Cooling system for rotorcraft laser system

Patent metadata

Field	Value
Publication number	US-10389078-B2
Application number	US-201515534386-A
Country	US
Kind code	B2
Filing date	Dec 10, 2015
Priority date	Jan 21, 2015
Publication date	Aug 20, 2019
Grant date	Aug 20, 2019

Abstract

A cooling system for a rotorcraft laser system is provided. The cooling system includes at least one laser carrying component operatively coupling a laser turret and a laser generating assembly. The cooling system also includes at least one fuel line fluidly coupled to a fuel tank containing a fuel. The cooling system further includes a heat exchanger containing a portion of the laser carrying component and the fuel line to transfer heat therebetween to cool the laser carrying component.

First claim

What is claimed is:

1. A cooling system for a rotorcraft laser system comprising:
at least one laser carrying component operatively coupling a laser turret and a laser generating assembly;
at least one fuel line fluidly coupled to and extending between a fuel tank containing a fuel and a refueling probe; and
a heat sink including a portion of the laser carrying component and a portion of the fuel line such that heat is transferred therebetween to cool the laser carrying component.

2. The cooling system of claim 1 , further comprising a fuel temperature gage operatively coupled to the fuel tank to determine a temperature of the fuel stored therein.

3. The cooling system of claim 1 , further comprising a coolant tank containing a coolant for cooling the laser generating assembly.

4. The cooling system of claim 3 , further comprising:
a fuel supply line configured to route the fuel from the fuel tank to the coolant tank for cooling of the coolant stored therein; and
a fuel return line configured to route the fuel back to the fuel tank after cooling of the coolant.

5. The cooling system of claim 4 , further comprising:
a fuel supply line check valve disposed in the fuel supply line to regulate a flow rate of the fuel; and
a fuel return line check valve disposed in the fuel return line to regulate a flow rate of the fuel.

6. The cooling system of claim 1 , wherein the laser carrying component comprises a fiber cable.

7. The cooling system of claim 1 , further comprising:
a water tank;
a water supply line configured to route water from the water tank to the laser generating assembly; and
a water return line configured to route water back to the water tank after cooling the laser generating assembly.

8. The cooling system of claim 7 , further comprising:
a water temperature gage operatively coupled to the water tank to determine a temperature of the water stored therein; and
a water volume gage operatively coupled to the water tank to determine a volume of the water.

9. The cooling system of claim 7 , further comprising an exhaust line fluidly coupled to the water tank and configured to expel steam from the water tank and to an engine exhaust.

10. The cooling system of claim 7 , wherein the fuel is the primary heat sink for the laser generating assembly, the water being the secondary heat sink for the laser generating assembly.

11. The cooling system of claim 7 , wherein the water is the primary heat sink for the laser generating assembly, the fuel being the secondary heat sink for the laser generating assembly.

12. A cooling system for a rotorcraft laser system comprising:
a laser generating assembly;
a liquid tank, wherein the liquid tank is a water tank;
a liquid supply line configured to route liquid from the liquid tank to the laser generating assembly;
a liquid return line configured to route liquid back to the liquid tank after cooling the laser generating assembly; and
an exhaust line fluidly coupled to the water tank and configured to expel steam from the water tank and to an engine exhaust.

13. The cooling system of claim 12 , wherein the liquid tank is a water tank, the liquid supply line is a water supply line configured to route water from the water tank to the laser generating assembly, and the liquid return line is a water return line configured to route water back to the water tank after cooling the laser generating assembly.

14. A method of cooling a rotorcraft laser system comprising:
generating a laser beam with a laser generating assembly;
routing the laser beam through a laser carrying component from the laser generating assembly to a laser turret;
routing water from a water tank to the laser generating assembly for cooling of the laser generating assembly; and
routing fuel from a fuel tank to the laser generating assembly for cooling of the laser generating assembly.

15. The method of claim 14 , further comprising:
refueling the fuel tank with fuel routed from a refueling probe along at least one fuel line to the fuel tank; and
transferring heat from the laser carrying component to the fuel in the fuel line.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Smiley Alfred Russell
• Koliais Panagiotis
• Lauder Timothy Fred
• Alber Mark R

Classifications

• B64C27/00

  Rotorcraft; Rotors peculiar thereto · CPC title

• H01S3/06704

  Housings; Packages · CPC title

• H01S3/0407

  Liquid cooling, e.g. by water · CPC title

• B64C27/04

  Helicopters · CPC title

• B64D37/04

  Arrangement thereof in or on aircraft · CPC title