US4273183A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Mechanical heat transfer device
Assignee: United States Department of the Air Force
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Filing: 1979-07-31
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Granted: 1981-06-16
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Expires: 1999-07-31
Abstract
Abstract A unidirectional heat transfer device for use between an electronic assembly on an aircraft and the skin and/or pod on the aircraft. The device includes a thermal decoupler mechanism which operates to disengage a retractable interface heat transfer surface when the skin on the aircraft reaches a predetermined elevated temperature caused by the high speed of the aircraft. In the decoupled mode, the heat from the electronic equipment passes to a phase change material heat absorber to provide a limited capability cooling function during extended high speed aircraft operation.
Inventors
- 👤 Frank E. Altoz
- 👤 William H. Winn
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-02 17:29
CPC Classifications
B; B64; B64D; B64D43/00; F; F28; F28F; F28F27/00
Claims Analysis
Total Claims: 3
Claim 1
Independent Claim
307 words
A unidirectional heat transfer device for use on an aircraft to cool an electronic assembly installed therein, said heat transfer device comprising a heat exchanger in surface contact with the electronic assembly, a plate assembly having one side in surface contact with said heat exchanger, interface coupling surfaces formed between said heat exchanger and said plate assembly, a flexible thermal conductor in surface contact with the other side of said plate assembly, a stationary outer conductor plate having one side in surface contact with said flexible thermal conductor, the other side of said conductor plate being in contact with the outer skin of the aircraft, a thermal actuator positioned within said outer conductor plate for sensing and reacting to the increase in temperature of the outer skin of the aircraft, said actuator being fabricated of a phase change material, an actuator piston attached to said thermal actuator for producing linear movement in response to phase change thereof, a cam roller attached to said actuator piston for movement therewith, a pair of pivoting links positioned between said cam roller and said plate assembly, a cam surface on one of said pivoting links in contact with said cam roller to cause said pivoting links to pivot in response to movement of said cam roller, the pivoting of said pivoting links producing a decoupling movement of said plate assembly to prevent heat from the outer skin of the aircraft from flowing back to the electronic assembly, a first biasing means for holding said plate assembly against the surface of the electronic assembly, and a second biasing means for urging said actuator piston back to its first position when the temperature of the outer skin of the aircraft decreases to a predetermined lower level, thereby allowing heat to flow again from the electronic assembly to the outer skin of the aircraft.
Claim 2
Dependent Claim
307 words
A unidirectional heat transfer device for use on an aircraft to cool an electronic assembly installed therein, said heat transfer device comprising a heat exchanger in surface contact with the electronic assembly, a plate assembly having one side in surface contact with said heat exchanger, interface coupling surfaces formed between said heat exchanger and said plate assembly, a flexible thermal conductor in surface contact with the other side of said plate assembly, a stationary outer conductor plate having one side in surface contact with said flexible thermal conductor, the other side of said conductor plate being in contact with the outer skin of the aircraft, a thermal actuator positioned within said outer conductor plate for sensing and reacting to the increase in temperature of the outer skin of the aircraft, said actuator being fabricated of a phase change material, an actuator piston attached to said thermal actuator for producing linear movement in response to phase change thereof, a cam roller attached to said actuator piston for movement therewith, a pair of pivoting links positioned between said cam roller and said plate assembly, a cam surface on one of said pivoting links in contact with said cam roller to cause said pivoting links to pivot in response to movement of said cam roller, the pivoting of said pivoting links producing a decoupling movement of said plate assembly to prevent heat from the outer skin of the aircraft from flowing back to the electronic assembly, a first biasing means for holding said plate assembly against the surface of the electronic assembly, and a second biasing means for urging said actuator piston back to its first position when the temperature of the outer skin of the aircraft decreases to a predetermined lower level, thereby allowing heat to flow again from the electronic assembly to the outer skin of the aircraft.
Claim 3
Dependent Claim
40 words
The unidirectional heat exchanger defined in claim 1 wherein said flexible thermal conductor is fabricated of thin corrugated copper sheet material and deflects under the action of said thermal actuator when said plate assembly is decoupled from said heat exchanger.
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) | 1984-06-15 | 1984-12-15 | 1985-06-16 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1988-06-15 | 1988-12-15 | 1989-06-16 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1992-06-15 | 1992-12-15 | 1993-06-16 | $7700.00 | Window Closed / Lapsed |