Electrically powered rotorcraft capable of autorotative landing
AssigneeSiFly Aviation, Inc.
InventorsBrian L. Hinman, Jeffrey G. Bernstein
Life of this patent
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Abstract
A method of operating an electrically powered rotorcraft of the type having a fuselage and a set of N rotors driven by a set of electric motors and coupled to the fuselage, N≥4, under a failure condition preventing ordinary operation of the rotorcraft. The method includes entering a failsafe mode of operation wherein autorotation of at least four of the rotors is enabled. The method also includes using electrical braking associated with a selected group of the rotors to control yaw of the rotorcraft.
Claims22
A method of operating an electrically powered rotorcraft having a fuselage and a set of N rotors driven by a set of electric motors and coupled to the fuselage, N≥4, as well as a system controller configured to control operation of the set of N rotors the method operating under a failure condition preventing ordinary operation of the rotorcraft and comprising:
- entering, by the system controller, into a failsafe mode of operation wherein autorotation of at least four of the rotors is enabled;
- controlling, by the system controller, (a) collective pitch of blades of each rotor in the set of rotors to support autorotation and (b) collective pitch of blades of each rotor in the set relative to collective pitch of blades of each other rotor in the set to affect pitch and roll of the rotorcraft;
- and
- causing, by the system controller, use of electrical braking associated with a selected group of the rotors to control yaw of the rotorcraft.
An electrically powered rotorcraft having a fuselage and a set of N rotors driven by a set of electric motors and coupled to the fuselage, N>4,
- wherein a controller is configured to operate the rotorcraft under a failure condition preventing ordinary operation of the rotorcraft, by:
- causing the rotorcraft to enter a failsafe mode of operation wherein autorotation of at least four of the rotors is enabled;
- controlling, by the system controller, (a) collective pitch of blades of each rotor in the set of rotors to support autorotation and (b) collective pitch of blades of each rotor in the set relative to collective pitch of blades of each other rotor in the set to affect pitch and roll of the rotorcraft;
- and
- causing the rotorcraft to use electrical braking associated with a selected group of the rotors to control yaw of the rotorcraft.
A method of operating an electrically powered rotorcraft having a fuselage and a set of N rotors driven by a set of electric motors and coupled to the fuselage, N≥4, as well as a system controller configured to control operation of the set of N rotors, the rotorcraft being devoid of means of propulsion by other than the set of rotors, each of the rotors having an axis of rotation that is fixed relative to the fuselage, the method operating under a failure condition preventing ordinary operation of the rotorcraft and comprising:
- entering, by the system controller, into a failsafe mode of operation wherein autorotation of at least four of the rotors is enabled;
- controlling, by the system controller, (a) collective pitch of blades of each rotor in the set of rotors to support autorotation and (b) collective pitch of blades of each rotor in the set relative to collective pitch of blades of each other rotor in the set to affect pitch and roll of the rotorcraft;
- and
- causing, by the system controller, use of electrical braking associated with a selected group of the rotors to control yaw of the rotorcraft.
Dependencies are inferred from the claim text.