US4899810A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Low pressure drop condenser/heat pipe heat exchanger
Assignee: Lockheed Martin Corp
•
Filing: 1987-10-22
•
Granted: 1990-02-13
•
Expires: 2007-10-22
Abstract
Abstract A thermal control system adapted for test in a 1G gravity environment and for operation as a microgravity environment includes a capillary pumped loop with a wicked evaporator which produces a coolant vapor head of about 1/2 PSI upon absorbing heat from a heat source. A heat pipe includes a cylindrical portion adapted for absorbing heat, and also includes a radiator panel which rejects absorbed heat. A heat exchanger coupled to receive coolant vapor from the wicked evaporator includes a manifold which directs the vapor to a plurality of parallel fluid channels helically wound about and thermally coupled with the heat absorbing portion of the heat pipe. A liquid manifold is coupled to the liquid side of the fluid channels for receiving cooled liquid, which is returned to the wicked evaporator. The helically disposed fluid channels are dimensioned so that the surface tension forces of the coolant liquid are at least large compared with gravitational forces, and so that the centrifugal forces due to the helical disposition of the fluid channel at least aid in making the flow regimes similar in both microgravity and 1-G testing conditions.
Inventors
- 👤 Joseph E. Fredley
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-09 00:37
CPC Classifications
F; F28; F28F; F28F1/00; F28F1/10; F28F1/12; F28F1/14; B; B64; B64G; B64G1/00; B64G1/22; B64G1/46; B64G1/50; B64G1/506; F28B; F28B1/00; F28B1/02; F28D; F28D15/00; F28D15/02; F28D15/04; F28D15/043; B64G1/503; F28F2200/00; F28F2200/005
Claims Analysis
Total Claims: 15
Claim 1
Independent Claim
155 words
A heat exchanger for a spacecraft having a source of heat, a heat source tube passing through said source of heat, a coolant, and a radiator, comprising in combination: a heat pipe having one end coupled to said radiator; a plurality of passages helically wound about said heat pipe, said passages being connected to common first and second junctions at opposite first and second ends of said plurality of passages, said first and second junctions being coupled to respective first and second opposite ends on said heat source tube, said coolant being of a material that tends to be vaporized by said source of heat at said first end of said plurality of passages and tends to liquify at said second end of said plurality of passages, each of said plurality of passages being of a sufficiently small diameter that helical circulation along the walls is primarily due to surface tension and secondary flow effects.
Claim 2
Dependent Claim
155 words
A heat exchanger for a spacecraft having a source of heat, a heat source tube passing through said source of heat, a coolant, and a radiator, comprising in combination: a heat pipe having one end coupled to said radiator; a plurality of passages helically wound about said heat pipe, said passages being connected to common first and second junctions at opposite first and second ends of said plurality of passages, said first and second junctions being coupled to respective first and second opposite ends on said heat source tube, said coolant being of a material that tends to be vaporized by said source of heat at said first end of said plurality of passages and tends to liquify at said second end of said plurality of passages, each of said plurality of passages being of a sufficiently small diameter that helical circulation along the walls is primarily due to surface tension and secondary flow effects.
Claim 3
Dependent Claim
23 words
The combination of claim 1 wherein the diameter of each of said passages is on the order of 1/10 th of an inch.
Claim 4
Dependent Claim
215 words
A heat exchanger adapted for testing in a 1 G gravity environment and operation in a microgravity environment, comprising: an elongated heat pipe including a portion adapted to be coupled to a heat-rejecting plate for rejecting heat, and also including an elongated cylindrical portion adapted for receiving heat which is to be rejected; a source of a flow of heat-laden fluid which is to be cooled; a plurality of channels helically wound about an thermally coupled to said elongated cylindrical portion of said heat pipe, said plurality of channels being coupled for receiving said heat-laden fluid, said channels being wetted by said fluid and having cross-sectional dimensions selected so that the surface tension forces of said fluid are predominant relative to the gravitational forces on said fluid in a 1 G gravity environment, and the helix dimensions being selected so that centrifugal forces are at least significant relative to said gravitational forces in said 1 G gravity environment, whereby heat is transferred from said fluid in said channels to said heat pipe for rejection, resulting in cooled fluid, in much the same manner in a microgravity environment as in a 1 G gravity environment, and testing can therefore take place in a 1 G gravity environment, and operation can take place in a microgravity environment.
