In-flight insulation generation using matrix-based heat sink for missiles and other flight vehicles

Patent metadata

Field	Value
Publication number	US-9952026-B2
Application number	US-201514884515-A
Country	US
Kind code	B2
Filing date	Oct 15, 2015
Priority date	Oct 15, 2015
Publication date	Apr 24, 2018
Grant date	Apr 24, 2018

Abstract

A method includes absorbing heat generated at a flight vehicle using a heat sink, where the heat sink includes a matrix. The matrix includes a porous structure having multiple pores at least partially filled with one or more phase change materials. The method also includes converting the matrix into an insulator as the one or more phase change materials change state and exit the porous structure due to the absorbed heat. The matrix with the one or more phase change materials could include an alcogel, and the insulator could include an aerogel. The matrix could reside within a pressurized container that includes at least one seal. The at least one seal can fail due to increased pressure within the pressurized container as the heat is absorbed by the heat sink in order to allow the one or more phase change materials to exit the porous structure.

First claim

What is claimed is:

1. A method comprising:
absorbing heat generated at a flight vehicle using a heat sink, the heat sink comprising a matrix that includes a porous structure having multiple pores at least partially filled with one or more phase change materials; and
converting the matrix into an insulator as the one or more phase change materials change state and exit the porous structure due to the absorbed heat;
wherein the insulator comprises an aerogel.

2. The method of claim 1 , wherein the matrix that includes the porous structure having the multiple pores at least partially filled with the one or more phase change materials comprises an alcogel.

3. The method of claim 2 , wherein:
the matrix comprises silica; and
the one or more phase change materials comprise one or more alcohols.

4. The method of claim 1 , wherein:
the matrix resides within a pressurized container;
the pressurized container comprises at least one seal; and
the at least one seal fails due to increased pressure within the pressurized container as the heat is absorbed by the heat sink in order to allow the one or more phase change materials to exit the porous structure.

5. The method of claim 4 , further comprising:
after the at least one seal fails, maintaining an elevated pressure within the pressurized container using a pressure regulator.

6. The method of claim 1 , further comprising:
venting the one or more phase change materials after the one or more phase change materials exit the porous structure.

7. An apparatus comprising:
a heat sink configured to absorb heat, the heat sink comprising a matrix that includes a porous structure having multiple pores at least partially filled with one or more phase change materials;
wherein the heat sink is configured to convert the matrix into an insulator that comprises an aerogel as the one or more phase change materials change state and exit the porous structure due to the absorbed heat.

8. The apparatus of claim 7 , wherein the matrix that includes the porous structure having the multiple pores at least partially filled with the one or more phase change materials comprises an alcogel.

9. The apparatus of claim 8 , wherein:
the matrix comprises silica; and
the one or more phase change materials comprise one or more alcohols.

10. The apparatus of claim 7 , wherein:
the matrix resides within a pressurized container;
the pressurized container comprises at least one seal; and
the at least one seal is configured to fail due to increased pressure within the pressurized container as the heat is absorbed by the heat sink in order to allow the one or more phase change materials to exit the porous structure.

11. The apparatus of claim 10 , further comprising:
a pressure regulator configured to maintain an elevated pressure within the pressurized container after the at least one seal fails.

12. The apparatus of claim 7 , further comprising:
at least one vent configured to allow escape of the one or more phase change materials after the one or more phase change materials exit the porous structure.

13. The apparatus of claim 7 , wherein the heat sink when absorbing the heat is configured to cool at least one of:
an outer skin of a flight vehicle; and
a motor of the flight vehicle.

14. The apparatus of claim 13 , wherein the heat sink after converting the matrix into the insulator is configured to insulate one or more internal components of the flight vehicle.

15. A system comprising:
a flight vehicle; and
a heat sink configured to absorb heat generated at the flight vehicle, the heat sink comprising a matrix that includes a porous structure having multiple pores at least partially filled with one or more phase change materials;
wherein the heat sink is configured to convert the matrix into an insulator that comprises an aerogel as the one or more phase change materials change state and exit the porous structure due to the absorbed heat.

16. The system of claim 15 , wherein the matrix that includes the porous structure having the multiple pores at least partially filled with the one or more phase change materials comprises an alcogel.

17. The system of claim 16 , wherein:
the matrix comprises silica; and
the one or more phase change materials comprise one or more alcohols.

18. The system of claim 15 , wherein:
the matrix resides within a pressurized container;
the pressurized container comprises at least one seal; and
the at least one seal is configured to fail due to increased pressure within the pressurized container as the heat is absorbed by the heat sink in order to allow the one or more phase change materials to exit the porous structure.

19. The system of claim 15 , wherein:
the flight vehicle comprises one or more internal components; and
the heat sink after converting the matrix into the insulator is configured to insulate the one or more internal components.

20. The system of claim 15 , wherein:
the flight vehicle comprises a missile or rocket; and
the heat sink is one of: (i) positioned under an outer skin of the missile or rocket or (ii) positioned on an exterior surface of a motor of the missile or rocket.

Assignees

• Raytheon Co

Inventors

• Wood Adam C

Classifications

• F42B15/34 Primary

  Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements {(thermal protection fitted in or to cosmonautic vehicles B64G1/58)} · CPC title

• B64G1/58

  Thermal protection, e.g. heat shields · CPC title