Drainage system for an aircraft

Patent metadata

Field	Value
Publication number	US-2018362136-A1
Application number	US-201715627968-A
Country	US
Kind code	A1
Filing date	Jun 20, 2017
Priority date	Jun 20, 2017
Publication date	Dec 20, 2018
Grant date	—

Abstract

A drainage system for an aircraft is taught herein. The drainage system includes a drain tube defining an orifice. The drainage system further includes a cover movable between a first cover position and a second cover position. The cover is configured to overlay the orifice when the cover is in the first cover position. The cover is configured to expose the orifice when the cover is in the second cover position. The cover is configured to move between the first cover position and the second cover position in the presence of air pressure.

First claim

What is claimed is:

1 . A drainage system for an aircraft, the drainage system comprising:
a drain tube defining an orifice; and a cover movable between a first cover position and a second cover position, the cover configured to overlay the orifice when the cover is in the first cover position, the cover configured to expose the orifice when the cover is in the second cover position, and the cover configured to move between the first cover position and the second cover position in the presence of air pressure.

2 . The drainage system of claim 1 , wherein the air pressure is further defined as freestream pressure generated by the freestream air during flight of the aircraft.

3 . The drainage system of claim 2 , wherein the cover defines an extension portion extending beyond the orifice when the cover is in the first cover position, and the extension portion is configured to cooperate with the freestream air to move the cover against the bias to the second cover position.

4 . The drainage system of claim 3 , wherein the cover has a first side having a first side length and a second side having a second side length with the first side spaced from the second side, the second side length is greater than the first side length, and the second side extends beyond the orifice to define the extension portion.

5 . The drainage system of claim 4 , wherein the first side is pivotably coupled to the drain tube and the cover is configured to pivot between the first cover position and the second cover position.

6 . The drainage system of claim 3 , wherein the cover comprises a base and a shell extending from the base, the shell is configured to overlay the orifice, and the base defines the extension portion.

7 . The drainage system of claim 6 , wherein the shell is slidably coupled to the drain tube and the cover is configured to slide between the first cover position and the second cover position.

8 . The drainage system of claim 3 , wherein the cover comprises a hinge portion and a lever portion extending from the hinge portion, the hinge portion is configured to overlay the orifice, and the lever portion defines the extension portion.

9 . The drainage system of claim 8 , wherein the hinge portion is rotatably coupled to the drain tube and the cover is configured to rotate between the first cover position and the second cover position.

10 . The drainage system of claim 1 , wherein the cover is configured to sealably couple to the orifice to prevent ingress of an object into the orifice when the cover is in the first cover position.

11 . The drainage system of claim 1 , wherein the cover is configured to permit egress of a fluid through the orifice when the cover is in the second cover position.

12 . The drainage system of claim 1 , wherein the cover comprises a spring configured to cooperate with the cover and the drain tube to bias the cover toward the first cover position.

13 . The drainage system of claim 1 , wherein the cover is configured to bias toward the first cover position by gravity when the aircraft is on the ground.

14 . The drainage system of claim 1 further comprising a magnet configured to maintain the cover in first cover position or the second cover position.

15 . An aircraft comprising a drainage system, the drainage system comprising:
a drain tube in fluid communication with the aircraft and defining an orifice; and a cover movable between a first cover position and second cover position, the cover configured to overlay the orifice when the cover is in the first cover position, the cover configured to expose the orifice when the cover is in the second cover position, and the cover configured to move between the first position and the second position in the presence of air pressure.

16 . The aircraft of claim 15 , wherein the air pressure is further defined as freestream pressure generated by the freestream air during flight of the aircraft and wherein the cover comprises an extension portion extending beyond the orifice when the cover is in the first cover position, and the extension portion is configured to cooperate with the freestream air to move the cover against the bias to the second cover position.

17 . The aircraft of claim 16 , wherein the cover has a first side having a first side length and a second side having a second side length with the first side spaced from the second side, the second side length is greater than the first side length, and the second side extends beyond the orifice to define the extension portion, and wherein the first side is pivotably coupled to the drain tube and the cover is configured to pivot between the first cover position and the second cover position.

18 . The aircraft of claim 16 , wherein the cover comprises a base and a shell extending from the base, the shell is configured to overlay the orifice, and the base defines the extension portion, and wherein the shell is slidably coupled to the drain tube and the cover is configured to slide between the first cover position and the second cover position.

19 . The aircraft of claim 16 , wherein the cover comprises a hinge portion and a lever portion extending from the hinge portion, the hinge portion is configured to overlay the orifice, and the lever portion defines the extension portion, and wherein the hinge portion is rotatably coupled to the drain tube and the cover is configured to rotate between the first cover position and the second cover position.

20 . The aircraft of claim 15 , wherein the cover is configured to sealably couple to the orifice to prevent ingress of an object into the orifice when the cover is in the first cover position, and wherein the cover is configured to permit egress of a fluid through the orifice when the cover is in the second cover position.

Assignees

• Gulfstream Aerospace Corp

Inventors

• Wozniak Gregg

Classifications

• B64D11/02

  Toilet fittings · CPC title

• B64C1/1453 Primary

  Drain masts · CPC title

• B64D33/04 Primary

  of exhaust outlets or jet pipes · CPC title

• B64D1/16

  Dropping or releasing powdered, liquid, or gaseous matter, e.g. for fire-fighting (jettisoning fuel B64D37/26) · CPC title

• B61D35/007

  comprising toilet waste receiving, treatment, storage, disposal or removal devices · CPC title