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US 10,894,599 B1Granted
Retractable VTOL rotor systems and methods
AssigneeUav Factory Sia
InventorKonstantins Popiks
Life of this patent
Estimating the term…
Abstract
A hybrid multi-rotor aircraft, includes a plurality of vertical propulsion rotors and at least one forward propulsion rotor. The aircraft also includes a rotor compartment within for each of the vertical propulsion rotors such that a vertical propulsion rotor may be stowed within its respective rotor compartment. A deployable rotor-compartment cover for each rotor compartment is provided and may be moved to an open state to allow the vertical propulsion rotors to be deployed and moved to a closed state to cover their respective vertical propulsion rotors when the vertical propulsion rotors or in a closed state.
Claims16
A hybrid multi-rotor aircraft, comprising:
- a plurality of vertical propulsion rotors;
- a forward propulsion rotor;
- and
- a rotor compartment for each of the plurality of vertical propulsion rotors, the rotor compartments disposed within a respective body portion of the hybrid multi-rotor aircraft, each rotor compartment configured to stow its respective vertical propulsion rotor;
- a deployable rotor-compartment cover for each rotor compartment, the deployable rotor-compartment covers each configured to be moved to an open state to allow the vertical propulsion rotors to be deployed for vertical flight modes and to be moved to a closed state to cover its respective vertical propulsion rotor for forward flight operations;
- a motor coupled to at least one of the deployable rotor-compartment covers by a linkage, wherein operation of the motor moves the linkage to open and close the at least one of the deployable rotor-compartment covers;
- wherein the linkage comprises:
- an elongate rod having a proximal and a distal end, the proximal end coupled to a shaft of the motor;
- an actuating arm having a base portion coupled to the distal end of the elongate rod and an extension portion coupled to its respective deployable rotor-compartment cover.
6 more elements
A hybrid multi-rotor aircraft, comprising;
- a plurality of vertical propulsion rotors;
- a forward propulsion rotor;
- and
- a rotor compartment for each of the plurality of vertical propulsion rotors, the rotor compartments disposed within a respective body portion of the hybrid multi-rotor aircraft, each rotor compartment configured to stow its respective vertical propulsion rotor;
- a deployable rotor-compartment cover for each rotor compartment, the deployable rotor-compartment covers each comprising structure configured to be moved upward from its respective body portion and in an aft direction to an open state to allow the vertical propulsion rotors to be deployed for vertical flight modes and to be moved forward and downward toward its respective body portion to a closed state to cover its respective vertical propulsion rotor for forward flight operations;
- a linkage, wherein the linkage comprises:
- an elongate rod having a proximal and a distal end, the proximal end coupled to a shaft of the motor;
- an actuating arm having a base portion coupled to the distal end of the elongate rod and an extension portion coupled to its respective deployable rotor-compartment cover.
5 more elements
A method for hybrid multi-rotor aircraft operation, comprising:
- receiving a signal to operate the hybrid multi-rotor aircraft in a vertical flight mode;
- in response to the signal to operate the hybrid multi-rotor aircraft in a vertical flight mode, opening a plurality of deployable rotor-compartment covers to permit operation of a plurality of vertical propulsion rotors, wherein opening a plurality of deployable rotor-compartment covers, comprises moving each of the plurality of deployable rotor-compartment covers upward from its respective body portion and in an aft direction to an open position to allow the vertical propulsion rotors to be deployed for vertical flight modes;
- causing rotation of the plurality of vertical propulsion rotors to operate the aircraft in a vertical flight mode;
- receiving a signal to operate the hybrid multi-rotor aircraft in a forward flight mode;
- and
- in response to the signal to operate the hybrid multi-rotor aircraft in a forward flight mode, closing the plurality of deployable rotor-compartment covers to enclose the plurality of vertical propulsion rotors within their respective rotor compartments, wherein closing the plurality of deployable rotor-compartment covers comprises moving each of the plurality of deployable rotor-compartment covers from the open position forward and downward toward its respective body portion to a closed position to cover its respective vertical propulsion rotor for forward flight operations;
- a linkage, wherein the linkage comprises:
- an elongate rod having a proximal and a distal end, the proximal end coupled to a shaft of the motor;
- an actuating arm having a base portion coupled to the distal end of the elongate rod and an extension portion coupled to its respective deployable rotor-compartment cover.
6 more elements
Dependencies are inferred from the claim text.