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    ENHANCED NET PITCHING MOMENT MULTI-WING VTOL COMPACT PERSONAL AIRCRAFT
    163.
    发明申请
    ENHANCED NET PITCHING MOMENT MULTI-WING VTOL COMPACT PERSONAL AIRCRAFT 审中-公开

    公开(公告)号：US20180093765A1

    公开(公告)日：2018-04-05

    申请号：US15683870

    申请日：2017-08-23

    Applicant: BRENDAN GRAHAM

    Inventor： BRENDAN GRAHAM

    IPC: B64C29/02 ,  B64C39/08 ,  B64C1/28 ,  B64C27/26 ,  G05D1/08 ,  G05D1/10

    CPC classification number: B64C29/02 ,  B64C1/28 ,  B64C27/26 ,  B64C39/08 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  G05D1/0858 ,  G05D1/102

    Abstract: This disclosure describes a multi-wing manned or unmanned compact personal vertical takeoff and landing aircraft, comprising the integration of: a plurality of parallel wings forming a boxed planform multi-wing assembly with no dynamic airfoil control surfaces, statically affixed to a co-planar adjacent counter-rotating quad-rotor air propulsion system; and a fuselage free to rotate under servo control about an axial shaft, permitting dynamic orientation manipulation. The vehicle described herein achieves: high maneuverability and attitude orientation control incumbent upon the ratio of power delivered to the quad-rotors; area constrained and enhanced wind gust insensitive VTOL capability; high fuel efficient non-hover aerodynamic flight capability; high external field-of-view optical visibility from the fuselage interior; convenient fuselage interior accessibility; and enhanced net pitching moment of inertia about the multi-wing assembly net aerodynamic center, permitting rapid transitioning to and from aerodynamic flight orientation.

    Method and Device for Increasing the Stability and Maneuverability of Unmanned Aerial Vehicles (UAV) using a Gyroscopic Effect
    167.
    发明申请
    Method and Device for Increasing the Stability and Maneuverability of Unmanned Aerial Vehicles (UAV) using a Gyroscopic Effect 审中-公开

    公开(公告)号：US20180029695A1

    公开(公告)日：2018-02-01

    申请号：US15551037

    申请日：2016-02-23

    Applicant: Arif Mir Jalal ogly PASHAYEV ,  Toghrul Isa ogly KARIMLI

    Inventor： Arif Mir Jalal ogly PASHAYEV ,  Toghrul Isa ogly KARIMLI

    IPC: B64C17/06 ,  B64C39/02

    CPC classification number: B64C17/06 ,  B64C39/024 ,  B64C2201/104

    Abstract: Proposed method and device could be applied as controlling system facilitating the maneuverability and stabilization parameters of UAV, as well as various flight objects and small satellites. The aim of the invention is to reduce the occurrences of imbalances of UAV in strong wind or atmospheric turbulence situations and simultaneously rehabilitation of maneuverability and stabilization parameters without increasing flight speed.Thus, in order to upgrade the above mentioned parameters of UAV along with the gyroscopic momentum compensation it's necessary to increasing of the kinetic moment by means of gyroscope.This is achieved by installing the gyroscopes oppose to the propeller taking into account the gravity center of UAV (with rear-mounted propeller gyroscope should be installed in front sector), the direction of rotation of the gyro rotor is directed against the rotation of the propeller (the axis of the gyro rotor and propeller are in straight line); availing high kinetic momentum the devise becomes less subjected to the effects of the wind and turbulence; changing of the flight trajectory performed by moving axis of the gyroscope (stabilization and moments motors) and reductor, that fixed on moving shaft of the rotary frame, and the gyroscope is installed in a device to perform coincidence of the gyroscopic moments with the direction of the rotation of UAV. Coincidence of the directions of gyroscopic moments with the moments of the elevator and rudder increases the UAVs maneuverability. Stabilization and modification of the angular position of the UAV relative to the longitudinal roll axis is performed by increasing or decreasing of rotations of the gyro rotor with adjustable inertial moment.

    Hybrid multicopter and fixed wing aerial vehicle
    170.
    发明授权
    Hybrid multicopter and fixed wing aerial vehicle 有权

    公开(公告)号：US09873508B2

    公开(公告)日：2018-01-23

    申请号：US15585743

    申请日：2017-05-03

    Applicant: Coriolis Games Corporation

    Inventor： Jacob Apkarian

    IPC: B64C29/00 ,  B64C39/02 ,  B64F5/10

    CPC classification number: B64C29/0033 ,  B64C27/20 ,  B64C27/52 ,  B64C39/024 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2211/00 ,  B64F5/10

    Abstract: An aerial vehicle is includes a wing, first and second rotors, and a movement sensor. The first and second multicopter rotors are rotatably coupled to the wing, the first multicopter rotor is rotatable relative to the wing about a first lateral axis, and the second multicopter rotor is rotatable relative to the wing about a second lateral axis. Each multicopter rotor is coupled to each other multicopter rotor, wherein the multicopter rotors are restricted to collective synchronous rotation relative to the wing between a multicopter configuration and a fixed-wing configuration. The movement sensor is coupled to the multicopter rotors, wherein the movement sensor is positioned to rotate relative to the wing when the multicopter rotors rotate relative to the wing between the multicopter and fixed-wing configurations.

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