Aircraft de-icing using heat from an electromechanical actuator

摘要

An aircraft de-icing system 300 utilises heat generated from an electromechanical actuator 302. Heat from the electromechanical actuator is received by an electromechanical actuator heat sink 304. A heat transportation 306 device is operable to transport heat from the electromechanical actuator heat sink 304 to a heat distribution element 308 and then distribute it to an aerodynamic surface 310. A thermal capacitor 312 is able to store heat and provides inertia against temperature fluctuations. A controller module 314 comprises a processor module 316 and a memory module 318 and provides a means to control operation of the de-icing system.