Ventilation conduit for an aircraft

Patent metadata

Field	Value
Publication number	US-10734622-B2
Application number	US-201715495436-A
Country	US
Kind code	B2
Filing date	Apr 24, 2017
Priority date	Feb 25, 2013
Publication date	Aug 4, 2020
Grant date	Aug 4, 2020

Abstract

According to an embodiment, an aircraft comprises 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 ventilation conduit including: a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, and a second portion extending between the composite skin and the second end of the first portion, the second portion comprising an electrically non-conductive material.

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;
a vent valve coupled to a wall of the enclosure, the vent valve having a normally closed position at least between a takeoff altitude and a cruise altitude of the aircraft, wherein the vent valve is configured to automatically move to an open position in response to a battery failure event; and
a ventilation conduit extending from the vent valve to an opening in the composite skin, the ventilation conduit including:
a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, and
a second portion extending between the composite skin and the second end of the first portion, the second portion comprising an electrically non-conductive material.

2. The aircraft of claim 1 , in which the first portion comprises an electrically non-conductive material.

3. The aircraft of claim 2 , in which the electrically non-conductive material of the first portion includes one of a thermoplastic, a fiberglass composite, and an aramid fiber.

4. The aircraft of claim 3 , in which the electrically non-conductive material of the second portion includes one of a thermoplastic, a fiberglass composite, and an aramid fiber.

5. The aircraft of claim 1 , in which the second portion comprises a connector fitting configured to be secured to the second end of the first portion.

6. The aircraft of claim 1 , in which the second portion of the ventilation conduit includes a tube made of an electrically non-conductive material.

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

8. The aircraft of claim 1 , further comprising a thermal spacer; wherein the second portion further includes a flange fitting having a portion that extends into the opening; and wherein the thermal spacer is located between the flange fitting and the composite skin.

9. 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.

10. The aircraft of claim 9 , in which the doubler plate has a protrusion around the opening in the composite skin.

11. 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 second portion at the composite skin.

12. An aircraft comprising:
a fuselage including composite skin;
an enclosure located inside the fuselage;
a rechargeable battery disposed inside the enclosure;
a vent valve coupled to a wall of the enclosure, the vent valve having a normally closed position at least between a takeoff altitude and a cruise altitude of the aircraft, wherein the vent valve is configured to automatically move to an open position in response to a battery failure event;
a ventilation conduit extending from the vent valve to an opening in the composite skin, the ventilation conduit including:
a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, the first portion being formed of an electrically non-conductive material;
a second portion extending between the composite skin and the second end of the first portion, the second portion being formed of an electrically non-conductive material; and
a flange fitting attached to the second portion of the ventilation conduit, 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 , in which the electrically non-conductive material of each of the first portion and the second portion includes one of a thermoplastic, a fiberglass composite, and an aramid fiber.

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 normally closed vent valve that couples the first portion of the ventilation conduit to the enclosure.

16. The aircraft of claim 12 , in which the second portion includes an electrically non-conductive tube having a first end coupled to the second end of the first portion.

17. An aircraft comprising:
a fuselage including composite skin;
a fairing on an exterior surface of the composite skin;
an enclosure located inside the fuselage;
a rechargeable battery disposed inside the enclosure;
a vent valve coupled to a wall of the enclosure, the vent valve having a normally closed position at least between a takeoff altitude and a cruise altitude of the aircraft, wherein the vent valve is configured to automatically move to an open position in response to a battery failure event;
a ventilation conduit extending from the vent valve to an opening in the composite skin, the ventilation conduit including:
a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, the first portion being formed of an electrically non-conductive material;
a second portion extending between the composite skin and the second end of the first portion, the second portion being formed of an electrically non-conductive material; and
a flange fitting attached to the second portion of the ventilation conduit, the flange fitting having a portion that extends into the opening in the composite skin;

a thermal spacer located between the flange fitting and the composite skin;
a second conduit that penetrates the fairing; and
a flexible hose that connects the second conduit to the second portion at the composite skin.

18. The aircraft of claim 17 , in which the electrically non-conductive material of each of the first portion and the second portion includes one of a thermoplastic, a fiberglass composite, and an aramid fiber.

19. The aircraft of claim 18 , further comprising a doubler plate on an exterior surface of the composite skin, over the opening in the composite skin, wherein the doubler plate has a protrusion extending around the opening in the composite skin.

20. The aircraft of claim 17 , in which the composite skin is made of a carbon fiber-reinforced plastic (CFRP).

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

• B64C1/00

  Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like · CPC title

• H01M50/317 Primary

  Re-sealable arrangements · CPC title

• H01M50/3425

  in the form of rupturable membranes or weakened parts, e.g. pierced with the aid of a sharp member · CPC title

• H01M50/333

  Spring-loaded vent valves · CPC title

• Y02E60/10

  Energy storage using batteries · CPC title