Aircraft water tank and method for manufacturing same

Patent metadata

Field	Value
Publication number	US-11067227-B2
Application number	US-201716337897-A
Country	US
Kind code	B2
Filing date	Sep 6, 2017
Priority date	Sep 28, 2016
Publication date	Jul 20, 2021
Grant date	Jul 20, 2021

Abstract

An aircraft water tank includes a conical surface of a skirt portion and a conical surface of an inner liner attached together using an adhesive, with an identical adhesive used in forming a fiber-reinforced resin layer on the inner liner via a filament winding method. When attaching with the adhesive, the adhesive is expelled at the outer circumferential edge of the skirt portion from between the conical surface of the skirt portion and the conical surface of the inner liner. Reinforcement fibers are applied on top of the protruding adhesive, and the adhesive impregnates into the reinforcement fibers. The protruding adhesive and the reinforcement fibers form a reinforcing member which connects a uniform stress surface of the skirt portion to a uniform stress surface of the inner liner located radially outward of the skirt portion.

First claim

The invention claimed is:

1. An aircraft water tank, comprising:
a mouthpiece provided at a center of a dome portion, the dome portion comprising an inner liner and a fiber-reinforced resin layer,
the mouthpiece comprising;
a tubular portion penetrating through an opening of the inner liner and the fiber-reinforced resin layer and to which a lid is joined; and
a skirt portion extending radially outward, between the inner liner and the fiber-reinforced resin layer, from an entire outer circumferential portion of the tubular portion and attached around the opening to the inner liner and the fiber-reinforced resin layer with an adhesive; wherein
the inner liner comprises a first curved surface portion attached to an inner circumferential surface of the skirt portion and a second curved surface portion located radially outward of the skirt portion;
the first curved surface portion is attached to the inner circumferential surface of the skirt portion with an identical adhesive as that used in attaching the fiber-reinforced resin layer to the inner liner;
reinforcing fibers are provided at a portion of the second curved surface portion in a vicinity of an outer circumferential end of the skirt portion via the adhesive expelled from between the inner circumferential surface of the skirt portion and the first curved surface portion radially outward of the skirt portion; and
the adhesive expelled and the reinforcing fibers constitute a reinforcing member for connecting an outer circumferential surface of the skirt portion and the second curved surface portion of the inner liner in a continuous manner.

2. The aircraft water tank according to claim 1 , wherein
the outer circumferential surface of the skirt portion is formed as a uniform stress surface, and the inner circumferential surface of the skirt portion is formed as a conical surface;
the first curved surface portion is formed as a conical surface portion attachable to the conical surface of the skirt portion;
the second curved surface portion comprises a portion of the conical surface portion located radially outward of the skirt portion, and a uniform stress surface portion connected to a portion of the conical surface portion via a bent portion radially outward of the skirt portion;
an imaginary extended surface of the uniform stress surface portion is connected to the uniform stress surface of the skirt portion; and
the reinforcing member is provided on the conical surface portion located radially outward of the skirt portion.

3. The aircraft water tank according to claim 2 , wherein
a bulging portion connected to the skirt portion and bulges radially inward of the tubular portion is provided at a section close to a tank body in an axial center direction of the tubular portion at an inner circumferential portion of the tubular portion;
a mouthpiece-side joint portion to which the lid is joined is provided at a section away from the tank body in the axial center direction of the tubular portion at the inner circumferential portion of the tubular portion;
the bulging portion is provided so as to further project further radially inward than an inner diameter of the mouthpiece-side joint portion;
the bulging portion comprises a surface facing a space inside the mouthpiece-side joint portion at a section close to the mouthpiece-side joint portion of the bulging portion in the axial center direction of the tubular portion;
the inner liner is attached to a surface of the bulging portion from the inner circumferential surface of the skirt portion; and
an end portion of the inner liner is attached to a section of the surface located further radially inward than the inner diameter of the mouthpiece-side joint portion.

4. The aircraft water tank according to claim 3 , wherein
a groove comprising an inner circumferential surface larger in dimension than an inner diameter of the mouthpiece-side joint portion is formed at a boundary section between the mouthpiece-side joint portion and the bulging portion at the inner circumferential portion of the tubular portion.

5. The aircraft water tank according to claim 1 , wherein
the outer circumferential surface of the skirt portion is formed as a uniform stress surface, and the inner circumferential surface of the skirt portion is formed as a conical surface;
the first curved surface portion is formed as a conical surface portion attached to the conical surface of the skirt portion;
the second curved surface portion comprises a uniform stress surface portion located radially outward of the skirt portion, and a connection curved surface portion of the inner liner connected to the conical surface portion located radially inward of the skirt portion via a bent portion and connected to the uniform stress surface portion located radially outward of the skirt portion in a continuous manner;
an imaginary extended surface of the uniform stress surface portion is connected to the uniform stress surface of the skirt portion;
radially inward of the skirt portion and radially outward of the bent portion, in a space between the conical surface of the skirt portion and the connection curved surface portion of the inner liner, the adhesive expelled radially outward of the skirt portion from between the conical surface of the skirt portion and the conical surface portion of the inner liner is filled; and
the reinforcing member is provided on the connection curved surface portion located radially outward of the skirt portion.

6. The aircraft water tank according to claim 5 , wherein
a bulging portion connected to the skirt portion and bulges radially inward of the tubular portion is provided at a section close to a tank body in an axial center direction of the tubular portion at an inner circumferential portion of the tubular portion;
a mouthpiece-side joint portion to which the lid is joined is provided at a section away from the tank body in the axial center direction of the tubular portion at the inner circumferential portion of the tubular portion;
the bulging portion is provided so as to further project further radially inward than an inner diameter of the mouthpiece-side joint portion;
the bulging portion comprises a surface facing a space inside the mouthpiece-side joint portion at a section close to the mouthpiece-side joint portion of the bulging portion in the axial center direction of the tubular portion;
the inner liner is attached to a surface of the bulging portion from the inner circumferential surface of the skirt portion; and
an end portion of the inner liner is attached to a section of the surface located further radially inward than the inner diameter of the mouthpiece-side joint portion.

7. The aircraft water tank according to claim 6 , wherein
a groove comprising an inner circumferential surface larger in dimension than an inner diameter of the mouthpiece-side joint portion is formed at a boundary section between the mouthpiece-side joint portion and the bulging portion at the inner circumferential portion of the tubular portion.

8. The aircraft water tank according to claim 1 , wherein
a bulging portion connected to the skirt portion and bulges radially inward of the tubular portion is provided at a section close to a tank body in an axial center direction of the tubular portion at an inner circumferential portion of the tubular portion;
a mouthpiece-side joint portion to which the lid is joined is provided at a section away from the tank body in the axial center direction of the tubular portion at the inner circumferential portion of the tubular portion;
the bulging portion is provided so as to further project further radially inward than an inner diameter of the mouthpiece-side joint portion;
the bulging portion comprises a

Assignees

• Yokohama Rubber Co Ltd

Inventors

• Kato Hayato
• Ozawa Takahiro

Classifications

• B64D11/02

  Toilet fittings · CPC title

• B64D11/04

  Galleys · CPC title

• F17C2203/0602

  Wall structures; Special features thereof · CPC title

• F17C13/08

  Mounting arrangements for vessels · CPC title

• F17C2203/0604

  Liners · CPC title