A flying object (drone) has a propeller drive unit provided in a fuselage thereof, and flies through the air by being driven by the propeller drive unit. The drone has a gravitational center movement device which is provided in the upper section of the fuselage and is capable of moving the total gravitational center position of the entire drone. The drone is equipped with a movement controller which moves the total gravitational center position to a target position by acquiring the total gravitational center position and controlling operation of the gravitational center movement device.

A flying object (drone) has a propeller drive unit provided in a fuselage thereof, and flies through the air by being driven by the propeller drive unit. The drone has a gravitational center movement device which is provided in the upper section of the fuselage and is capable of moving the total gravitational center position of the entire drone. The drone is equipped with a movement controller which moves the total gravitational center position to a target position by acquiring the total gravitational center position and controlling operation of the gravitational center movement device.

A helicopter includes a propulsion system, gimbal assembly, and a controller. The propulsion system includes a first rotor assembly and a second rotor assembly. The first rotor assembly comprises a first motor coupled to a first rotor and the second rotor assembly comprises a second motor coupled to a second rotor. The second rotor is coaxial to the first rotor and is configured to be counter-rotating to the first rotor. The gimbal assembly couples a fuselage of the helicopter to the propulsion system. The controller is communicably coupled to the gimbal assembly and is configured to provide instructions to the gimbal assembly in order to weight-shift the fuselage of the helicopter, thereby controlling movements of the helicopter.

A helicopter includes a propulsion system, gimbal assembly, and a controller. The propulsion system includes a first rotor assembly and a second rotor assembly. The first rotor assembly comprises a first motor coupled to a first rotor and the second rotor assembly comprises a second motor coupled to a second rotor. The second rotor is coaxial to the first rotor and is configured to be counter-rotating to the first rotor. The gimbal assembly couples a fuselage of the helicopter to the propulsion system. The controller is communicably coupled to the gimbal assembly and is configured to provide instructions to the gimbal assembly in order to weight-shift the fuselage of the helicopter, thereby controlling movements of the helicopter.

An aircraft has a fuselage, and pivot wings pivotally connected with the fuselage, the pivot wings pivoting between a vertical orientation for vertical takeoff, and a horizontal orientation for horizontal flight. Ailerons on each of the pivot wings provide roll control for the aircraft in all phases of flight. A gimbal motor assembly is mounted on the fuselage to adjustably support a motor. An upper rotary pivot free wing is mounted on a mast driven by the motor. A vectored thrust mechanism is provided for forward movement of the aircraft.

An aircraft has a fuselage, and pivot wings pivotally connected with the fuselage, the pivot wings pivoting between a vertical orientation for vertical takeoff, and a horizontal orientation for horizontal flight. Ailerons on each of the pivot wings provide roll control for the aircraft in all phases of flight. A gimbal motor assembly is mounted on the fuselage to adjustably support a motor. An upper rotary pivot free wing is mounted on a mast driven by the motor. A vectored thrust mechanism is provided for forward movement of the aircraft.

[Problem] To provide an aerial vehicle wherein the flight efficiency can be improved. [Solution] An aerial vehicle according to the present invention relates in particular to a aerial vehicle having a loading section whereon a payload and the like can be loaded. The aerial vehicle is capable of traveling at least forward and backward, is provided with lift generation sections, arm sections for holding the lift generation sections, a loading section disposed on the arm sections and positioned posterior to the center of gravity of the aerial vehicle, and a maintaining means for maintaining the aerial vehicle at least in the horizontal attitude, and the loading section has a first connection part for maintaining a loaded object at least in the horizontal attitude. On the basis of the above mentioned, the payload can be prevented from entering slipstream regions created by propellers, improving flight efficiency

[Problem] To provide an aerial vehicle wherein the flight efficiency can be improved. [Solution] An aerial vehicle according to the present invention relates in particular to a aerial vehicle having a loading section whereon a payload and the like can be loaded. The aerial vehicle is capable of traveling at least forward and backward, is provided with lift generation sections, arm sections for holding the lift generation sections, a loading section disposed on the arm sections and positioned posterior to the center of gravity of the aerial vehicle, and a maintaining means for maintaining the aerial vehicle at least in the horizontal attitude, and the loading section has a first connection part for maintaining a loaded object at least in the horizontal attitude. On the basis of the above mentioned, the payload can be prevented from entering slipstream regions created by propellers, improving flight efficiency

A helicopter includes a gimbal assembly, a first rotor assembly, a second rotor assembly, a fuselage, and a controller. The first rotor assembly, the second rotor assembly, and the fuselage are mechanically coupled to the gimbal assembly. The first rotor assembly includes a first rotor and the second rotor assembly includes a second rotor, the first rotor including a plurality of first fixed-pitch blades and the second rotor including a plurality of second fixed-pitch blades. Each of the plurality of first and the second fixed-pitch blades are coupled to a hub of its respective rotor via a hinge mechanism that is configured to allow each of the fixed-pitch blades to pivot from a first position to a second position, the first position being substantially parallel to the fuselage and the second position being substantially perpendicular to the fuselage.

An aircraft is disclosed having a structure at least part of which is capable of generating aerodynamic lift. A body having a mass is movably mounted to a portion of the structure by an active support. The active support includes an actuator to move the body relative to the portion of the structure, and a controller for controlling movement of the actuator in response to a dynamic input. The active support provides a range of movement for the body in at least one degree of freedom. The actuator moves the body across the entire range of movement in that one degree of freedom in a time period of less than 3 seconds. The actuator moves the body sufficiently rapidly to generate an inertial force that is equal to or greater than any aerodynamic force generated by the body during that movement of the body. The active support may be used to reduce loads on the aircraft structure.