Thermal dissipation device for space equipment, in particular for satellite

The device has a dissipating panel (11) with inner and outer shells (211, 212) made of composite structure having organic resin and carbon fibers, where the organic resin is charged of carbon nanotubes. The structure is formed by alternating succession of layers having sets of carbon fibers arranged...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	VITUPIER, YANN, LALANDE, HUBERT, LUTZ, MARTINE, MONTREDON, FLORENCE, CHAIX, ALAIN
Format:	Patent
Sprache:	eng ; pol
Schlagworte:	AIRCRAFT AVIATION BLASTING COSMONAUTICS DETAILS OF HEAT-EXCHANGE AND HEAT-TRANSFER APPARATUS, OFGENERAL APPLICATION HEAT EXCHANGE IN GENERAL HEAT-EXCHANGE APPARATUS, NOT PROVIDED FOR IN ANOTHER SUBCLASS,IN WHICH THE HEAT-EXCHANGE MEDIA DO NOT COME INTO DIRECT CONTACT HEATING LIGHTING MANUFACTURE OR TREATMENT OF NANOSTRUCTURES MEASUREMENT OR ANALYSIS OF NANOSTRUCTURES MECHANICAL ENGINEERING NANOTECHNOLOGY PERFORMING OPERATIONS SPECIFIC USES OR APPLICATIONS OF NANOSTRUCTURES TRANSPORTING VEHICLES OR EQUIPMENT THEREFOR WEAPONS
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Beschreibung
Zusammenfassung:	The device has a dissipating panel (11) with inner and outer shells (211, 212) made of composite structure having organic resin and carbon fibers, where the organic resin is charged of carbon nanotubes. The structure is formed by alternating succession of layers having sets of carbon fibers arranged along alignments, respectively, where one alignment is perpendicular to another alignment. The shells are assembled at a set of tubular heat pipes (21) and connected via structure elements (22) formed by a honeycomb configuration of aluminum tubes or formed by conductive foam.