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US-20260129805-A1 - COOLING SYSTEM

US20260129805A1US 20260129805 A1US20260129805 A1US 20260129805A1US-20260129805-A1

Abstract

The present invention relates to at least one body ( 2 ) in an air and/or space vehicle; at least one avionics equipment ( 3 ) positioned on the body ( 2 ); at least one inlet port ( 4 ) located on the body ( 2 ); a coolant (A) transmitted into the body through the inlet port ( 4 ); at least one transmission line ( 5 ) removably mounted on the inlet port ( 4 ), thus enabling the transmission of coolant (A) into the body ( 2 ) for cooling the avionics equipment ( 3 ); at least one void ( 6 ) forming the internal volume of the body ( 2 ); at least one hole ( 7 ) on the body ( 2 ), which allows the coolant (A) to be passed through the void ( 6 ) to the avionics equipment ( 3 ), thus allowing a temperature value of the avionics equipment ( 3 ) to be decreased.

Inventors

  • Durukan TAMKAN
  • Hamdi Alpay Kucuker

Assignees

  • TUSAS- TURK HAVACILIK VE UZAY SANAYII ANONIM SIRKETI

Dates

Publication Date
20260507
Application Date
20230925
Priority Date
20220929

Claims (15)

  1. 1 . A cooling system ( 1 ) comprising at least one body ( 2 ) in an air and/or space vehicle; at least one avionics equipment ( 3 ) positioned on the body ( 2 ); at least one inlet port ( 4 ) located on the body ( 2 ); a coolant (A) transmitted into the body through the inlet port ( 4 ); at least one transmission line ( 5 ) removably mounted on the inlet port ( 4 ), thus enabling the transmission of coolant (A) into the body ( 2 ) for cooling the avionics equipment ( 3 ); at least one void ( 6 ) forming the internal volume of the body ( 2 ); at least one hole ( 7 ) on the body ( 2 ), which allows the coolant (A) to be passed through the void ( 6 ) and transmitted to the avionics equipment ( 3 ), thus allowing a temperature value of the avionics equipment ( 3 ) to be decreased, characterized by a plurality of protrusions ( 8 ) in the body ( 2 ), which extend in the void ( 6 ) in a geometric form predetermined by the user, thus enabling the coolant (A) that is transmitted through the inlet port ( 4 ) to the void ( 6 ) to be directed; at least one channel ( 9 ) located in the void ( 6 ) so as to remain between the protrusions ( 8 ) and extend in the same direction as the protrusions ( 8 ); at least one protrusion ( 8 ) that allows the coolant (A) transmitted to the void ( 6 ) to be directed to the channel ( 9 ) and transmitted to the avionics equipment ( 3 ) through the holes ( 7 ) that are located on the body ( 2 ) in line with the channel ( 9 ).
  2. 2 . A cooling system ( 1 ) according to claim 1 , wherein the protrusion ( 8 ) in a form predetermined by the user, which extends towards the inlet port ( 4 ) so as to be opposite the inlet port ( 4 ).
  3. 3 . A cooling system ( 1 ) according to claim 4 , wherein a plurality of carrier plates ( 10 ) positioned opposite each other on the body ( 2 ) with avionics equipment ( 3 ) therebetween, and allowing the avionics equipment ( 3 ) to be positioned and carried on the body ( 2 ).
  4. 4 . A cooling system ( 1 ) according to claim 3 , wherein a plurality of avionics equipment ( 3 ) located on the carrier plate ( 10 ), in line with the protrusion ( 8 ), each at a distance predetermined by the user from the other.
  5. 5 . A cooling system ( 1 ) according to claim 3 , wherein at least one groove ( 11 ) which is located on the carrier plate ( 10 ), opposite the inlet port ( 4 ), and through which the coolant (A) is transmitted; at least one transmission conduit ( 12 ) removably inserted inside the groove ( 11 ) and inlet port ( 4 ), thus allowing the fluid transmitted by the transmission line ( 5 ) to be transmitted into the body ( 2 ) without loss.
  6. 6 . A cooling system ( 1 ) according to claim 1 , wherein at least one upper cover panel ( 13 ) located on the body ( 2 ), integral with the body ( 2 ); at least one gap (G) between two avionics equipment ( 3 ); a plurality of holes ( 7 ) located consecutively on the upper cover panel ( 13 ) in line with the channels ( 9 ), each at a predetermined distance from the other, thereby allowing the coolant (A) to be transmitted to the gap (G).
  7. 7 . A cooling system ( 1 ) according to claim 6 , wherein a space (V) located between the avionics equipment ( 3 ) and the upper cover panel ( 13 ) at a distance predetermined by the user; the upper cover panel ( 13 ) which allows the heat generated on the avionics equipment ( 3 ) to be removed from the avionics equipment ( 3 ) by conduction only through the carrier plates ( 10 ), thanks to the space (V).
  8. 8 . A cooling system ( 1 ) according to claim 1 , wherein a plurality of lateral surfaces(S) on the avionics equipment ( 3 ); a plurality of fins ( 14 ) located on the lateral surfaces (S) so as to almost completely surround the lateral surfaces(S) and to be in line with the holes ( 7 ), thereby enabling the coolant (A), which is transmitted to the avionics equipment ( 3 ) through the holes ( 7 ), to be moved longitudinally along the lateral surfaces(S).
  9. 9 . A cooling system ( 1 ) according to claim 1 , wherein a lower surface (U) located at a lower part of the body ( 2 ); at least one lower cover panel ( 15 ) located on the lower surface (U) of the body ( 2 ) so as to almost completely surround the lower surface (U) and to be integral with the body ( 2 ).
  10. 10 . A cooling system ( 1 ) according to claim 3 , wherein the body ( 2 ) which is mounted removably on the carrier plates ( 10 ), with the edges thereof remaining at least partially in the carrier plates ( 10 ).
  11. 11 . A cooling system ( 1 ) according to claim 9 , wherein the body ( 2 ), which is a honeycomb core and located between the lower cover panel ( 15 ) and the upper cover panel ( 13 ).
  12. 12 . A cooling system ( 1 ) according to claim 1 , wherein the body ( 2 ) produced by an additive manufacturing method, in a geometry predetermined by the user.
  13. 13 . A cooling system ( 1 ) according to claim 3 , wherein the carrier plate ( 10 ) made of a metal material.
  14. 14 . A cooling system ( 1 ) according to claim 1 , wherein the avionics equipment ( 3 ) provided on an air and/or space vehicle.
  15. 15 . A cooling system ( 1 ) according to claim 1 , wherein the transmission line ( 5 ) that allows the coolant (A) transmitted by an air conditioning system of the air and/or space vehicle to be transmitted into the body ( 2 ).

