Hydrodynamic ram attenuating fuel tank

• US 4,469,295 A
• Filed: 12/21/1978
• Issued: 09/04/1984
• Est. Priority Date: 12/21/1978
• Status: Expired due to Term

• Current Assignee: Rockwell International Corporation
• Original Assignee: Rockwell International Corporation
• Inventors: Schuster, Irving
• Primary Examiner(s): Shoap, Allan N.
• Application Number:
  US05/972,141
• Time in Patent Office: 2,084 Days
• Field of Search: 244/135 R, 244/135 B, 244/135 A, 244/135 C, 220/900, 220/88 R, 220/469, 220/445, 220/426, 220/89 A, 220/22, 137/68 R
• US Class Current: 244/135.00R
• 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: Y10S 220/90 Rupture proof
• CPC Class Codes: Y10T 137/1632 Destructible element

Abstract

An aircraft fuel tank subject to penetration by projectiles that is improved by virtue of being a segmented container having a frangible liner secured to one internal wall of the fuel container thereby forming an auxiliary tank. Damage caused by hydrodynamic ram effects by a projectile penetrating the main tank is minimized by the rupturing and/or distortion of the frangible liner.

Claims

1. In an aircraft having an engine inlet duct, a fuel tank subject to penetration by a projectile comprising:

a casing defining a hollow fuel storage compartment, said casing being comprised of a plurality of walls connected together to form said casing, one of said walls being a common wall of said inlet duct by also forming a portion of a wall of said inlet duct;

a liner in the form of a sheet positioned within said casing to partition said storage compartment into two cells, said liner forming only one side of each of said two cells, one cell being a main tank and the other cell being an auxiliary tank, said liner being constructed of a shock attenuating frangible membrane;

securing means fastening said liner to said common wall, said liner being spaced from said common wall by said securing means, said liner in combination with said securing means having preselected strength characteristics relative to said common wall such that said liner will deflect and rupture under hydrodynamic ram pulse energy sufficient to puncture said common wall created by shock waves resulting from the projectile penetrating within said fuel tank with hydrodynamic ram pulse energy attenuation by said deflection and rupture of said liner being substantially maximized, whereby impact damage to said common wall from said shock waves is reduced.

2. A fuel tank as described in claim 1 wherein said liner is positioned parallel to said common wall.

3. A fuel tank as described in claim 2 also including fuel management means connected to said fuel tank for withdrawing fuel from said fuel tank, said fuel management means withdrawing substantially all the fuel from said auxiliary tank before withdrawing fuel from said main tank.

4. A fuel tank as described in claim 3 wherein said liner has a thickness in the range of from about 0.03 inches to 0.25 inches.

5. A fuel tank as described in claim 4 wherein said securing means comprises a plurality of fastening members, said members being connected to said common wall and said liner.

6. A fuel tank as described in claim 5 wherein said fastening members have a lateral spacing between each other in the range of about 4 to 16 inches.

7. A fuel tank as described in claim 6 wherein said liner is of a composite material.

8. A fuel tank as described in claim 6 wherein said liner is of a metal material.

9. A fuel tank as described in claim 6 wherein the minimum spacing of said liner from said common wall is 4 inches.

10. A fuel tank as described in claim 9 wherein said securing means allows fuel communication within said auxiliary tank.

11. A fuel tank as described in claim 10 wherein said fuel tank has a depth of at least 8 inches.