Ventilation conduit for an aircraft

Patent metadata

Field	Value
Publication number	US-9663233-B2
Application number	US-201414188603-A
Country	US
Kind code	B2
Filing date	Feb 24, 2014
Priority date	Feb 25, 2013
Publication date	May 30, 2017
Grant date	May 30, 2017

Abstract

An aircraft comprises composite skin having an opening, and a ventilation conduit having an end portion that extends to the opening in the composite skin. The conduit is made of metal except for the end portion, which functions as an electrical insulator.

First claim

The invention claimed is:

1. An aircraft comprising:
a fuselage including composite skin;
an enclosure located inside the fuselage;
a rechargeable battery disposed inside the enclosure; and
a ventilation conduit extending from the enclosure to an opening in the composite skin, the conduit including:
a metal portion having a first end coupled to the enclosure and a second end spaced from the composite skin, and
an electrically non-conductive portion coupled between the composite skin and the second end of the metal portion.

2. The aircraft of claim 1 , wherein the electrically non-conductive portion includes:
an electrically non-conductive tube having a first end coupled to the second end of the metal portion; and
a flange fitting attached to a second end of the non-conductive tube, the flange fitting having a portion that extends into the opening in the composite skin.

3. The aircraft of claim 2 , wherein the electrically non-conductive tube is made of one of a thermoplastic, a fiberglass composite, and an aramid composite.

4. The aircraft of claim 2 , further comprising a thermal spacer located between the flange fitting and the composite skin.

5. The aircraft of claim 1 , further comprising a doubler plate on an exterior surface of the composite skin, over the opening in the composite skin.

6. The aircraft of claim 5 , wherein the doubler plate has a protrusion around the opening in the composite skin.

7. The aircraft of claim 1 , wherein the composite skin is made of a carbon fiber-reinforced plastic (CFRP).

8. The aircraft of claim 1 , wherein the electrically non-conductive portion has a length of at least two inches.

9. The aircraft of claim 1 , wherein the electrically non-conductive portion is formed of at least one of a thermoplastic, a fiberglass composite, and an aramid fiber.

10. The aircraft of claim 1 , further comprising:
a fairing on an exterior surface of the composite skin;
a second conduit that penetrates the fairing; and
a flexible hose that connects the second conduit to the electrically non-conductive portion at the composite skin.

11. The aircraft of claim 1 , further comprising a normally closed vent valve that couples the metal portion of the conduit to the enclosure.

12. An aircraft comprising:
a fuselage including composite skin;
an enclosure located inside the fuselage;
a rechargeable battery disposed inside the enclosure;
a ventilation conduit extending from the enclosure to an opening in the composite skin, the conduit including:
a metal portion having a first end coupled to the enclosure and a second end spaced from the composite skin;
an electrically non-conductive portion coupled between the composite skin and the second end of the metal portion; and
a flange fitting attached to a second end of the non-conductive tube, the flange fitting having a portion that extends into the opening in the composite skin; and

a thermal spacer located between the flange fitting and the composite skin.

13. The aircraft of claim 12 , wherein the electrically non-conductive tube is made of one of a thermoplastic, a fiberglass composite, and an aramid composite.

14. The aircraft of claim 12 , further comprising a doubler plate on an exterior surface of the composite skin, over the opening in the composite skin.

15. The aircraft of claim 12 , further comprising:
a fairing on an exterior surface of the composite skin;
a second conduit that penetrates the fairing; and
a flexible hose that connects the second conduit to the electrically non-conductive portion at the composite skin.

16. The aircraft of claim 12 , further comprising a normally closed vent valve that couples the metal portion of the conduit to the enclosure.

17. The aircraft of claim 10 , wherein the electrically non-conductive portion includes:
an electrically non-conductive tube having a first end coupled to the second end of the metal portion; and
a flange fitting attached to a second end of the non-conductive tube, the flange fitting having a portion that extends into the opening in the composite skin.

18. The aircraft of claim 17 , wherein the electrically non-conductive tube is made of one of a thermoplastic, a fiberglass composite, and an aramid composite.

Assignees

• Boeing Co

Inventors

• Plessner Julie K
• Maben Douglas D
• Lewinski Daniel F
• Mceachen George A
• Smith Mark E
• Trent Michael L
• Johnson Richard K

Classifications

• B64C1/1453 Primary

  Drain masts · CPC title

• B64D13/00 Primary

  Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space · CPC title

• B64D41/00

  Power installations for auxiliary purposes · CPC title

• F16L25/026

  for flanged joints · CPC title