FUEL TANK OF AN AIRCRAFT AND COOLING SYSTEM

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...

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Bibliographische Detailangaben
Hauptverfasser:	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
Sprache:	eng ; fre ; ger
Schlagworte:	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
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Beschreibung
Zusammenfassung:	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.