Aircraft light

An aircraft light comprises a housing (24), at least one light source (32) to be cooled, the at least one light source (32) being arranged in the housing (24), a heat sink element (26) thermally coupled to the at least one light source (32) and defining a cooling surface (36) exposable to a cooling...

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Bibliographische Detailangaben
1. Verfasser:	HESSLING, ANDRE
Format:	Patent
Sprache:	eng ; fre ; ger
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION BLASTING COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS FUNCTIONAL FEATURES OR DETAILS OF LIGHTING DEVICES OR SYSTEMSTHEREOF HEATING INDEXING SCHEME ASSOCIATED WITH SUBCLASSES F21K, F21L, F21Sand F21V, RELATING TO THEFORM OR THE KIND OF THE LIGHT SOURCES OR OF THE COLOUR OF THELIGHT EMITTED INDEXING SCHEME ASSOCIATED WITH SUBCLASSES F21K, F21L, F21Sand F21V, RELATING TO USESOR APPLICATIONS OF LIGHTING DEVICES OR SYSTEMS LAND VEHICLES FOR TRAVELLING OTHERWISE THAN ON RAILS LIGHTING MECHANICAL ENGINEERING MOTOR VEHICLES PARACHUTES PERFORMING OPERATIONS STRUCTURAL COMBINATIONS OF LIGHTING DEVICES WITH OTHERARTICLES, NOT OTHERWISE PROVIDED FOR TRAILERS TRANSPORTING WEAPONS
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Beschreibung
Zusammenfassung:	An aircraft light comprises a housing (24), at least one light source (32) to be cooled, the at least one light source (32) being arranged in the housing (24), a heat sink element (26) thermally coupled to the at least one light source (32) and defining a cooling surface (36) exposable to a cooling airstream (52) for the cooling airstream (52) to flow along the cooling surface (36) in a flow direction. The cooling surface (36) extends between upstream and downstream end portions (40,42) spaced apart in the flow direction and means for generating a pressure difference between the upstream and downstream end portions (40,42) of the cooling surface. Due to the pressure difference, a cooling airstream (52) flowing along the cooling surface (36) is created.