SYSTEMS AND METHODS FOR A PASSIVE, FORCED CONVECTION COOLING SYSTEM

• US 20090277993A1
• Filed: 05/07/2008
• Published: 11/12/2009
• Est. Priority Date: 05/07/2008
• Status: Abandoned Application

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Storch, David Robert
• Application Number:
  US12/116,786
• Publication Number:
  US 20090277993A1
• Time in Patent Office: Days
• US Class Current: 244/117.A
• CPC Class Codes: B64D 13/00 Arrangements or adaptations of air-treatment apparatus for aircraft crew or passengers, or freight space , or structural parts of the aircraft treatment rooms with artificial climate for medical purposes A61G10/02; respiratory apparatus in general A62B; for vehicles in general B60H
• CPC Class Codes: B64D 2013/0614 with subsystems for cooling avionics
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y02T 50/50 On board measures aiming to increase energy efficiency

Abstract

Systems and methods for a passive, forced convection cooling system. A system for passive forced convection cooling includes, an intake port located in an area of high pressure on an air frame. The system further has an exhaust port located in an area of low pressure on an air frame. The areas of high and low pressure refer to areas of comparatively high and low pressure regions of the exterior ambient environment. Further still, an internal cooling duct connecting the intake port with the exhaust port, such that air flows from the intake port through the cooling duct to the exhaust port. Additionally the system contains, at least one heat sink located in proximity of the intake port and orientated inside the cooling duct in order to allow the cool air traveling through the cooling duct to cool the at least one heat sink.

Claims

1. A system for passive forced convection cooling comprising:

an intake port located in an area of high pressure on an aircraft;

an exhaust port located in an area of low pressure on an aircraft;

an internal cooling duct connecting the intake port with the exhaust port, such that an airflow travels from the intake port through the cooling duct to the exhaust port; and

at least one heat sink located in proximity of the intake port and orientated inside the cooling duct in order to allow the airflow traveling through the cooling duct to cool the at least one heat sink.

2. The system of claim 1, wherein the intake port and the exhaust port are located on a wing of an aircraft.

3. The system of claim 1, wherein the intake port and the exhaust port are located on a fuselage of an aircraft.

4. The system of claim 1, wherein at least one of the intake port and the output port contain means to block debris from entering the internal cooling duct.

5. The system of claim 1, wherein at least one of the intake port and the exhaust port are shaped to maintain unidirectional air flow.

6. The system of claim 1, wherein the heat sink includes a component located inside the airframe that is sealed from the cooling duct.

7. The system of claim 6, further comprising an electronics system thermally coupled to the heat sink.

8. A system for passive forced convection cooling comprising:

means for air intake in an area of high pressure on an aircraft;

means for air exhaust an area of low pressure on an aircraft;

means for connecting the intake port with the exhaust port, such that an airflow travels from the intake port to the exhaust port; and

means for absorbing heat from an electronic system located in proximity of the intake port and orientated inside the cooling duct in order to allow the airflow traveling through the cooling duct to cool the heat absorbing means.

9. The system of claim 8 wherein the air intake means and the air exhaust means are located on a wing of an aircraft.

10. The system of claim 8 wherein the air intake means and the air exhaust means are located on a fuselage of an aircraft.

11. The system of claim 8 wherein at least one of the intake port and the output port contain means to block debris from entering the internal cooling duct.

12. The system of claim 8 wherein at least one of the air intake means and the air exhaust means are shaped to maintain unidirectional air flow.

13. A method for passive forced convection cooling comprising:

creating a constant air flow through an internal area of an airplane when an intake port is located in an area of high pressure on the airplane and an exhaust port is located on an area of low pressure of the aircraft, the intake port and exhaust port connected by a cooling duct; and

cooling a temperature sensitive device having a heat sink in communication with the cooling duct.

14. The method of claim 13 wherein the intake port and the exhaust port are located on a wing of an airplane.

15. The method of claim 13 wherein the intake port and the exhaust port are located on a fuselage of an airplane.

16. The method of claim 13 wherein at least one of the intake port and the output port contain means to block debris from entering the internal cooling duct.

17. The method of claim 13 wherein at least one of the intake port and the exhaust port are shaped to maintain unidirectional air flow.

18. The method of claim 13 further comprising a heat fin, the heat fin coupled to the heat sink sealing from the heat sink from the cooling duct.