Structural gaseous material storage tank

Patent metadata

Field	Value
Publication number	US-11742500-B2
Application number	US-201916372341-A
Country	US
Kind code	B2
Filing date	Apr 1, 2019
Priority date	Apr 1, 2019
Publication date	Aug 29, 2023
Grant date	Aug 29, 2023

Abstract

A tank has a body defining a chamber therein, the chamber is configured to store a gas at a pressure greater than atmospheric pressure, a first mounting element extending from the body, and a second mounting element extending from the body. The first mounting element and the second mounting element are configured for coupling to a first component of a vehicle and a second component of the vehicle, respectively, and the body is configured to carry a structural load between the first component and the second component when the first mounting element and the second mounting element are coupled thereto. The first component carries a propulsion device and the second component comprises at least one of a wing and a landing element. The tank further includes a stem having an orifice and the stem is configured for delivering the gas to the propulsion device through the orifice.

First claim

What is claimed is:

1. A tank, comprising:
a body defining a chamber therein, the chamber being configured to store a gas at a pressure greater than atmospheric pressure and the body comprising a tubular wall joined between a first transverse wall and a second transverse wall;
a first mounting element extending axially from the first transverse wall of the body; and
a second mounting element extending from the second transverse wall of the body;
wherein the first mounting element and the second mounting element are configured for coupling to a first component of a vehicle and a second component of the vehicle, respectively, and the body is configured to carry a structural load between the first component and the second component when the first mounting element and the second mounting element are coupled thereto;
wherein the first component carries a propulsion device and wherein the second component comprises at least one of a wing and a landing element;
wherein the tank further comprises a stem comprising an orifice, the stem being configured for delivering the gas to the propulsion device through the orifice; and
wherein the first mounting element axially overlaps the stem and wherein the first mounting element comprises radially outer extents less than the radially outer extents of the tubular wall.

2. The tank of claim 1 , wherein the chamber is configured to store the gas at a pressure greater than approximately 55 bar (798 psi).

3. The tank of claim 2 , wherein the chamber is configured to store the gas at a pressure greater than approximately 300 bar (4351 psi).

4. The tank of claim 1 , wherein the body comprises a composite material.

5. The tank of claim 1 , wherein the body comprises a metal.

6. The tank of claim 1 , wherein the first mounting element is unitary with the body.

7. The tank of claim 1 , wherein the first mounting element is coupled to the body.

8. The tank of claim 1 , further comprising:
a fairing extending from the body.

9. A tank, comprising:
a body defining a chamber therein, the chamber being configured to store a gas at a pressure greater than atmospheric pressure and the body comprising a tubular wall joined between a first transverse wall and a second transverse wall; and
a first mounting element on a first portion of the body configured to be coupled to a first component of a vehicle, wherein the first mounting element extends axially from the first transverse wall and radially extends less than the tubular wall;
wherein an outer surface of the body is configured to create a flush junction with an exterior surface of the first component when the first mounting element is coupled to the first component; and
wherein the first component carries a propulsion device;
wherein the tank further comprises a stem comprising an orifice, the stem being configured for delivering the gas to the propulsion device through the orifice; and
wherein the first mounting element axially overlaps the stem.

10. The tank of claim 9 , further comprising:
a first orifice in communication with the chamber; and
a second orifice in communication with the chamber.

11. The tank of claim 9 , further comprising:
a fairing extending from the body.

12. The tank of claim 9 , further comprising:
a second mounting element on a second portion of the body configured to be coupled to a second component of the vehicle.

13. The tank of claim 9 , further comprising:
a third mounting element; and
a fourth mounting element,
wherein the third mounting element and the fourth mounting element are configured for coupling a fairing thereto.

14. The tank of claim 9 , wherein the chamber is configured to store the gas at a pressure greater than approximately 55 bar (798 psi).

15. The tank of claim 9 , wherein the body and the first mounting element comprise a composite material.

Assignees

• Bell Helicopter Textron Inc
• Textron Innovations Inc

Inventors

• Rainville Joseph Dean
• Johns William Ben

Classifications

• B64U20/70

  Constructional aspects of the UAV body · CPC title

• B64U50/32

  generated by fuel cells · CPC title

• B64U30/297

  Tilting rotors · CPC title

• B64U50/18

  Thrust vectoring · CPC title

• B64U10/25

  Fixed-wing aircraft (VTOL aircraft B64U10/20) · CPC title