# US 5,702,073 A · Modular liquid skin heat exchanger

> Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt

- Number: US 5,702,073 A
- Document ID: US5702073A
- Status: Granted
- Kind: A
- Application number: 08/620,992
- Filed: 1996-03-22
- Granted: 1997-12-30
- Earliest claimed: 1993-04-27
- Assignees: E-Systems, Inc.
- Inventors: Kyle G. Fluegel
- Web page: https://patentgrep.com/patent/US5702073A

## CPC

- F28D 7/0041: {the conduits for only one medium being tubes having parts touching each other or tubes assembled in panel form (F28D7/0008, F28D7/0058 take precedence)}
- B64C 1/38: Constructions adapted to reduce effects of aerodynamic or other external heating
- B64D 13/00: Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space
- F28F 1/22: the means having portions engaging further tubular elements
- F28F 13/00: Arrangements for modifying heat-transfer, e.g. increasing, decreasing (F28F1/00 - F28F11/00 take precedence)
- F28D 2021/0021: {for aircrafts or cosmonautics}
- Y02T 50/50: On board measures aiming to increase energy efficiency
- F28D: HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS, IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT (fluid heaters having heat generating means and heat transferring means F24H; furnaces F27; details of heat-exchange apparatus of general)
- B64C: AEROPLANES; HELICOPTERS
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- F28F: DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION (water and air traps, air venting F16)
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

A liquid coolant heat exchange system for use in semimonocoque aircraft includes an arcuate planar heat sink fixed along a radius of curvature R.sub.1 by forming members, a flexible arcuate planar spreader plate having a radius R.sub.2, such that R.sub.1 >R.sub.2, a heat exchange tube for transferring heat from the liquid coolant to the heat sink and means for attaching the spreader plate to the forming members to hold the spreader plate in contact with the heat sink.

## Claims

### Claim 1

A method of cooling an on-board electronics system for an aircraft including an arcuate planer fuselage skin having a radius R.sub.1, comprising the steps of:
mounting at least one heat exchange module having a flexible arcuate spreader plate where the spreader plate has a radius R.sub.2, with R.sub.1 >R.sub.2, in thermal contact with the fuselage skin of the aircraft, each heat exchange module having at least one heat exchange tube in thermal contact with the arcuate spreader plate;
coupling each heat exchange tube of the at least one heat exchange module to the on-board electronics system; and
circulating a liquid coolant through the on-board electronics system and through at least one heat exchange tube of at least one heat exchange module.

### Claim 2 (depends on 1)

The method of claim 1 including the step of selectively controlling the circulation of liquid coolant to the at least one of the heat exchange modules.

### Claim 3 (depends on 1)

The method of claim 1 further including the step of thermally cementing the arcuate spreader plate of each at least one heat exchange module to the fuselage skin of the aircraft.

### Claim 4 (depends on 1)

The method of claim 1 wherein the step of circulating includes circulating a microencapsulated phase change liquid coolant through the on-board electronics system and through the at least one heat exchange module.

### Claim 5

A method of cooling an on-board electronics system for an aircraft including an arcuate planer fuselage skin having a radius R.sub.1, comprising the steps of:
mounting a plurality of heat exchange modules each having a flexible arcuate spreader plate where the spreader plate has a radius R.sub.2, with R.sub.1 >R.sub.2, in thermal contact with the fuselage skin of the aircraft, each heat exchange module having at least one heat exchange tube in thermal contact with the arcuate spreader plate;
coupling each heat exchange tube to the on-board electronics system; and
circulating a liquid coolant through the on-board electronics system and through at least one heat exchange tube of the plurality of heat exchange modules.

### Claim 6 (depends on 5)

The method of claim 5, including the step of selectively controlling the circulation of liquid coolant to more than one of the plurality of heat exchange modules.

### Claim 7 (depends on 6)

The method of claim 6 including the step of bypassing the circulation of a liquid coolant through selected ones of the plurality of heat exchange modules.

### Claim 8 (depends on 5)

The method of claim 5 including the step of connecting the plurality of heat exchange modules in a series flow configuration.

### Claim 9 (depends on 5)

The method of claim 5 further including the step of connecting the plurality of heat exchange modules in a parallel flow configuration.

### Claim 10 (depends on 5)

The method of claim 5 including the step of thermally cementing the arcuate spreader plate of each heat exchange module to the fuselage skin of the aircraft.