Heat sink for electrical device
The present invention relates to an apparatus, detachably mountable to the external surface of an aircraft. More specifically, the present invention relates to a fully self-contained apparatus comprising an electrical device, such as a Directed Energy Weapon (DEW), and a corresponding thermal management system and power supply.
1. A pod for a vehicle, vessel or craft, the pod comprising:
an electrical device;
a thermal management system for the electrical device, the thermal management system comprising a heat-activated release hydrogen storage tank and a fluid coolant system having a carrier fluid and encapsulated phase change material (PCM) particles suspended in the carrier fluid;
a porous membrane in the thermal management system, the porous membrane configured to permit flow therethrough of the carrier fluid and to constrain the encapsulated PCM particles; and
an auxiliary power unit (APU), fueled, at least in part, by hydrogen released from the heat-activated release hydrogen storage tank.
2. The pod according to claim 1 , wherein the thermal management system further comprises a fluid coolant system, wherein said APU provides power to both the electrical device and the thermal management system.
3. The pod according to claim 1 , comprising a liquid fuel tank, wherein the APU is further fueled by a liquid fuel from the liquid fuel tank.
4. The pod according to claim 1 , wherein the heat-activated release hydrogen storage tank is a metal hydride system.
5. The pod according to claim 4 , wherein the metal hydride system is an AB, AB2 or AB5 type.
6. The pod according to claim 1 , wherein the APU provides a pressurized air supply to at least one of:
the electrical device;
the thermal management system; and
the APU.
7. The pod according to claim 1 , wherein the APU comprises:
a generator to provide electrical power to the electrical device; and
a gearbox to provide mechanical power to the thermal management system to pump fluid coolant to the electrical device.
8. The pod according to claim 1 , wherein the APU is a gas turbine generator, ram air turbine or a hydrogen fuel cell.
9. The pod according to claim 1 , wherein the electrical device is a laser directed energy weapon (DEW).
10. The pod according to claim 1 , comprising a liquid fuel feed to receive fuel from a fuel reservoir of the vehicle, vessel or craft.
11. The pod according to claim 1 , wherein the pod is configured to receive control signals from the vehicle, vessel or craft, to allow control of the electrical device.
12. The pod according to claim 1 , wherein the pod is detachably affixed to pylons on an aircraft wing.
13. The pod according to claim 1 , wherein the APU provides a pressurized air supply to at least one of:
the electrical device;
the thermal management system; and
an APU liquid fuel supply.
14. The pod according to claim 1 , wherein the pod is detachably affixable to pylons on an aircraft wing.
15. A detachable pod for a vehicle, vessel or craft, the pod comprising:
a liquid fuel tank or feed, to receive liquid fuel;
an electrical device;
a thermal management system for the electrical device, the thermal management system comprising a metal hydride system that includes a heat-activated release hydrogen storage tank and a fluid coolant system with a carrier fluid and encapsulated phase change material (PCM) particles suspended in the carrier fluid;
a porous membrane in the thermal management system, the porous membrane configured to permit flow therethrough of the carrier fluid and to constrain the encapsulated PCM particles; and
an auxiliary power unit (APU), fueled, at least in part, by hydrogen released from the heat-activated release hydrogen storage tank, wherein the APU is further fueled by a liquid fuel from the liquid fuel tank or feed, and wherein the said APU provides power to the electrical device and the thermal management system.
16. The pod according to claim 15 , wherein the electrical device is a laser directed energy weapon (DEW).