Moisture control systems and methods for controlling moisture in an aircraft

Patent metadata

Field	Value
Publication number	US-11548609-B2
Application number	US-201916275416-A
Country	US
Kind code	B2
Filing date	Feb 14, 2019
Priority date	Feb 14, 2019
Publication date	Jan 10, 2023
Grant date	Jan 10, 2023

Abstract

A moisture control system includes an anode coupled to an insulation blanket that is positioned between an inner wall and an outer wall of an aircraft fuselage, a cathode coupled to an interior surface of the outer wall, and a power control unit coupled to the anode and the cathode to apply voltage across the anode and the cathode. When the voltage is applied across the anode and the cathode, moisture is drawn away from the anode and toward the cathode on the interior surface of the outer wall and guided along a drainage path provided via structural members disposed between the inner wall and the outer wall toward a drainage port.

First claim

What is claimed is:

1. A moisture control system, comprising:
an anode coupled to an insulation blanket that is positioned between an inner wall and an outer wall of an aircraft fuselage;
a cathode coupled to an interior surface of the outer wall; and
a power control unit coupled to the anode and the cathode to apply voltage across the anode and the cathode, and when the voltage is applied across the anode and the cathode, moisture is drawn away from the anode and toward the cathode on the interior surface of the outer wall and guided along a drainage path provided via structural members disposed between the inner wall and the outer wall toward a drainage port.

2. The moisture control system of claim 1 , wherein the insulation blanket includes an exterior face positioned adjacent to the outer wall and an interior face opposite the exterior face, and
wherein the anode is coupled to the interior face of the insulation blanket, and wherein when the voltage is applied, the moisture accumulated on and in the insulation blanket is drawn out and away from the insulation blanket towards the cathode.

3. The moisture control system of claim 1 , wherein the insulation blanket includes an exterior face positioned adjacent to the outer wall and an interior face opposite the exterior face, and
wherein the anode is coupled to the exterior face of the insulation blanket.

4. The moisture control system of claim 1 , wherein the cathode includes a continuous cathode strip positioned along the drainage path.

5. The moisture control system of claim 1 , wherein the cathode is partitioned into a plurality of discrete cathodes positioned along the drainage path.

6. The moisture control system of claim 1 , wherein the structural members include frames interconnected with stringers, and
wherein the frames and the stringers include notches through which the moisture flows as the moisture is guided along the drainage path.

7. The moisture control system of claim 1 , further comprising:
a moisture sensor configured to detect presence of the moisture between the inner wall and the outer wall, as well as the moisture accumulating in the insulation blanket,
wherein the power control unit is further configured to apply the voltage in response to the moisture sensor detecting that the moisture exceeds a predefined moisture level.

8. An aircraft comprising:
a fuselage comprising an inner wall, an outer wall, and structural members coupled between the inner wall and the outer wall, wherein the structural members form a drainage path terminating at a drainage port;
an insulation blanket positioned between the inner wall and the outer wall;
an anode coupled to the insulation blanket;
a cathode coupled to an interior surface of the outer wall; and
a power control unit coupled to the anode and the cathode to apply voltage across the anode and cathode, and when the voltage is applied across the anode and the cathode, moisture is drawn away from the anode and toward the cathode on the interior surface of the outer wall and guided along a drainage path provided via the structural members toward the drainage port.

9. The aircraft of claim 8 , wherein the structural members include frames interconnected with stringers, and
wherein the frames and the stringers include notches through which the moisture flows as the moisture is guided along the drainage path.

10. The aircraft of claim 8 , wherein the outer wall of the fuselage includes an electrically conductive material.

11. The aircraft of claim 8 , wherein the insulation blanket includes an exterior face positioned adjacent to the outer wall and an interior face opposite the exterior face, and
wherein the anode is coupled to the interior face of the insulation blanket, and wherein when the voltage is applied, the moisture accumulated on and in the insulation blanket is drawn out and away from the insulation blanket towards the cathode.

12. The aircraft of claim 8 , wherein the insulation blanket includes an exterior face positioned adjacent to the outer wall and an interior face opposite the exterior face, and
wherein the anode is coupled to the exterior face of the insulation blanket.

13. The aircraft of claim 8 , wherein the cathode includes a continuous cathode strip positioned along the drainage path.

14. The aircraft of claim 8 , wherein the cathode is partitioned into a plurality of discrete cathodes positioned along the drainage path.

15. The aircraft of claim 8 , wherein the drainage port is closed when the fuselage is pressurized, and wherein the drainage port opens automatically when the fuselage is non-pressurized.

16. A method for controlling moisture in an aircraft, the method comprising:
coupling an anode to an insulation blanket that is positioned between an inner wall and an outer wall of an aircraft fuselage;
coupling a cathode to an interior surface of the outer wall; and
causing a power control unit to apply voltage across the anode and the cathode, thereby drawing moisture away from the anode and toward the cathode on the interior surface of the outer wall and guiding the moisture along a drainage path provided via structural members disposed between the inner wall and the outer wall toward a drainage port.

17. The method of claim 16 , wherein the insulation blanket includes an exterior face positioned adjacent to the outer wall and an interior face opposite the exterior face, and
wherein coupling the anode to the insulation blanket of the aircraft comprises coupling the anode to the interior face of the insulation blanket, and whereby when the power control unit is applying the voltage, the moisture accumulated on and in the insulation blanket is drawn out and away from the insulation blanket towards the cathode.

18. The method of claim 16 , wherein the insulation blanket includes an exterior face positioned adjacent to the outer wall and an interior face opposite the exterior face, and
wherein coupling the anode to the insulation blanket comprises coupling the anode to the exterior face.

19. The method of claim 16 , wherein coupling the cathode to the interior surface of the outer wall comprises coupling a continuous cathode strip positioned along the drainage path to the interior surface of the outer wall.

20. The method of claim 16 , further comprising:
detecting, by a moisture sensor, presence of the moisture between the inner wall and the outer wall, as well as the moisture accumulating in the insulation blanket;
wherein causing the power control unit to apply the voltage across the anode and the cathode comprises causing the power control unit to apply the voltage across the anode and the cathode in response to the moisture sensor detecting that the moisture exceeds a predefined moisture level.

Assignees

• Boeing Co

Inventors

• Lemery Steven G

Classifications

• Y02T50/40

  Weight reduction · CPC title

• B01D61/56

  Electro-osmotic dewatering · CPC title

• B64C1/40 Primary

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

• B64C1/066

  Interior liners · CPC title

• B64C1/067 Primary

  comprising means for preventing icing or condensation conditions · CPC title