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.

This invention presents a unique propulsion and maneuver-control system for crafts and devices. This invention develops its desired thrust force vectors from the vectors sum of centrifugal force vectors of rotating masses and their controlled gyroscopic force vectors. Also shown are applications of this propulsion and maneuver-control system for future VTOL-Hovering-Flying crafts, Scooters, Surfboards, marine/submarine-crafts, earth, moon, mars satellites disks and space-crafts. This invention has great potentials of creating new businesses in aerospace markets, all planets' weather modification business, bring people of the world closer together and perform critical tasks of modify trajectories to prevent run-away asteroids from hitting the earth.

This invention presents a unique propulsion and maneuver-control system for crafts and devices. This invention develops its desired thrust force vectors from the vectors sum of centrifugal force vectors of rotating masses and their controlled gyroscopic force vectors. Also shown are applications of this propulsion and maneuver-control system for future VTOL-Hovering-Flying crafts, Scooters, Surfboards, marine/submarine-crafts, earth, moon, mars satellites disks and space-crafts. This invention has great potentials of creating new businesses in aerospace markets, all planets' weather modification business, bring people of the world closer together and perform critical tasks of modify trajectories to prevent run-away asteroids from hitting the earth.

An unmanned aerial vehicle (UAV) is provided. The UAV includes a main body, a plurality of motors connected to the main body, each of the plurality of motors having a rotor blade, a plurality of ultrasonic sensors located at least one of the plurality of motors and the main body, and transmitting and receiving ultrasonic waves to and from a ground surface, and measuring distances from the ground surface, a gyro sensor disposed at the main body and maintaining the UAV in a horizontal state, and a controller disposed at the main body, detecting an unevenness of the ground surface based on the distances from the plurality of ultrasonic sensors to the ground surface, generating a control signal whether to land on the ground surface or not in response to the detection of the unevenness, and transmitting the control signal to the plurality of motors.

An unmanned aerial vehicle (UAV) is provided. The UAV includes a main body, a plurality of motors connected to the main body, each of the plurality of motors having a rotor blade, a plurality of ultrasonic sensors located at least one of the plurality of motors and the main body, and transmitting and receiving ultrasonic waves to and from a ground surface, and measuring distances from the ground surface, a gyro sensor disposed at the main body and maintaining the UAV in a horizontal state, and a controller disposed at the main body, detecting an unevenness of the ground surface based on the distances from the plurality of ultrasonic sensors to the ground surface, generating a control signal whether to land on the ground surface or not in response to the detection of the unevenness, and transmitting the control signal to the plurality of motors.

A VTOL (vertical take-off and landing) aerial flying vehicle comprising an inner frame, a gimbal system and an outer frame, the inner frame comprising a propulsion system and a control system. The propulsion system being able to generate a lift force. The VTOL may also include a decoupling mechanism having either a linear or non-linear beam coupled to a ring. The beam may optionally include sliders at ends thereof that provide an additional rotation freedom to the inner frame.

A hybrid power source and control moment gyroscope (“HPCMG”) is disclosed. The HPCMG includes a control moment gyroscope (“CMG”), a first conductive bearing, and a second conductive bearing. The CMG includes a first transverse gimbal assembly, a central mass that produces a voltage potential, and a second gimbal assembly rotationally connected to the first transverse gimbal assembly. The first transverse gimbal assembly is rotationally connected to the central mass along a first axis of rotation and the central mass is configured to spin about the first axis of rotation and the first transverse gimbal assembly is configured to rotate about a second axis of rotation of the second gimbal assembly. The first conductive bearing rotationally connects the central mass with the first position of the first transverse gimbal assembly along the first axis of rotation.

An active stabilisation system including: a first motor having a stator connected to a system mount and a rotor configured for rotation about a first axis in a first plane of rotation passing through the first motor; a second motor having a stator connected with a first connection link to the rotor of the first motor and a rotor configured for rotation about a second axis in a second plane of rotation passing through the second motor, the second plane of rotation intersecting with the first motor; a third motor having a stator connected with a second connection link to the rotor of the second motor and a rotor configured for rotation about a third axis in a third plane of rotation passing through the third motor; and a payload mount connected to the rotor of the third motor and configured for attachment to a payload.

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.