System for structurally integrated thermal management for thin wing aircraft control surface actuators

• US 10,723,437 B2
• Filed: 05/30/2017
• Issued: 07/28/2020
• Est. Priority Date: 05/30/2017
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: White, Edward V.
• Primary Examiner(s): Bonzell, Philip J
• Assistant Examiner(s): Abell, Tye William
• Application Number:
  US15/607,962
• Publication Number:
  US 20180346096A1
• Time in Patent Office: 1,155 Days
• CPC Class Codes: B32B 2260/023 Two or more layers
• CPC Class Codes: B32B 2260/046 Synthetic resin
• CPC Class Codes: B32B 2262/101 Glass fibres
• CPC Class Codes: B32B 2262/106 Carbon fibres, e.g. graphite fibres
• CPC Class Codes: B32B 2266/02 Organic
• CPC Class Codes: B32B 2307/302 Conductive
• CPC Class Codes: B32B 2307/72 Density
• CPC Class Codes: B32B 2605/18 Aircraft blades, propellers B32B2603/00
• CPC Class Codes: B32B 27/065 of foam
• CPC Class Codes: B32B 5/02 characterised by structural features of a fibrous or filamentary layer layer formed of metallic wires B32B15/02; layer formed of natural mineral fibres B32B19/02; layer formed of wood fibres B32B21/02
• CPC Class Codes: B32B 5/18 characterised by features of a layer of foamed material
• CPC Class Codes: B32B 5/245 another layer next to it being a foam layer
• CPC Class Codes: B32B 7/08 by mechanical means
• CPC Class Codes: B64C 1/38 Constructions adapted to reduce effects of aerodynamic or other external heating
• CPC Class Codes: B64C 1/40 Sound or heat insulation , e.g. using insulation blankets
• CPC Class Codes: B64C 13/50 using electrical energy
• CPC Class Codes: B64C 2001/0072 from composite materials
• CPC Class Codes: B64C 3/18 Spars; Ribs; Stringers
• CPC Class Codes: B64C 3/26 Construction, shape, or attachment of separate skins, e.g. panels
• CPC Class Codes: B64C 3/36 Structures adapted to reduce effects of aerodynamic or other external heating
• CPC Class Codes: B64C 9/00 : Adjustable control surfaces or members, e.g. rudders trimming stabilising surfaces B64C5/10
• CPC Class Codes: B64D 13/006 : the air being used to cool structural parts of the aircraft
• CPC Class Codes: B64G 1/50 : for temperature control
• CPC Class Codes: F28F 13/14 : by endowing the walls of conduits with zones of different degrees of conduction of heat
• CPC Class Codes: F28F 2013/001 : Particular heat conductive materials, e.g. superconductive elements for thermal joints F28F2013/006
• CPC Class Codes: Y02T 50/40 : Weight reduction
• CPC Class Codes: Y02T 50/50 : On board measures aiming to increase energy efficiency

Abstract

A thermal management system for transferring heat from a heat load includes a first composite structural member that supports a heat load source, a second composite structural member, and a heat transfer member positioned between the first composite structural member and the second composite structural member and in thermal contact with at least the first composite structural member, and in thermal contact with a heat sink. The system further includes at least one thermally-conductive first fastener that is in thermal contact with the heat transfer member, couples the heat load source to at least the first composite structural member, and conducts heat from the heat load source into the heat transfer member. The heat transfer member conducts heat from the thermally-conductive first fastener to the heat sink.

Claims

1. A thermal management system for transferring heat from a heat load source, the system comprising:

a first composite structural member that supports the heat load source;

a second composite structural member;

a heat transfer member, which is positioned between the first composite structural member and the second composite structural member, is in thermal contact with at least the first composite structural member, and is in thermal contact with a heat sink;

at least one thermally conductive first fastener that connects the first composite structural member to the second composite structural member, is in thermal contact with the heat transfer member, that couples the heat load source to the first composite structural member, and that conducts heat from the heat load source into the heat transfer member; and

wherein

the heat transfer member conducts heat from the thermally conductive first fastener to the heat sink.

2. The system of claim 1 wherein the heat transfer member comprises a pyrolytic graphite strip or strap.

3. The system of claim 1 wherein the heat transfer member further comprises:

carbon foam material.

4. The system of claim 1 wherein the first composite structural member has a first thermal conductivity coefficient, the heat transfer member has a second thermal conductivity coefficient that is higher than the first thermal conductivity coefficient, and the at least one thermally conductive first fastener has a third thermal conductivity coefficient that is higher than the second thermal conductivity coefficient.

5. The system of claim 1 wherein the heat load source further comprises:

an electric actuation system (EAS).

6. The system of claim 1 wherein the at least one thermally conductive first fastener comprises stainless steel.

7. The system of claim 1 wherein the heat transfer member comprises a metallic foam.

8. The system of claim 1 wherein the heat transfer member comprises a graphene material.

9. The system of claim 1 wherein the heat transfer member comprises a carbon nano tube strip or strap.

10. The system of claim 1 wherein the heat transfer member comprises a metallic strip or strap.

11. The system of claim 10 wherein the metallic strip or strap comprises copper.

12. The system of claim 1 wherein the heat sink comprises ambient atmosphere and the system further comprises:

a thermally conductive second fastener, in thermal contact with the heat transfer member, and that couples a composite wing skin to at least the first composite structural member; and

wherein the composite wing skin has at least one side exposed to the ambient atmosphere, and at least a portion of the thermally-conductive second fastener extends to the at least one side exposed to the ambient atmosphere.

13. The system of claim 12 wherein the composite wing skin further comprises:

fibers in a resin and wherein the fibers are more thermally conductive than the resin.

14. The system of claim 12 wherein the at least one thermally conductive first fastener, or the thermally-conductive second fastener comprises stainless steel.

15. The system of claim 12 wherein the composite wing skin comprises fibers in a resin.

16. The system of claim 15 wherein the fibers comprise glass or carbon.

17. The system of claim 12 further comprising:

a stiffening member in contact with at least the first composite structural member and with an interior side of the composite wing skin.

18. The system of claim 17 wherein the stiffening member defines one or more channels.

19. The system of claim 18 wherein the one or more channels contain a portion of the heat transfer member.

20. The system of claim 19 wherein the heat transfer member comprises carbon foam material.