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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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
LanguageEnglish
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
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Summary: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.
Bibliography:Application Number: EP20150197436