Aerodynamic rotor blade configurations

    公开(公告)号:US12122503B1

    公开(公告)日:2024-10-22

    申请号:US17948545

    申请日:2022-09-20

    Applicant: Wisk Aero LLC

    CPC classification number: B64C11/04 B64C11/46 B64C27/021 B64C27/22

    Abstract: Embodiments of the invention are directed to systems and methods for reducing drag on an aircraft. The aircraft can include at least one propulsion system with rotor blades configured to reduce aerodynamic drag when the propulsion system is deactivated. To reduce the amount of drag, the rotor blades can be locked into an aerodynamic position, and prevented from passively spinning. Additionally, the rotor blades can be configured to have angular positions that reduce drag. For example, the rotor blades as a group may be configured to generally point toward and/or away from an airflow current.

    Rotorcraft
    3.
    发明授权

    公开(公告)号:US11926443B2

    公开(公告)日:2024-03-12

    申请号:US18035443

    申请日:2021-11-29

    Inventor: Efraim Kastiel

    Abstract: Rotorcraft including a fuselage, at least three rotor system arms, a forward propulsion unit for providing forward propulsion to the rotorcraft and a flight control system. Each rotor system arm has a rotor system including a mast having at least two rotor blades and an electric rotor motor coupled to the mast for driving the mast whereupon the rotor blades act as a rotating rotor disc. Each rotor system has an individually controllable collective rotor blade pitch. At least one rotor system has a controllable cyclic rotor blade pitch. The flight control system controls the at least three electric rotor motors, the collective rotor blade pitch of each rotor system, the cyclic rotor blade pitch of the at least one rotor system and the forward propulsion unit in response to an input control indicating a desired maneuver to operate the rotorcraft for takeoff, flight and landing.

    Personal aircraft
    7.
    发明授权

    公开(公告)号:US09845150B2

    公开(公告)日:2017-12-19

    申请号:US13764697

    申请日:2013-02-11

    Inventor: Ilan Kroo

    Abstract: A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with a front and rear wing, permits a balancing of the center of lift with the center of gravity for both vertical and horizontal flight. This wing and multiple rotor system has the ability to tolerate a relatively large variation of the payload weight for hover, transition, or cruise flight while also providing vertical thrust redundancy. The propulsion system uses multiple lift rotors and forward thrust propellers of a small enough size to be shielded from potential blade strike and provide increased perceived and real safety to the passengers. Using multiple independent rotors provides redundancy and the elimination of single point failure modes that can make the vehicle non-operable in flight.

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