Patent ID: 6611659
Filing Date: 2003-08-26
Classification: B64C,B64D,F24D,Y02B,Y02T

Abstract:
An aircraft floor heating panel comprising a heat resistant fiber composite core structure (1B) for providing the structural strength of an aircraft floor panel, an outer first section (1A) including an electrical heater (4) and a heat distributing metal plate (2) forming a walk-on surface, a first adhesive bonding layer (3) between said electrical heater (4) and said heat distributing metal plate (2), a second adhesive bond (5) between said electrical heater (4) and said fiber composite core structure (1B), an outer second section (1C) including a heat insulating layer (11, 12) bonded to said fiber composite core structure (1B) opposite said outer first section (1A) so that said fiber composite core structure is sandwiched between said outer first and second sections, cut-out means in said composite core structure below said heat distributing metal plate, a temperature sensor (31) embedded in said cut-out means in heat sensing contact with said heat distributing metal plate, said temperature sensor being electrically connected to a control and power supply unit (29) in said aircraft for switching a power supply on and off to maintain normal operating temperatures, and fire hazard protection means electrically connected in series with said electrical heater for interrupting an electrical power supply to said electrical heater thereby overriding any control by said temperature sensor in response to temperatures exceeding said normal operating temperatures.