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Method and apparatus for radiative heat transfer augmentation for aviation electronic equipments cooled by convection

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Method and apparatus for radiative heat transfer augmentation for aviation electronic equipments cooled by convection


A method and apparatus for radiative heat transfer augmentation for aviation electronic equipments cooled by forced and/or natural convection are disclosed. In one embodiment, the apparatus includes a first heat dissipation device to dissipate heat from the aviation electronic equipments housed in an aviation electronic equipment rack using forced convection. Further, the apparatus includes a second heat dissipation device to enhance heat dissipation from the aviation electronic equipments by radiation and natural convection. Furthermore, the second heat dissipation device is strategically disposed with respect to aircraft skin and configured to maximize radiative view factor.

Inventors: Punit Tiwari, Shreesh Mishra
USPTO Applicaton #: #20120298337 - Class: 16510426 (USPTO) - 11/29/12 - Class 165 
Heat Exchange > Intermediate Fluent Heat Exchange Material Receiving And Discharging Heat >Liquid Fluent Heat Exchange Material >Utilizing Change Of State >Utilizing Capillary Attraction

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The Patent Description & Claims data below is from USPTO Patent Application 20120298337, Method and apparatus for radiative heat transfer augmentation for aviation electronic equipments cooled by convection.

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RELATED APPLICATIONS

Benefit is claimed under 35 U.S.C. 119(a)-(d) to Indian Provisional Application Serial No. 1757/CHE/2011 entitled “METHOD AND APPARATUS FOR RADIATIVE HEAT TRANSFER AUGMENTATION FOR AVIATION ELECTRONIC EQUIPMENTS COOLED BY CONVECTION” filed on May 24, 2011 by Airbus Engineering Centre India.

FIELD OF TECHNOLOGY

Embodiments of the present subject matter relate to dissipating heat from electronic equipments. More particularly, embodiments of the present subject matter relate to dissipating heat by radiation augmentation for electronic equipments on board aircraft cooled by forced and/or natural convection.

BACKGROUND

Electronic equipments installed inside aircraft, often contain many heat generating components that are housed in racks. Existing techniques for cooling such electronic equipments primarily depend on ventilation systems based on forced and/or natural convection. Typically, ventilation of such electronic equipments is based on forced airflow from the bottom of the racks, which then passes through the electronic equipments. The heated air coming from the electronic equipments is then collected and exhausted from the aircraft. Such method of heat extraction is generally referred to as “forced ventilation”. Further, the ventilation of such electronic equipments is also based on natural convection. Generally, natural convection does not occur due to fluid motion generated by an external source (e.g., a pump, a fan, a suction device and the like), but occurs due to density difference in the fluid occurring as a result of temperature gradients.

However, a failure in the forced ventilation system can lead to complete dependence of cooling of the electronic equipments by natural convection and this may not be sufficient and can lead to failure of the electronic equipments.

SUMMARY

A method and apparatus for radiative heat transfer augmentation for aviation electronic equipments cooled by convection are disclosed. According to one aspect of the present subject matter, heat from the aviation electronic equipments housed in an aviation electronic equipment rack is dissipated by forced convection using a first heat dissipation device. Further, heat dissipation from the aviation electronic equipments by radiation and natural convection is enhanced using a second heat dissipation device. In one embodiment, the second heat dissipation device is strategically disposed with respect to aircraft skin and configured to maximize radiative view factor.

According to another aspect of the present subject matter, the apparatus for radiative heat transfer augmentation for the aviation electronic equipments cooled by forced and/or natural convection includes the first heat dissipation device to dissipate heat from the aviation electronic equipments housed in the aviation electronic equipment rack using forced convection. Further, the apparatus includes the second heat dissipation device to enhance heat dissipation from the aviation electronic equipments by natural convection. Furthermore, the second heat dissipation device is strategically disposed with respect to the aircraft skin and configured to maximize radiative view factor.

The methods and apparatuses disclosed herein may be implemented in any means for achieving various aspects. Other features will be apparent from the accompanying drawings and from the detailed description that follow.

BRIEF DESCRIPTION OF THE DRAWINGS

Various embodiments are described herein with reference to the drawings, wherein:

FIG. 1 is a side elevation view of an aircraft showing location of avionics bay, in the context of the invention;

FIG. 2 is an isometric view of the avionics bay in the aircraft, such as those shown in FIG. 1, in the context of the invention;

FIG. 3 is a schematic showing a radiative heat transfer augmentation technique deployed in the aircraft for aviation electronic equipments cooled by forced and/or natural convection, according to one embodiment; and

FIG. 4 illustrates a flow diagram of an exemplary method for radiative heat transfer augmentation for the aviation electronic equipments cooled by forced and/or natural convection, such as those shown in FIG. 3, according to one embodiment.

The drawings described herein are for illustration purposes only and are not intended to limit the scope of the present disclosure in any way.

DETAILED DESCRIPTION

A method and apparatus for radiative heat transfer augmentation for aviation electronic equipments cooled by convection are disclosed. In the following detailed description of the embodiments of the present subject matter, reference is made to the accompanying drawings that form a part hereof, and in which are shown by way of illustration specific embodiments in which the present subject matter may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the present subject matter, and it is to be understood that other embodiments may be utilized and that changes may be made without departing from the scope of the present subject matter. The following detailed description is, therefore, not to be taken in a limiting sense, and the scope of the present subject matter is defined by the appended claims.

FIG. 1 is a side elevation view of an aircraft 100 showing location of avionics bay 102, in the context of the invention. Particularly, FIG. 1 illustrates a portion of the aircraft 100 including the avionics bay 102, a cockpit 104, a cabin 106 and a cargo bay 108. As shown in FIG. 1, the avionics bay 102 is, typically, located below the cockpit 104. However, one can envision, the avionics bay 102 being located anywhere else in the aircraft based on the design and configuration of an aircraft. Further as shown in FIG. 1, the avionics bay 102 includes aviation electronic equipments housed in racks 110. For example, the aviation electronic equipments housed in racks 110 can include one or more aviation electronic equipment racks 110A-N.

Referring now to FIG. 2, an isometric view of the avionics bay 102 in the aircraft 100, such as those shown in FIG. 1, is illustrated, in the context of the invention. Particularly, FIG. 2 illustrates the aviation electronic equipments housed in racks 110, in the avionics bay 102, including one or more aviation electronic equipment racks 110A-N. As shown in FIG. 2, each of the aviation electronic equipment racks 110A-N includes one or more heat generating aviation electronic equipments. Exemplary aviation electronic equipments include equipments used for navigation of the aircraft 100, control of other equipments in the aircraft 100 and the like. For example, the aviation electronic equipments can also be arranged in the form of stacks or the aviation electronic equipments can be placed independently. Further, the aviation electronic equipments in the aviation electronic equipment racks 110A-N are cooled by forced and/or natural convection.



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stats Patent Info
Application #
US 20120298337 A1
Publish Date
11/29/2012
Document #
13477080
File Date
05/22/2012
USPTO Class
16510426
Other USPTO Classes
16510434, 165185
International Class
/
Drawings
5



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