Cooling a target using electrons

Patent metadata

Field	Value
Publication number	US-10935285-B2
Application number	US-201815919463-A
Country	US
Kind code	B2
Filing date	Mar 13, 2018
Priority date	Jun 13, 2014
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

In an embodiment, a method includes, impinging a plurality of particles on a target such that electrons are emitted from the target and transporting the electrons from the target to a heat sink through a transporting medium. The target and the heat sink may be separated by a distance. The method further includes cooling the electrons using the heat sink and returning the electrons from the heat sink to the target.

First claim

What is claimed is:

1. A system, comprising:
a heat sink configured to cool electrons, the electrons being emitted from a target in response to an impingement of a plurality of particles on the target, wherein the heat sink and the target are separated by a distance;
a return member configured to return the electrons from the heat sink to the target, the return member configured to couple to the heat sink and the target;
a first temperature sensor configured to measure a temperature of the target; and
a processor configured to receive the temperature of the target through the first temperature sensor and to control flow of the electrons from the heat sink back to the target based at least in part on the received temperature.

2. The system of claim 1 , wherein the target comprises a leading edge of a wing of an aerial vehicle.

3. The system of claim 1 , wherein the target comprises an electrically emissive material.

4. The system of claim 1 , wherein a ratio of a cross-sectional area of the heat sink to a cross-sectional area of the target is greater than one.

5. The system of claim 1 , further comprising a cooling device configured to cool the heat sink using a coolant.

6. The system of claim 5 , further comprising:
a first temperature sensor configured to measure a first temperature of the heat sink;
a second temperature sensor configured to measure a second temperature of the target; and
a processor configured to determine whether to adjust a rate of flow of the coolant from the cooling device to the heat sink based on the first temperature and the second temperature.

7. A system, comprising:
a heat sink configured to cool electrons, the electrons being emitted from a leading edge of a wing of an aerial vehicle in response to an impingement of air on the leading edge of the wing, wherein the heat sink is separated from the leading edge of the wing by a distance;
a return member configured to return the electrons from the heat sink to the leading edge of the wing, the return member configured to couple to the heat sink and the leading edge of the wing;
a first temperature sensor configured to measure a temperature of the leading edge; and
a processor configured to receive the temperature of the leading edge through the first temperature sensor and to control flow of the electrons from the heat sink back to the leading edge based at least in part on the received temperature.

8. The system of claim 7 , wherein the return member comprises a wired connection.

9. The system of claim 7 , wherein a ratio of a cross-sectional area of the heat sink to a cross-sectional area of the leading edge of the wing is greater than one.

Assignees

• Lockheed Corp

Inventors

• Allen Edward Henry
• Uribarri Luke Alexander

Classifications

• G12B15/06 Primary

  by contact with heat-absorbing or radiating masses, e.g. heat-sink · CPC title

• B64D47/00

  Equipment not otherwise provided for · CPC title

• B64D43/00

  Arrangements or adaptations of instruments · CPC title

• F25B21/00 Primary

  Machines, plants or systems, using electric or magnetic effects · CPC title

• F25B2321/003

  by using thermionic electron cooling effects · CPC title