# US 2019/0315501 A1 · Thermally-enhanced and deployable structures

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- Number: US 2019/0315501 A1
- Document ID: US20190315501A1
- Status: Published application
- Kind: A1
- Application number: 16/386,968
- Filed: 2019-04-17
- Published: 2019-10-17
- Earliest claimed: 2018-04-17
- Assignees: Raytheon Company
- Applicants: Raytheon Company; ThermAvant Technologies, LLC
- Inventors: Tuan L. Duong; Adam D. Leeds; James E. Benedict; Joseph A. Boswell; Daniel A. Pounds
- Web page: https://patentgrep.com/patent/US20190315501A1

## CPC

- B64G 1/506: {Heat pipes}
- B64G 1/503: {Radiator panels}
- F03G 7/0614: {using shape memory elements}
- F28D 15/0208: {using moving tubes}
- F28F 3/12: Elements constructed in the shape of a hollow panel, e.g. with channels {(F28D1/02, F28D1/03 take precedence)}
- F28D 2021/0021: {for aircrafts or cosmonautics}
- F28F 2255/04: comprising shape memory alloys or bimetallic elements
- F42B 15/34: Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements {(thermal protection fitted in or to cosmonautic vehicles B64G1/58)}
- B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- F03G: SPRING, WEIGHT, INERTIA OR LIKE MOTORS; MECHANICAL-POWER PRODUCING DEVICES OR MECHANISMS, NOT OTHERWISE PROVIDED FOR OR USING ENERGY SOURCES NOT OTHERWISE PROVIDED FOR (arrangements in connection with power supply in vehicles from force of nature B60K16/00; electric propulsion with power supply in vehicles from force of nature B60L8/00)
- 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)
- F28F: DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OF GENERAL APPLICATION (water and air traps, air venting F16)
- F42B: EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION (explosive compositions C06B; fuzes F42C; blasting F42D)

## Abstract

An apparatus includes a structure configured to receive thermal energy and to reject the thermal energy into an external environment. The structure includes a lid and a body. The structure also includes (i) multiple inline and interconnected thermomechanical regions and (ii) one or more oscillating heat pipes embedded in at least some of the thermomechanical regions. Different portions of at least one of the lid and the body form the thermomechanical regions. The one or more oscillating heat pipes are configured to transfer the thermal energy between different ones of the thermomechanical regions. At least one of the thermomechanical regions includes one or more shape-memory materials configured to cause a shape of the structure to change. Each of the one or more oscillating heat pipes includes at least one channel in the structure.

## Claims

### Claim 1

An apparatus comprising:
a structure configured to receive thermal energy and to reject the thermal energy into an external environment, the structure comprising a lid and a body;
wherein the structure also comprises (i) multiple inline and interconnected thermomechanical regions and (ii) one or more oscillating heat pipes embedded in at least some of the thermomechanical regions, different portions of at least one of the lid and the body forming the thermomechanical regions;
wherein the one or more oscillating heat pipes are configured to transfer the thermal energy between different ones of the thermomechanical regions;
wherein at least one of the thermomechanical regions comprises one or more shape-memory materials configured to cause a shape of the structure to change; and
wherein each of the one or more oscillating heat pipes comprises at least one channel in the structure.

### Claim 2 (depends on 1)

The apparatus of claim 1, wherein the thermomechanical regions comprise:
one or more heat input regions configured to receive the thermal energy;
one or more heat rejection regions configured to reject the thermal energy into the external environment; and
one or more morphable regions comprising the one or more shape-memory materials and configured to change shape.

### Claim 3 (depends on 2)

The apparatus of claim 2, wherein the thermomechanical regions further comprise:
one or more adiabatic regions configured to provide structural support or reinforcement while at least substantially preventing heat transfer to and from an external environment.

### Claim 4 (depends on 1)

The apparatus of claim 1, wherein:
the at least one channel of each of the one or more oscillating heat pipes is (i) partially formed in the body and (ii) partially formed in the lid; and
a bond line interface between the body and the lid is aligned with a neutral axis of the structure.

