Cooling system

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).