[특허]Direct condensation radiator for spacecraft

Direct condensation radiator for spacecraft 원문보기

IPC분류정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F28F-011/00 F28F-027/02 B64G-001/56 B64G-001/44
출원번호	US-0838671 (1986-03-12)
발명자 / 주소	Chalmers Douglas R. (Mercer County NJ) Pustay John J. (Mercer County NJ)
출원인 / 주소	RCA Corporation (Princeton NJ 02)
인용정보	피인용 횟수 : 22 인용 특허 : 0

초록 ▼

Cost and weight of a heat transfer structure for a space vehicle can be reduced by an arrangement of redundant channels for the flow of coolant to heat radiating panels, micrometeroid resisting bumpers located adjacent the channels for preventing penetration by all but the most energetic micrometeroids, and a sensing and control arrangement for sensing the penetration of a coolant channel for shutting off that channel to prevent loss of coolant.

대표청구항 ▼

A heat transfer arrangement for removing heat from a space vehicle, comprising: a vapor plenum adapted for receiving heat-laden coolant vapor for distributing said coolant vapor to a plurality of vapor output ports; a liquid plenum including a plurality of input ports for receiving coolant liquid for collecting said coolant liquid and for making said coolant liquid available to a source of waste heat for cooling thereof; a thermally conductive pipe including first and second ends and first and second independent fluid channels extending therethrough from said first end to said second end; fluid coupling means coupled to said first and second fluid channels at said first and second ends, to said vapor and liquid plenums for controllably coupling coolant fluid through said first and second channels from said vapor plenum to said liquid plenum; at least one thermally conductive radiator panel thermally coupled to said pipe and including a portion adapted for substantial black-body radiation into space, whereby said pipe transfers heat from coolant fluid flowing therethrough to said panel for radiation thereof, thereby cooling said fluid, whereby coolant vapor flowing into said first and second channels from said vapor plenum has its latent heat removed, and condenses to a liquid form which in passing towards said liquid plenum further loses sensible heat and decreases in temperature, the environment of said space vehicle being populated by micrometeroids possessing a distribution of kinetic energy ranging from insignificant amounts to amounts sufficient to penetrate the walls of said pipe, which penetration might create an aperture in one of said first and second channels through which said coolant can escape, thereby rendering said heat transfer arrangement ineffective; sensing and control means coupled to said fluid coupling means and to said first and second fluid channels for sensing a coolant leak from one of said first and second fluid channels and for controlling said fluid coupling means for decoupling said vapor and liquid plenums from said one of said first and second channels, whereby coolant fluid flow through the other of said first and second channels maintains a substantial amount of capacity of said heat transfer arrangement.

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Aston, Richard William, Spacecraft radiator panels.
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Aston, Richard William; Langmack, Michael J., Spacecraft radiator panels.
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Low, Lenny; Sebata, Susan, Spacecraft radiator system and method using cross-coupled deployable thermal radiators.
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Dowdy Mack W. (LaCanada CA) Benko Doanld J. (Princeton NJ), Two-phase thermal control system with a spherical wicked reservoir.
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Rossi David A. ; Thompson Clark ; Lounge John M., Universal communications system for space applications.
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IPC	Description
A	생활필수품
A62	인명구조; 소방(사다리 E06C)
A62B	인명구조용의 기구, 장치 또는 방법(특히 의료용에 사용되는 밸브 A61M 39/00; 특히 물에서 쓰이는 인명구조 장치 또는 방법 B63C 9/00; 잠수장비 B63C 11/00; 특히 항공기에 쓰는 것, 예. 낙하산, 투출좌석 B64D; 특히 광산에서 쓰이는 구조장치 E21F 11/00)
A62B-1/08	.. 윈치 또는 풀리에 제동기구가 있는 것

내보내기 구분	파일저장 인쇄 메일전송
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Direct condensation radiator for spacecraft 원문보기

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Direct condensation radiator for spacecraft 원문보기

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이 특허를 인용한 특허 (22)

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