### Claim 5 (depends on 4)

The apparatus of claim 4, wherein the at least one channel of each of the one or more oscillating heat pipes is substantially symmetrical across the neutral axis of the structure to minimize stress along the bond line interface between the body and the lid.

### Claim 6 (depends on 1)

The apparatus of claim 1, wherein the one or more oscillating heat pipes comprise:
a first oscillating heat pipe extending substantially through the structure; and
a second oscillating heat pipe extending substantially through the one or more shape-memory materials.

### Claim 7 (depends on 1)

The apparatus of claim 1, wherein:
the apparatus further comprises at least one heater configured to actively generate thermal energy;
the one or more oscillating heat pipes are configured to receive the actively-generated thermal energy; and
the one or more shape-memory materials are configured to cause the shape of the structure to change based on the actively-generated thermal energy.

### Claim 8 (depends on 1)

The apparatus of claim 1, wherein:
the structure comprises a deployable radiator; and
the apparatus further comprises a flight vehicle, the deployable radiator configured to deploy from the flight vehicle.

### Claim 9 (depends on 8)

The apparatus of claim 8, wherein the flight vehicle comprises a satellite.

### Claim 10

A system comprising:
a flight vehicle;
one or more deployable panels; and
one or more shape-changeable hinges coupled to the one or more deployable panels and the flight vehicle;
wherein each of the one or more shape-changeable hinges comprises:
one or more shape-memory materials configured to cause a shape of the hinge to change; and
one or more thermal energy transfer devices embedded in the one or more shape-memory materials, the one or more thermal energy transfer devices configured to transfer thermal energy at least partially along a length of the hinge.

### Claim 11 (depends on 10)

The system of claim 10, wherein the one or more shape-changeable hinges are configured to:
permit the one or more deployable panels to be folded against the flight vehicle; and
unfold the one or more deployable panels to deploy the one or more deployable panels extending away from the flight vehicle.

### Claim 12 (depends on 10)

The system of claim 10, wherein the system comprises multiple deployable panels and multiple hinges.

### Claim 13 (depends on 12)

The system of claim 12, wherein the hinges are configured to:
permit the deployable panels to be folded upon each other; and
unfold the deployable panels to deploy the deployable panels extending away from the flight vehicle, the deployed panels having a larger exposed surface area than the folded panels.

### Claim 14 (depends on 10)

The system of claim 10, wherein each hinge comprises:
one or more morphable regions comprising the one or more shape-memory materials and configured to change shape.

### Claim 15 (depends on 14)

The system of claim 14, wherein each hinge further comprises:
one or more heat input regions configured to receive the thermal energy; and
one or more heat rejection regions configured to reject the thermal energy.

### Claim 16 (depends on 15)

The system of claim 15, wherein each hinge further comprises:
one or more adiabatic regions configured to provide structural support or reinforcement while at least substantially preventing heat transfer to and from an external environment.

### Claim 17 (depends on 10)

The system of claim 10, wherein, for each hinge, the one or more thermal energy transfer devices comprise one or more oscillating heat pipes.

### Claim 18 (depends on 17)

The system of claim 17, wherein, for each hinge, a bond line interface between a body of the hinge and a lid of the hinge is aligned with a neutral axis of the hinge.

### Claim 19 (depends on 18)

The system of claim 18, wherein, for each hinge, the neutral axis of the hinge equally divides a vertical thickness of the hinge.

### Claim 20 (depends on 10)

The system of claim 10, wherein the flight vehicle comprises a satellite.

### Claim 21

A method comprising:
receiving thermal energy at a structure, the structure comprising (i) a lid and a body, different portions of at least one of the lid and the body forming multiple inline and interconnected thermomechanical regions and (ii) one or more oscillating heat pipes embedded in at least some of the thermomechanical regions;
transferring the thermal energy between different ones of the thermomechanical regions using the one or more oscillating heat pipes; and
rejecting the thermal energy from the structure into an external environment;
wherein at least one of the thermomechanical regions comprises one or more shape-memory materials configured to cause a shape of the structure to change; and
wherein each of the one or more oscillating heat pipes comprises at least one channel in the structure.