An aircraft includes at least one propulsion engine, coupled to a fuselage, and configured to provide forward thrust to propel the aircraft along a first vector during forward flight. Each of at least two of multiple rotors coupled to the fuselage is coupled to a motor configured to supply power to that rotor and/or to draw power from that rotor. At least two of the rotors are configured to operate during forward flight to provide at least some lift to the aircraft along a second vector. A flight control system is configured to control the rotors that are configured to operate during forward flight in a power managed regime in which a net electrical power, consisting of the sum of the power being supplied to or drawn from each rotor by its motor, is maintained within a range determined by a feedback control system of the flight control system.
Hybrid gyrodyne aircraft employing a managed autorotation flight control system
14.08.2018
Patent
Elektronische Ressource
Englisch
HYBRID GYRODYNE AIRCRAFT EMPLOYING A MANAGED AUTOROTATION FLIGHT CONTROL SYSTEM
Europäisches Patentamt | 2016
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