AN ELECTRICAL DRIVE SYSTEM FOR AN ELECTRICALLY DRIVEN AIRCRAFT

An electrical drive system for an electrically driven aircraft comprising:a power source (130);at least one motor (110);a main motor controller (222A) using at least one sensor (115) for controlling said at least one motor based on parameters measured with said sensors; a redundant motor controller...

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Bibliographische Detailangaben
1. Verfasser:	DEMONT, Sébastien
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AIRCRAFT ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSIONTRANSMISSIONS IN AIRCRAFT AVIATION CONTROL OR REGULATING SYSTEMS IN GENERAL CONTROLLING COSMONAUTICS EQUIPMENT FOR FITTING IN OR TO AIRCRAFT FLYING SUITS FUNCTIONAL ELEMENTS OF SUCH SYSTEMS MONITORING OR TESTING ARRANGEMENTS FOR SUCH SYSTEMS ORELEMENTS PARACHUTES PERFORMING OPERATIONS PHYSICS REGULATING SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES TRANSPORTING
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Beschreibung
Zusammenfassung:	An electrical drive system for an electrically driven aircraft comprising:a power source (130);at least one motor (110);a main motor controller (222A) using at least one sensor (115) for controlling said at least one motor based on parameters measured with said sensors; a redundant motor controller (222B) for controlling said at least one motor, said redundant motor controller being sensorless. Cette invention concerne un système de commande électrique pour un aéronef à commande électrique, comprenant : une source d'alimentation (130); au moins un moteur (110); un dispositif principal de commande de moteur (222A) mettant en œuvre au moins un capteur (115) pour commander ledit/lesdits moteur(s) sur la base de paramètres mesurés avec lesdits capteurs; un dispositif de commande redondant de moteur (222B) pour commander ledit/lesdits moteur(s), ledit dispositif de commande redondant de moteur étant sans capteur.