adapted for collecting and guiding the fuel or the oxidizer, wherein the propellant guide plates protrude inwardly from and extend along said internal part of said engine thrust frame in said first one of said chambers. 11. The rocket stage according to claim 10, further comprising additional propellant guide plates that are adapted for collecting and guiding the oxidizer or the fuel, wherein the additional propellant guide plates protrude inwardly from and extend along a tank wall of said tank in said second one of said chambers. 12. The rocket stage according to claim 1, further comprising a disc-shaped reinforcement plate or rim interposed between and connecting said engine thrust frame to said engine. 13. The rocket stage according to claim 1, wherein said tank has a substantially spherical shape. 14. The rocket stage according to claim 1, wherein said tank includes a cylindrical tank wall portion and two end domes at opposite ends of said cylindrical tank wall portion. 15. The rocket stage according to claim 1, wherein said tank includes two substantially elliptically curved domes. 16. The rocket stage according to claim 1, wherein said tank includes two substantially partially spherically curved domes. 17. The rocket stage according to claim 1, wherein said internal part of said engine thrust frame has a substantially conical shape with a conical wall that extends linearly. 18. The rocket stage according to claim 1, wherein a vertex end of said engine thrust frame ends inside said tank, and further comprising a cylindrical extension that connects said vertex end to said engine. 19. The rocket stage according to claim 1, wherein said internal part of said engine thrust frame has a substantially conical shape with a conical wall that extends convexly. 20. The rocket stage according to claim 1, wherein said internal part of said engine thrust frame has a substantially conical shape with a conical wall that extends concavely.

이 특허에 인용된 특허 (8)

이 특허를 인용한 특허 피인용횟수: 1

Lopez, Alfredo; Grayson, Gary David; Addison, Stephen Michael. Antivortex device and method of assembling thereof. USP2018059970389.

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Rocket stage having engine thrust frame integrated with tank

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Rocket stage having engine thrust frame integrated with tank

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이 특허에 인용된 특허 (8)

이 특허를 인용한 특허 피인용횟수: 1

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