FUEL TANK OF AN AIRCRAFT AND COOLING SYSTEM

• Main Authors: JOJIC, IVANA, BELIÉRES, JEAN-PHILIPPE A, ADKINS II, DAVID A, MULVANEY, PATRICK J, THORNTON, MARK M, GRAHAM, RODNEY N, MORAVEC, BRADFORD A, OLSON, ERIC C, GRIM, ALAN
• Format: Patent
• Language: English; French; German
• Published: 08.06.2016
• Subjects: AIRCRAFT; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT; AVIATION; COSMONAUTICS; EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLYING SUITS; PARACHUTES; PERFORMING OPERATIONS; TRANSPORTING

A cooling system for a fuel tank (24) of an aircraft includes a temperature sensor (140), a cooling system (70), and a control module (72). The temperature sensor (140) detects a fuel temperature within the fuel tank. The cooling system (70) maintains the fuel temperature below a control temperature. The phase change cooling system (92) includes a heat exchanger (86). A cooling fluid (94) flows through the heat exchanger (86) and is in thermal communication with a surface (50) of the fuel tank (24). The control module (72) is in signal communication with the temperature sensor (140) and the cooling system (70). The control module (72) includes control logic for monitoring the temperature sensor (140), determining if the fuel temperature is above the control temperature, and generating an activation signal.