Liquid storage system

• US 10,640,226 B2
• Filed: 05/06/2015
• Issued: 05/05/2020
• Est. Priority Date: 05/07/2014
• Status: Active Grant

• Current Assignee: BAE Systems Plc
• Original Assignee: BAE Systems Plc
• Inventors: Park, Nicholas, Jenkins, Simon Anthony
• Primary Examiner(s): Cheung, Chun Hoi
• Assistant Examiner(s): Patel, Brijesh V.
• Application Number:
  US15/307,669
• Publication Number:
  US 20170043880A1
• Time in Patent Office: 1,826 Days
• Field of Search: 220563, 220562, 220 415, 220 414, 220 412, 220501, 220555, 220553, 137574, 137576, 137571, 244135 B, 244135 R, 2441723, 2441722
• CPC Class Codes: B60K 15/03 Fuel tanks chassis frame comprising fluid storage compartment B62D21/16 ; Details of the fuel feeding system related to the fuel tank F02M37/0076
• CPC Class Codes: B60K 2015/03407 to protect tanks against projectiles
• CPC Class Codes: B60Y 2200/51 Aeroplanes
• CPC Class Codes: B64D 2037/325 Fuel tanks with provisions for reduction hydraulic ram shocks due to projectile impacts
• CPC Class Codes: B64D 37/06 Constructional adaptations thereof
• CPC Class Codes: B64D 37/32 Safety measures not otherwise provided for, e.g. preventing explosive conditions extinguishing or preventing fires in aircraft A62C
• CPC Class Codes: F41H 5/0492 Layered armour containing hard elements, e.g. plates, spheres, rods, separated from each other, the elements being connected to a further flexible layer or being embedded in a plastics or an elastomer matrix

Abstract

A liquid storage system comprising: a tank for containing a liquid, the tank enclosing a liquid storage space; and a tank liner fixedly attached to an internal surface of the tank (16). The tank liner comprises: a plurality of elements, each element having a hardness value of 2 GPa or above; and a binder material in which the plurality of elements are embedded. The elements have a higher hardness value than the binder material. A distance between a first element and the internal surface of the tank in a direction normal to the internal surface of the tank is different to a distance between a second element and the internal surface of the tank in the direction normal to the internal surface of the tank, the first element being different to the second element.

Claims

1. An aircraft fuel storage system comprising:

an aircraft fuel tank for containing aircraft fuel, said aircraft fuel tank enclosing a liquid storage space; and

a tank liner fixedly attached to an internal surface of the aircraft fuel tank, wherein the tank liner comprises;

a plurality of spherical elements, each spherical element having a hardness value of 2 GPa or above; and

a binder material in which the plurality of spherical elements are embedded,

wherein the plurality of spherical elements have a higher hardness value than the binder material,

wherein the tank liner comprises a proximal surface fixedly attached to the internal surface of the aircraft fuel tank and a distal surface spaced apart therefrom opposite to the proximal surface,

wherein a space between opposing distal surfaces of the tank liner defines an enclosed, fuel-storing portion of the aircraft fuel tank,

wherein at least portions of the binder material are exposed directly to the liquid storage space, and

wherein the plurality of spherical elements are arranged as multiple layers of spherical elements between the proximal surface and the distal surfaces of the tank liner.

2. The aircraft fuel storage system according to claim 1, wherein the plurality of spherical elements are uniformly distributed throughout the binder material.

3. The aircraft fuel storage system according to claim 1, wherein the tank liner is more flexible than walls of the aircraft fuel tank.

4. The aircraft fuel storage system according to claim 1, wherein a distance between the proximal surface and the distal surface of the tank liner is between 10 mm and 25 mm.

5. The aircraft fuel storage system according to claim 1, wherein a diameter of each of the plurality of spherical elements is in the range of 2 mm to 6 mm.

6. The aircraft fuel storage system according to claim 1, wherein each of the plurality of spherical element has a hardness value of 20 GPa or above.

7. The aircraft fuel storage system according to claim 1, wherein the plurality of spherical elements are made of ceramic, metal, or a metal alloy.

8. The aircraft fuel storage system according to claim 1, wherein the binder material is a rubber or a polymer.

9. An aircraft comprising the aircraft fuel storage system of claim 1.

10. A method of producing an aircraft fuel storage system, the method comprising:

providing an aircraft fuel tank for containing aircraft fuel, said aircraft fuel tank enclosing a liquid storage space; and

providing, in a liquid or semi-liquid form, a binder material;

adding a plurality of spherical elements to the liquid or semi-liquid binder material, each of the plurality of spherical elements having a hardness value of 2 GPa or above;

solidifying the binder material so as to embed the plurality of spherical elements in the binder material; and

fixedly attaching, to an internal surface of the aircraft fuel tank, the solidified binder material with the plurality of spherical elements embedded therein, thereby proving a tank liner for the aircraft fuel tank, the tank liner being such that the tank liner comprises a proximal surface fixedly attached to the internal surface of the aircraft fuel tank, and a distal surface opposite to the proximal surface, and the plurality of spherical elements are arranged as multiple layers of spherical elements between the proximal surface and the distal surface.

11. The method according to claim 10, wherein the method further comprises:

applying the mixture of the liquid or semi-liquid binder material and the plurality of spherical elements to the internal surface of the aircraft fuel tank; and

solidifying the mixture of the liquid or semi-liquid binder material and the plurality of spherical elements that has been applied to the internal surface of the aircraft fuel tank, thereby bonding the binder material with the plurality of spherical elements embedded therein to the internal surface of the aircraft fuel tank.

12. The method according to claim 10, wherein the method further comprises:

providing a mold, the mold having a shape complementary to the internal surface of the aircraft fuel tank;

applying the mixture of the liquid or semi-liquid binder material and the plurality of spherical elements to the mold;

solidifying the mixture of the liquid or semi-liquid binder material and the plurality of spherical elements that has been applied to the mold; and

thereafter, fixedly attaching, to the internal surface of the aircraft fuel tank, the solidified binder material with the spherical elements embedded therein.