Electromagnetic gyroscopic stabilizing propulsion system method and apparatus is an electric gyroscope that creates magnetic fields used to rotate its flywheel. The rotation of its flywheel creates both a gyroscopic effect and thrust with airfoil shaped spokes. The invention attaches to an airframe through an articulating joint that causes the axle of the gyroscope to precess in a vertical orientation regardless of the movements/angle of the airframe. The gyroscope's thrust aligns itself with the axle of the gyroscope. The net effect is that the invention has tremendous efficiency, no external drive because it is also a motor, tremendous power from magnetic leverage of the flywheel, and stability because of the gyroscopic effect.

Electromagnetic gyroscopic stabilizing propulsion system method and apparatus is an electric gyroscope that creates magnetic fields used to rotate its flywheel. The rotation of its flywheel creates both a gyroscopic effect and thrust with airfoil shaped spokes. The invention attaches to an airframe through an articulating joint that causes the axle of the gyroscope to precess in a vertical orientation regardless of the movements/angle of the airframe. The gyroscope's thrust aligns itself with the axle of the gyroscope. The net effect is that the invention has tremendous efficiency, no external drive because it is also a motor, tremendous power from magnetic leverage of the flywheel, and stability because of the gyroscopic effect.

An autonomous unmanned aerial vehicle for land, sea and air use. The autonomous unmanned aerial vehicle is more specifically related to an unmanned aerial vehicle, wherein the autonomous unmanned aerial vehicle is configured to vertically take off and vertically land, fly with fixed wings and stay in the air silently for a long time by means of a balloon inflated behind it.

A vibration control assembly for an aircraft includes a housing operatively coupled to the aircraft. Also included is a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis. Further included is a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle. Yet further included is a control assembly at least partially surrounding the gyroscope wheel for controlling the controllable moment. The control assembly includes a structure having an inner surface, a track disposed along the inner surface, and an arm operatively coupled to the gyroscope wheel, the arm having an end disposed within the track, the gyroscope wheel angularly displaceable upon translation of the arm along the track

A vibration control assembly for an aircraft includes a housing operatively coupled to the aircraft. Also included is a cage disposed within an interior region of the housing, the cage rotatable within the housing about a first axis. Further included is a gyroscope wheel disposed within the cage and rotatable about a second axis other than the first axis, wherein a controllable moment is imposed on the aircraft upon rotation of the gyroscope wheel to counter vibratory moments produced by the vehicle. Yet further included is a control assembly at least partially surrounding the gyroscope wheel for controlling the controllable moment. The control assembly includes a structure having an inner surface, a track disposed along the inner surface, and an arm operatively coupled to the gyroscope wheel, the arm having an end disposed within the track, the gyroscope wheel angularly displaceable upon translation of the arm along the track

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.

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.

In a hybrid flight vehicle, having four rotors attached to a frame and configured to produce propelling force to propel the frame, a gas turbine engine attached to the frame and configured to rotate when fuel is supplied, a generator connected to an output shaft of the engine and configured to generate electric power when driven by the engine, a battery configured to store the electrical power generated by the generator, and four first electric motors each connected to the rotors to drive associated one of the rotors when the electric power is supplied from the battery, and an electronic control unit configured to control flight by regulating driving of the four rotors by the first electric motors. In the vehicle, the output shaft of the engine is attached parallel to at least one among yaw axis, pitch axis and roll axis of the frame.

In a hybrid flight vehicle, having four rotors attached to a frame and configured to produce propelling force to propel the frame, a gas turbine engine attached to the frame and configured to rotate when fuel is supplied, a generator connected to an output shaft of the engine and configured to generate electric power when driven by the engine, a battery configured to store the electrical power generated by the generator, and four first electric motors each connected to the rotors to drive associated one of the rotors when the electric power is supplied from the battery, and an electronic control unit configured to control flight by regulating driving of the four rotors by the first electric motors. In the vehicle, the output shaft of the engine is attached parallel to at least one among yaw axis, pitch axis and roll axis of the frame.

Electromagnetic gyroscopic stabilizing propulsion system method and apparatus is an electric gyroscope that creates magnetic fields used to rotate its flywheel. The rotation of its flywheel creates both a gyroscopic effect and thrust with airfoil shaped spokes. The invention attaches to an airframe through an articulating joint that causes the axle of the gyroscope to precess in a vertical orientation regardless of the movements/angle of the airframe. The gyroscope's thrust aligns itself with the axle of the gyroscope. The net effect is that the invention has tremendous efficiency, no external drive because it is also a motor, tremendous power from magnetic leverage of the flywheel, and stability because of the gyroscopic effect.