Thermal insulation for aircraft components

Patent metadata

Field	Value
Publication number	US-10494080-B2
Application number	US-201715590693-A
Country	US
Kind code	B2
Filing date	May 9, 2017
Priority date	Oct 13, 2015
Publication date	Dec 3, 2019
Grant date	Dec 3, 2019

Abstract

A thermal insulation system for an aircraft is provided. The thermal insulation system includes a carrier and a container. The carrier has an interior surface including a first plurality of magnets that generate a first magnetic field, and an exterior surface that is thermally coupled to at least one high temperature component. The container is surrounded by the interior surface of the carrier, has an exterior surface including a second plurality of magnets that generate a second magnetic field oriented opposite the first magnetic field, and has an interior surface that is thermally coupled to at least one temperature sensitive component. The first magnetic field and the second magnetic field generate a gap between the carrier and the container to reduce a heat transfer from the at least one high temperature component to the at least one temperature sensitive component during operation of the aircraft.

First claim

What is claimed is:

1. A thermal insulation system for an aircraft that includes at least one high temperature component and at least one temperature sensitive component, the thermal insulation system comprising:
a carrier comprising an interior surface that comprises:
a first plurality of magnets, comprising electromagnets that are configured to generate a first magnetic field, and
an exterior surface, thermally coupled to the at least one high temperature component;

a container, surrounded by the interior surface of the carrier, the container comprising:
an exterior surface, comprising a second plurality of magnets, configured to generate a second magnetic field oriented opposite the first magnetic field, and
an interior surface, thermally coupled to the at least one temperature sensitive component; and

at least one controller,
wherein the first magnetic field and the second magnetic field are configured to generate a gap between the interior surface of the carrier and the exterior surface of the container to reduce heat transfer from the at least one high temperature component to the at least one temperature sensitive component during operation of the aircraft,
wherein the at least one controller is configured to apply an excitation current to the first plurality of magnets to generate the first magnetic field, to monitor variations in the gap between the exterior surface of the container and the interior surface of the carrier, and to vary the excitation current applied to the first plurality of magnets to reduce the variations in the gap.

2. The thermal insulation system of claim 1 , wherein:
the second plurality of magnets comprise electromagnets, and
the at least one controller is configured to apply an excitation current to the second plurality of magnets to generate the second magnetic field.

3. The thermal insulation system of claim 2 , wherein:
the at least one controller is configured to vary the excitation current applied to the second plurality of magnets to reduce the variations in the gap.

4. The thermal insulation system of claim 1 , further comprising an Infrared reflective coating, applied to the exterior surface of the container.

5. The thermal insulation system of claim 1 , further comprising an Infrared reflective coating, applied to the interior surface of the carrier.

6. The thermal insulation system of claim 1 , further comprising:
a vacuum line, coupled to an interior space of the carrier, wherein the interior space of the carrier is defined by the interior surface of the carrier; and
a vacuum source, coupled to the vacuum line.

7. The thermal insulation system of claim 1 , further comprising:
a coolant line, coupled to an interior space of the carrier, wherein the interior space of the carrier is defined by the interior surface of the carrier; and
a coolant source, coupled to the coolant line.

8. The thermal insulation system of claim 7 , wherein the coolant source comprises a fuel source for the aircraft.

9. The thermal insulation system of claim 1 , wherein the at least one temperature sensitive component comprises flight electronics for the aircraft.

10. A method of thermally isolating a high temperature component of an aircraft from a temperature sensitive component of the aircraft during operation of the aircraft, the method comprising steps of:
generating a first magnetic field utilizing a first plurality of magnets that are proximate to an interior surface of a carrier onboard the aircraft, wherein the carrier includes an external surface that is thermally coupled to the high temperature component;
generating a second magnetic field oriented opposite the first magnetic field utilizing an excitation current, applied to a second plurality of magnets comprising electromagnets, wherein the second plurality of magnets are proximate to an exterior surface of a container, wherein the exterior surface of the container is surrounded by the interior surface of the carrier, wherein the container includes an interior surface that is thermally coupled to the temperature sensitive component;
generating a gap between the interior surface of the carrier and the exterior surface of the container utilizing the first magnetic field and the second magnetic field to reduce a heat transfer from the high temperature component to the temperature sensitive component during the operation of the aircraft;
monitoring variations in the gap between the exterior surface of the container and the interior surface of the carrier; and
varying the excitation current applied to the second plurality of magnets to reduce the variations in the gap.

11. The method of claim 10 , wherein:
the first plurality of magnets comprises electromagnets; and
the step of generating the first magnetic field further comprises applying an excitation current to the first plurality of magnets.

12. The method of claim 11 , further comprising varying the excitation current, applied to the first plurality of magnets to reduce the variations in the gap.

13. A method of assembly of a thermal insulation system for an aircraft that includes a high temperature component and a temperature sensitive component, the method comprising:
coupling a first plurality of magnets to an interior surface of a carrier, the first plurality of magnets configured to generate a first magnetic field;
thermally coupling the high temperature component to an exterior surface of the carrier;
coupling a second plurality of magnets to an exterior surface of a container, the second plurality of magnets configured to generate a second magnetic field oriented opposite to the first magnetic field;
thermally coupling the temperature sensitive component to an interior surface of the container;
positioning the container within an interior space of the carrier, the interior space defined by the interior surface of the carrier;
coupling a coolant line to the interior space of the carrier; and
coupling a fuel source for the aircraft to the coolant line.

14. The method of claim 13 , wherein the step of coupling the first plurality of magnets to the interior surface of the carrier comprises:
coupling a first plurality of electromagnets to the interior surface of the carrier; and
electrically coupling the first plurality of electromagnets to a current source that is configured to apply an excitation current to generate the first magnetic field.

15. The method of claim 13 , wherein the step of coupling the second plurality of magnets to the exterior surface of the container comprises:
coupling a second plurality of electromagnets to the exterior surface of the container; and
electrically coupling the second plurality of electromagnets to a current source that is configured to apply an excitation current to generate the second magnetic field.

16. The method of claim 13 , further comprising:
applying an Infrared reflective coating to the exterior surface of the container.

17. The method of claim 13 , further comprising:
applying an Infrared reflective coating to the interior surface of the carrier.

18. The method of claim 13 , wherein the step of thermally coupling the high temperature component to the exterior surface of the carrier further comprises thermally coupling a leading surface of the aircraft to the exterior surface of the carrier.

19. The method of claim 13 , wherein the step of thermally coupling the temperature sensitive component to the interior surface of the container further comprises thermally coupling flight electronics for the aircraf

Assignees

• Boeing Co

Inventors

• Clemen Jr Mark Joseph
• Wert Jerry Lee

Classifications

• B64C1/40 Primary

  Sound or heat insulation {, e.g. using insulation blankets} · CPC title

• H01F7/0236

  Magnetic suspension or levitation (for vehicles B60L13/04; magnetic bearings F16C39/063) · CPC title

• B64C1/38

  Constructions adapted to reduce effects of aerodynamic or other external heating · CPC title

• B64C30/00

  Supersonic type aircraft · CPC title