US5036905A
Expired / Lapsed
US
⏱️ 0.0 years remaining
High efficiency heat exchanger
Assignee: United States Department of the Air Force
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Filing: 1989-10-26
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Granted: 1991-08-06
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Expires: 2009-10-26
Abstract
Abstract A high efficiency deployable heat radiator system for radiating heat generated at a source of heat aboard an orbiting spacecraft or like vehicle is described which comprises a first subsystem for circulating liquid heat exchange medium into heat exchange relationship with the heat source and for conducting vaporous medium generated at the heat source to a manifold; one or more interconnected movable radiator panels each including a pair of spaced wall members defining heat radiating surfaces; a plurality of heat pipes each having an elongated condenser end disposed between wall members of the radiator panels and in heat exchange relationship with the heat radiating surfaces; a manifold for conducting vaporous medium from the source into heat exchange contact with the evaporator ends of the heat pipes; an interface structure interconnecting the evaporator end of each heat pipe with the manifold and including a tubular member enclosing each evaporator end for conducting vaporous heat exchange medium into contact with the evaporator end and conducting condensed heat exchange medium back toward the source of heat; and wherein each heat pipe includes a flexible portion between the interface structure and the first panel and between panels so that the panels may be selectively moved between folded and deployed positions. The evaporator ends of the heat pipes and the inner surface of the tubular members of the interface structure are preferably grooved to promote heat exchange at the evaporator ends of the heat pipes.
Inventors
- 👤 James E. Eninger
- 👤 David Antonink
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 00:36
CPC Classifications
F; F28; F28D; F28D15/00; F28D15/02; F28D15/0233; B; B64; B64G; B64G1/00; B64G1/22; B64G1/46; B64G1/50; B64G1/503; B64G1/506
Claims Analysis
Total Claims: 12
Claim 1
Independent Claim
300 words
A system for radiating heat generated by a source of heat aboard a spacecraft or like vehicle, which comprises: (a) a source of liquid first heat exchange medium; (b) circulating means for conducting said liquid first heat exchange medium from said source into heat exchange relationship with said source of heat, and for conducting vaporous first heat exchange medium away from said source; (c) a radiator panel comprising a pair of spaced wall members defining heat radiating surfaces; (d) a plurality of heat pipes each having an evaporator end and an elongated condenser end and including a second heat exchange medium, each said elongated condenser end disposed within said radiator panel between said spaced wall members and in heat exchange relationship with said heat radiating surfaces; (e) a manifold having an inlet operatively connected to said circulating means for conducting said vaporous first heat exchange medium from said source into said manifold; (f) a multiplicity of grooves on the outer surface of said evaporator end of each said heat pipe for promoting condensation of said vaporous first heat exchange medium; (g) interface means interconnecting the evaporator end of each said heat pipe with said manifold, said interface means including a tubular member enclosing each said evaporator end and defining a vapor flow passageway therearound, said vapor flow passageway communicating with said manifold for conducting said vaporous first heat exchange medium into heat exchange contact with each said evaporator end, said interface means including a liquid outlet for conducting liquid first heat exchange medium from said interface means toward said circulating means; (h) each of said heat pipes including a flexible portion between said interface means and said panel; and (i) means interconnecting said manifold and said panel for selectively moving said panel between a folded position and a deployed position.
Claim 2
Independent Claim
300 words
A system for radiating heat generated by a source of heat aboard a spacecraft or like vehicle, which comprises: (a) a source of liquid first heat exchange medium; (b) circulating means for conducting said liquid first heat exchange medium from said source into heat exchange relationship with said source of heat, and for conducting vaporous first heat exchange medium away from said source; (c) a radiator panel comprising a pair of spaced wall members defining heat radiating surfaces; (d) a plurality of heat pipes each having an evaporator end and an elongated condenser end and including a second heat exchange medium, each said elongated condenser end disposed within said radiator panel between said spaced wall members and in heat exchange relationship with said heat radiating surfaces; (e) a manifold having an inlet operatively connected to said circulating means for conducting said vaporous first heat exchange medium from said source into said manifold; (f) a multiplicity of grooves on the outer surface of said evaporator end of each said heat pipe for promoting condensation of said vaporous first heat exchange medium; (g) interface means interconnecting the evaporator end of each said heat pipe with said manifold, said interface means including a tubular member enclosing each said evaporator end and defining a vapor flow passageway therearound, said vapor flow passageway communicating with said manifold for conducting said vaporous first heat exchange medium into heat exchange contact with each said evaporator end, said interface means including a liquid outlet for conducting liquid first heat exchange medium from said interface means toward said circulating means; (h) each of said heat pipes including a flexible portion between said interface means and said panel; and (i) means interconnecting said manifold and said panel for selectively moving said panel between a folded position and a deployed position.
Claim 3
Dependent Claim
34 words
The radiator system of claim 1 further comprising a multiplicity of grooves on the inner surface of said evaporator end of each said heat pipe for promoting evaporation of said second heat exchange medium.
Claim 4
Dependent Claim
41 words
The radiator system of claim 1 wherein said first heat exchange medium and said second heat exchange medium each comprise a material selected from the group consisting of hydrogen, oxygen, nitrogen, a hydrocarbon, a fluorocarbon, ammonia, water and a liquid metal.
