Electric de-icing device for turbojet engine nacelle

The invention relates to an electric de-icing/anti-icing device for a turbojet engine/turbo-prop nacelle element for an element of an aircraft to be protected from ice, comprising: - a heating assembly comprising two heating stages positioned in the nacelle element to be protected from ice; - an ele...

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Bibliographische Detailangaben
Hauptverfasser:	MAALIOUNE HAKIM, PEREIRA DAVID, COAT-LENZOTTI CAROLINE
Format:	Patent
Sprache:	eng
Schlagworte:	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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Beschreibung
Zusammenfassung:	The invention relates to an electric de-icing/anti-icing device for a turbojet engine/turbo-prop nacelle element for an element of an aircraft to be protected from ice, comprising: - a heating assembly comprising two heating stages positioned in the nacelle element to be protected from ice; - an electricity supply circuit delivering a primary voltage to the first stage of the heating assembly, and comprising: an electricity source; a de-icing/anti-icing circuit (13) connected to the heating assembly and supplied with voltage by said electricity supply source. The de-icing/anti-icing device according to the invention is remarkable in that it further comprises means (25, 29) for delivering a complementary voltage supplying the second stage of the heating assembly.