Patent ID: 8991763
Filing Date: 2015-03-31
Classification: B64D

Abstract:
1. A de-icing system comprising: a leading edge of an aircraft wing or air intake lip of an aircraft engine; a plurality of infrared emitting members arranged inside a cavity defined by a front partition and said leading edge or said lip; a plurality of supports that extend between an inner wall of the air intake lip and the front partition and distributed evenly on an inner circumference of the air intake lip, wherein the plurality of infrared emitting members are fixed to the plurality of supports and are distanced from the inner wall of the air intake lip; power supply means for said emitters; and control means for adjusting a voltage, intensity and duration of said power supply means, so as to regulate heating energy radiated toward an inner wall of said leading edge of said lip, wherein said front partition separates said cavity from an inner area, thus functioning as both load-carrying structure and for thermal insulation of the cavity relative to the inner area, wherein said emitters are made of ceramic and have a radiated power/weight ratio of 500 W for 100 g, an emissivity of 97% at 800° C. over a spectrum between 1.5 μm and 10 μm, a surface energy greater than 70 kW per square meter, and an efficiency greater than 95%.