Claim 5
Dependent Claim
60 words
The heat exchange system of claim 1 wherein each of said heat pipes comprise a slab shaped wicking element disposed axially of each of said heat pipes and extending between said evaporator end and said condenser end thereof for wicking liquid second heat exchange medium from said condenser end to said evaporator end in the operation of said heat pipes.
Claim 6
Dependent Claim
15 words
The heat exchange system of claim 1 further comprising a movable boom supporting said manifold.
Claim 7
Independent Claim
352 words
A system for radiating heat generated by a source of heat aboard a spacecraft or like vehicle, which comprises: (a) a source of liquid first heat exchange medium; (b) circulating means for conducting said liquid first heat exchange medium from said source into heat exchange relationship with said source of heat, and for conducting vaporous first heat exchange medium away from said source; (c) first and second radiator panels each comprising a pair of spaced wall members defining heat radiating surfaces; (d) a plurality of heat pipes each having an evaporator end and an elongated condenser end and including a second heat exchange medium, each said elongated condenser end disposed within said first and second radiator panels between said spaced wall members and in heat exchange relationship with said heat radiating surfaces; (e) each of said condenser ends including a flexible portion between said first and second radiator panels; (f) means interconnecting said first and second radiator panels for selectively moving said second radiator between a folded posistion on said first panel to a deployed position; (g) a manifold having an inlet operatively connected to said circulating means for conducting said vaporous first heat exchange medium from said source into said manifold; (h) a multiplicity of grooves on the outer surface of said evaporator end of each said heat pipe for promoting condensation of said vaporous first heat exchange medium; (i) interface means interconnecting the evaporator end of each said heat pipe with said manifold, said interface means including a tubular member enclosing each said evaporator end and defining a vapor flow passageway therearound, said vapor flow passageway communicating with said manifold for conducting said vaporous first heat exchange medium into heat exchange contact with each said evaporator end, said interface means including a liquid outlet for conducting liquid first heat exchange medium from said interface means toward said circulating means; (i) each of said heat pipes including a flexible portion between said interface means and said panel; and (k) means interconnecting said manifold and said first panel for selectively moving said first panel between a folded position and a deployed position.
Claim 8
Independent Claim
352 words
A system for radiating heat generated by a source of heat aboard a spacecraft or like vehicle, which comprises: (a) a source of liquid first heat exchange medium; (b) circulating means for conducting said liquid first heat exchange medium from said source into heat exchange relationship with said source of heat, and for conducting vaporous first heat exchange medium away from said source; (c) first and second radiator panels each comprising a pair of spaced wall members defining heat radiating surfaces; (d) a plurality of heat pipes each having an evaporator end and an elongated condenser end and including a second heat exchange medium, each said elongated condenser end disposed within said first and second radiator panels between said spaced wall members and in heat exchange relationship with said heat radiating surfaces; (e) each of said condenser ends including a flexible portion between said first and second radiator panels; (f) means interconnecting said first and second radiator panels for selectively moving said second radiator between a folded posistion on said first panel to a deployed position; (g) a manifold having an inlet operatively connected to said circulating means for conducting said vaporous first heat exchange medium from said source into said manifold; (h) a multiplicity of grooves on the outer surface of said evaporator end of each said heat pipe for promoting condensation of said vaporous first heat exchange medium; (i) interface means interconnecting the evaporator end of each said heat pipe with said manifold, said interface means including a tubular member enclosing each said evaporator end and defining a vapor flow passageway therearound, said vapor flow passageway communicating with said manifold for conducting said vaporous first heat exchange medium into heat exchange contact with each said evaporator end, said interface means including a liquid outlet for conducting liquid first heat exchange medium from said interface means toward said circulating means; (i) each of said heat pipes including a flexible portion between said interface means and said panel; and (k) means interconnecting said manifold and said first panel for selectively moving said first panel between a folded position and a deployed position.
Claim 9
Dependent Claim
34 words
The radiator system of claim 6 further comprising a multiplicity of grooves on the inner surface of said evaporator end of each said heat pipe for promoting evaporation of said second heat exchange medium.
Claim 10
Dependent Claim
41 words
The radiator system of claim 6 wherein said first heat exchange medium and said second heat exchange medium each comprise a material selected from the group consisting of hydrogen, oxygen, nitrogen, a hydrocarbon, a fluorocarbon, ammonia, water and a liquid metal.
Claim 11
Dependent Claim
60 words
The heat exchange system of claim 6 wherein each of said heat pipes comprise a slab shaped wicking element disposed axially of each of said heat pipes and extending between said evaporator end and said condenser end thereof for wicking liquid second heat exchange medium from said condenser end to said evaporator end in the operation of said heat pipes.
Claim 12
Dependent Claim
15 words
The heat exchange system of claim 6 further comprising a movable boom supporting said manifold.
References Cited (Backward Citations)
US4040478A
Cited
US4133376A
Cited
US4738304A
Cited
US4727932A
Cited
US4756493A
Cited
US4706740A
Cited
US4832113A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1994-08-05 | 1995-02-04 | 1995-08-06 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1998-08-05 | 1999-02-04 | 1999-08-06 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2002-08-05 | 2003-02-04 | 2003-08-06 | $7700.00 | Window Closed / Lapsed |