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

Abstract

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.

1 . An apparatus for radiative heat transfer augmentation for aviation electronic equipments cooled by convection, comprising:
 a first heat dissipation device to dissipate heat from the aviation electronic equipments housed in an aviation electronic equipment rack using forced convection; and   a second heat dissipation device strategically disposed with respect to aircraft skin and configured to maximize radiative view factor to enhance heat dissipation from the aviation electronic equipments by radiation and natural convection.   
     
     
         2 . The apparatus of  claim 1 , wherein the first heat dissipation device dissipates heat from the aviation electronic equipments using air stream capable of causing forced ventilation. 
     
     
         3 . The apparatus of  claim 1 , wherein the first heat dissipation device cools the aviation electronic equipments by natural and forced convection in thermal contact with one or more hot spots of the aviation electronic equipments. 
     
     
         4 . The apparatus of  claim 1 , wherein the second heat dissipation device is an external thermal radiator. 
     
     
         5 . The apparatus of  claim 4 , wherein the external thermal radiator comprises a heat collector that is coupled to the one or more heat spots of the aviation electronic equipments using thermal conductors. 
     
     
         6 . The apparatus of  claim 5 , wherein the thermal conductors are heat pipes. 
     
     
         7 . The apparatus of  claim 5 , wherein the heat pipes have high thermal conductivity in the longitudinal direction. 
     
     
         8 . The apparatus of  claim 1 , wherein the second heat dissipation device is sized to complement the cooling provided by the first heat dissipation device should the forced convection be lost and wherein the second heat dissipation device is disposed with respect to the aircraft skin to maximize heat dissipation by radiation. 
     
     
         9 . A method of radiative heat transfer augmentation for aviation electronic equipments cooled by forced and/or natural convection, comprising:
 dissipating heat from the aviation electronic equipments housed in an aviation electronic equipment rack by forced convection using a first heat dissipation device; and   enhancing heat dissipation from the aviation electronic equipments by radiation and natural convection using a second heat dissipation device, wherein the second heat dissipation device is strategically disposed with respect to aircraft skin and configured to maximize radiative view factor.   
     
     
         10 . The method of  claim 9 , wherein, in dissipating heat from the aviation electronic equipments, the first heat dissipation device dissipates heat from the aviation electronic equipments using air stream capable of causing forced ventilation. 
     
     
         11 . The method of  claim 9 , wherein, in dissipating heat from the aviation electronic equipments, the first heat dissipation device cools the aviation electronic equipments by natural and forced convection in thermal contact with one or more hot spots of the aviation electronic equipments. 
     
     
         12 . The method of  claim 9 , wherein the second heat dissipation device is an external thermal radiator. 
     
     
         13 . The method of  claim 12 , wherein the external thermal radiator comprises a heat collector that is coupled to the one or more hot spots of the aviation electronic equipments using thermal conductors. 
     
     
         14 . The method of  claim 13 , wherein the thermal conductors are heat pipes. 
     
     
         15 . The method of  claim 13 , wherein the heat pipes have high thermal conductivity in the longitudinal direction. 
     
     
         16 . The method of  claim 9 , wherein the second heat dissipation device is sized to complement the cooling provided by the first heat dissipation device should the forced convection be lost and wherein the second heat dissipation device is disposed with respect to the aircraft skin to maximize heat dissipation by radiation.