Cooling system for center wing fuel tank of aircraft

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

The invention relates to a cooling system for a fuel tank of an aircraft. The cooling system includes a temperature sensor, a cooling system, and a control module. The temperature sensor detects a fuel temperature within the fuel tank. The cooling system maintains the fuel temperature below a control temperature. The phase change cooling system includes a heat exchanger. A cooling fluid flows through the heat exchanger and is in thermal communication with a surface of the fuel tank. The control module is in signal communication with the temperature sensor and the cooling system. The control module includes control logic for monitoring the temperature sensor, determining if the fuel temperature is above the control temperature, and generating an activation signal. 本公开涉及种用于飞行器的中央机翼油箱的冷却系统。该冷却系统包括温度传感器、冷却系统和控制模块。所述温度传感器检测所述燃料箱内的燃料温度。所述冷却系统维持所述燃料温度低于控制温度。所述相变冷却系统包括热交换器。冷却流体流过所述热交换器并且与所述燃料箱的表面热连通。所述控制模块与所述温度传感器和所述冷却系统信号通信。所述控制模块包括控制逻辑，用于监控所述温度传感器、确定所述燃料温度是否高于所述控制温度、并且产生激活信号。