Claim 5
Dependent Claim
215 words
A heat exchanger adapted for testing in a 1 G gravity environment and operation in a microgravity environment, comprising: an elongated heat pipe including a portion adapted to be coupled to a heat-rejecting plate for rejecting heat, and also including an elongated cylindrical portion adapted for receiving heat which is to be rejected; a source of a flow of heat-laden fluid which is to be cooled; a plurality of channels helically wound about an thermally coupled to said elongated cylindrical portion of said heat pipe, said plurality of channels being coupled for receiving said heat-laden fluid, said channels being wetted by said fluid and having cross-sectional dimensions selected so that the surface tension forces of said fluid are predominant relative to the gravitational forces on said fluid in a 1 G gravity environment, and the helix dimensions being selected so that centrifugal forces are at least significant relative to said gravitational forces in said 1 G gravity environment, whereby heat is transferred from said fluid in said channels to said heat pipe for rejection, resulting in cooled fluid, in much the same manner in a microgravity environment as in a 1 G gravity environment, and testing can therefore take place in a 1 G gravity environment, and operation can take place in a microgravity environment.
Claim 6
Dependent Claim
23 words
An exchanger according to claim 3 wherein said cooled fluid is returned to said source of a flow of heat-laden fluid for reheating.
Claim 7
Dependent Claim
14 words
An exchanger according to claim 4 wherein said cooled fluid is a subcooled liquid.
Claim 8
Dependent Claim
11 words
An exchanger according to claim 4 wherein said fluid is ammonia.
Claim 9
Dependent Claim
19 words
An exchanger according to claim 6 wherein said channels have maximum cross-sectional dimensions of approximately 1/10 inch (2.5 mm).
Claim 10
Dependent Claim
24 words
An exchanger according to claim 6 wherein the pressure drop across said plurality of channels is less than about 0.04 PSI (280N/m 2 ).
Claim 11
Dependent Claim
31 words
An exchanger according to claim 7 wherein said helix has an average diameter of approximately 0.8 inch for a linear flow rate within each of said channels of about 0.25 lbm/hour.
Claim 12
Dependent Claim
187 words
A thermal control system for a spacecraft, comprising: a capillary pumped system for pumping fluid ammonia around a closed loop, said system including a wicked evaporator for absorbing heat and for using the absorbed heat to vaporize ammonia to produce ammonia vapor at low pressure; at least one condenser coupled to said wicked evaporator for receiving said ammonia vapor, said condenser including a heat rejecting radiator thermally coupled to one end of an elongated heat pipe including a cylindrical portion adapted for receiving heat, said condenser further including a plurality of fluid channels coupled in parallel for receiving said ammonia vapor, said fluid channels being helically wound about said cylindrical portion of said heat pipe and thermally coupled thereto, said fluid channels further having cross-sectional dimensions selected to cause surface tension forces between said ammonia in said liquid form and the interior surfaces of said fluid channels to be at least significant in relation to gravitational forces when operated in a 1 G gravity environment, whereby said condenser cools said ammonia vapor to a liquid form; and means for returning said liquid ammonia to said wicked evaporator.
Claim 13
Dependent Claim
187 words
A thermal control system for a spacecraft, comprising: a capillary pumped system for pumping fluid ammonia around a closed loop, said system including a wicked evaporator for absorbing heat and for using the absorbed heat to vaporize ammonia to produce ammonia vapor at low pressure; at least one condenser coupled to said wicked evaporator for receiving said ammonia vapor, said condenser including a heat rejecting radiator thermally coupled to one end of an elongated heat pipe including a cylindrical portion adapted for receiving heat, said condenser further including a plurality of fluid channels coupled in parallel for receiving said ammonia vapor, said fluid channels being helically wound about said cylindrical portion of said heat pipe and thermally coupled thereto, said fluid channels further having cross-sectional dimensions selected to cause surface tension forces between said ammonia in said liquid form and the interior surfaces of said fluid channels to be at least significant in relation to gravitational forces when operated in a 1 G gravity environment, whereby said condenser cools said ammonia vapor to a liquid form; and means for returning said liquid ammonia to said wicked evaporator.
Claim 14
Dependent Claim
61 words
A thermal control system according to claim 10 wherein said condenser includes, in addition to said radiator thermally coupled to one end of said heat pipe, a second radiator thermally coupled to a second end of said heat pipe, said cylindrical portion of said heat pipe being thermally coupled between said one end and said second end of said heat pipe.
Claim 15
Dependent Claim
16 words
A system according to claim 10 wherein said cross-section dimensions are about 1/10 inch (2.5 mm).
References Cited (Backward Citations)
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1993-02-12 | 1993-08-14 | 1994-02-13 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1997-02-12 | 1997-08-14 | 1998-02-13 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2001-02-12 | 2001-08-14 | 2002-02-13 | $7700.00 | Window Closed / Lapsed |