Description

This invention relates to a cooling system developed to reduce temperatures of equipment in air and/or space vehicles. Most equipment requires active cooling. For this reason, both racks and cooling lines are used in an area to position the equipment. Cooling lines occupy space in the area and increase costs in production and assembly processes. As the cooling lines are closer to the equipment, cooling efficiency increases; however, since they use a predetermined space for the equipment and equipment carrier elements, it causes heavier carriers to be designed. U.S. Pat. No. 9,526,190B2, which is included in the known-state of the art, discloses a system in which avionics rack modules enable the transportation of multiple electronic equipment arranged side by side. Cooling air is moved through avionics equipment to cool equipment elements. Each piece of avionics equipment is also mounted to the rack module via a support chair as described above. According to said document, the rack modules are mounted on the channels. Additionally, there are holes on the structure in the form of a seat to provide cooling. Therefore, air passage is provided between the air flow channel and the equipment. JP3644176B2, which is included in the known-state of the art, discloses a panel with an increased strength, which is used for assembly purposes in air and/or space vehicles and also allows pipes to be passed in order to carry out heat transfer. Thanks to a cooling system according to the present invention, a lighter cooling system with more effective cooling is provided. Another object of the invention is to provide the strength required for more effective cooling and transportation of avionics equipment by using the structural properties of the plate itself. A further object of the invention is to increase the static strength in transporting avionics equipment, thanks to the structural features of the plate in the cooling system. The cooling system realized to achieve the object of the invention, which is defined in the first claim and other claims dependent thereon, comprises at least one body positioned in an air and/or space vehicle; at least one avionics equipment positioned on the body; at least one inlet port located in the body to provide access to the internal volume of the body; at least one transmission line removably mounted on the inlet port and placed almost completely at the inlet port for transmitting a coolant, i.e. cooling air, to the internal volume of the body for the purpose of cooling the avionics equipment positioned on the body; at least one void that forms the internal volume of the body so as to fill the internal volume of the body; at least one hole positioned on the body, which allows the coolant transmitted to the void by the transmission line to pass through the void and contact the avionics equipment in order to transmit the coolant to the avionics equipment on the body and to cool the heated avionics equipment by reducing a temperature to a value predetermined by the user. The cooling system according to the invention comprises a plurality of protrusions produced in a user-predetermined geometric form in the void, next to the inlet port, from the inner surface of the body opposite the inlet port, wherein the protrusions extend towards the inner surfaces of the body and the inlet opening to fill the void, thus allowing the coolant transmitted through the inlet port to the void to be directed in the void in a direction predetermined by the user; at least one channel formed in the void, between at least two protrusions; the protrusion enabling the coolant transmitted from the inlet port to the void to be transmitted to the channels located in line with the holes without being distributed randomly within the void, thus allowing the coolant filled into the channels to be transmitted to the avionics equipment through the holes and allowing the avionics equipment to be cooled more effectively. In an embodiment of the invention, the cooling system comprises the protrusion in a geometry predetermined by the user, which extends from the inner surface of the body towards the inlet port so as to be opposite thereto, wherein said inner surface of the body is opposite to the inlet port and in contact with the void. In an embodiment of the invention, the cooling system comprises a plurality of carrier plates positioned opposite each other on the body, with at least one avionics equipment therebetween, wherein the avionics equipment is mounted removably on the carrier plates, thus allowing the avionics equipment to be carried on the body. In an embodiment of the invention, the cooling system comprises a plurality of avionics equipment each located in the body, which are positioned on two carrier plates to extend in line with the protrusion. In an embodiment of the invention, the cooling system comprises at least one groove located on the carrier plate placed on the body, so as to be opposite and in contact wit