Stagnation pressure activated fuel release mechanism for hypersonic projectiles

• US 6,536,350 B2
• Filed: 03/07/2001
• Issued: 03/25/2003
• Est. Priority Date: 03/07/2001
• Status: Expired due to Term

• Current Assignee: US Department of Energy (Government of the United States of America)
• Original Assignee: United States Department of Energy
• Inventors: Hunter, John W., Cartland, Harry E.
• Primary Examiner(s): Carone, Michael J.
• Assistant Examiner(s): Semunegus, Lulit
• Application Number:
  US09/799,572
• Publication Number:
  US 20020124758A1
• Time in Patent Office: 748 Days
• Field of Search: 244/3.22, 244/130, 102/374, 102/381, 102/380, 102/520, 602/45, 602/51
• US Class Current: 102/374
• CPC Class Codes: F02K 7/10 characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
• CPC Class Codes: F42B 15/10 Missiles having a trajectory only in the air

Abstract

A propulsion-assisted projectile has a body, a cowl forming a combustion section and a nozzle section. The body has a fuel reservoir within a central portion of the body, and a fuel activation system located along the central axis of the body and having a portion of the fuel activation system within the fuel reservoir. The fuel activation system has a fuel release piston with a forward sealing member where the fuel release piston is adapted to be moved when the forward sealing member is impacted with an air flow, and an air-flow channel adapted to conduct ambient air during flight to the fuel release piston.

Claims

1. A gun-launched, propulsion-assisted projectile comprising:

a body having a compression section and a cowl forming a combustion section and a nozzle section;

a fuel reservoir within a central portion of said body; and

a fuel activation system located along the central axis of said body and having a portion of said fuel activation system within said fuel reservoir, said fuel activation system comprising;

a fuel release piston with a forward fuel sealing member wherein said fuel release piston is adapted to be moved when said forward sealing member is impacted with an air flow; and

an air-flow channel adapted to conduct ambient air during flight to said fuel release piston.

2. The projectile of claim 1 wherein said fuel release piston includes a rear sealing member spaced from said forward fuel sealing member and disposed within said fuel reservoir.

3. The projectile of claim 1 wherein said fuel release piston includes a pitot sealing member spaced forwardly of said forward fuel sealing member and adapted to receive said air during flight.

4. The projectile of claim 3 wherein the distance between said pitot sealing member and said forward fuel sealing member is sufficient to prevent said air from mixing with fuel from said fuel reservoir when said fuel release piston is activated.

5. The projectile of claim 1 wherein said air-flow channel is located along the central axis of said body.

6. A fuel release mechanism for use in a propulsion-assisted projectile comprising:

a fuel release piston having a forward fuel sealing member adapted to seal a fuel exit port of a fuel reservoir of said projectile; and

an air-flow channel forward of said fuel release piston and adapted to provide an air-flow pressure from ambient air during flight to said forward fuel sealing member for activating said fuel release piston.

7. The fuel release mechanism of claim 6 wherein said fuel release piston further includes an air-flow channel sealing member forward of said forward fuel sealing member, said air-flow channel sealing member adapted for receiving said air-flow pressure causing activation of said fuel release piston.

8. The fuel release mechanism of claim 6 wherein said fuel release piston further includes a rear channel sealing member spaced rearwardly from said forward fuel sealing member, said rear channel sealing member adapted to seal a rear fuel filling aperture when said fuel release piston is activated.

9. A method of reducing premature fuel release in a propulsion-assisted projectile, said method comprising:

providing a fuel release mechanism having a fuel release piston with at least a fuel release sealing member communicably engaged with a fuel exit aperture;

incorporating an air-flow channel forward of a fuel release piston and adapted to receive an air flow of ambient air during flight of said projectile, said air-flow channel being in communication with said fuel release sealing member; and

adapting said fuel release piston to disengage said fuel release sealing member from said fuel exit aperture when said air flow of ambient air engages said fuel release sealing member during flight.

10. The method of claim 9 further includes providing an air-flow channel sealing member on said fuel release piston spaced forward of said fuel release sealing member wherein said air-flow channel sealing member is adapted to receive said air flow from said air-flow channel, said air-flow channel sealing member further adapted to prevent said air flow and fuel from said fuel exit aperture from mixing.