A helicopter with a rotor pivotally connected to a shaft by a universal joint or ball and socket joint. The helicopter includes: a fuselage; a rotor mast that is fixed against relative rotation with respect to the fuselage; at least one blade; a motor for rotating the at least one blade; and a universal joint or ball and socket joint. The universal joint or ball and socket joint: (i) is disposed between the at least one blade and the rotor mast, with the at least one blade being rotatable relative to the universal joint or ball and socket joint; (ii) is disposed between the motor and the rotor mast; and (iii) is fixed against relative rotation with respect to the rotor mast, such that, pivoting of the universal joint or ball and socket joint causes the at least one blade and the motor to tilt.

A helicopter with a rotor pivotally connected to a shaft by a universal joint or ball and socket joint. The helicopter includes: a fuselage; a rotor mast that is fixed against relative rotation with respect to the fuselage; at least one blade; a motor for rotating the at least one blade; and a universal joint or ball and socket joint. The universal joint or ball and socket joint: (i) is disposed between the at least one blade and the rotor mast, with the at least one blade being rotatable relative to the universal joint or ball and socket joint; (ii) is disposed between the motor and the rotor mast; and (iii) is fixed against relative rotation with respect to the rotor mast, such that, pivoting of the universal joint or ball and socket joint causes the at least one blade and the motor to tilt.

Provided is a flight vehicle and in particular a flight vehicle in which a main module equipped with a device capable of carrying cargo, photographing, etc. may freely switch directions during flight while applying a posture independent of a thrust module because the thrust module is configured to freely perform roll and pitch motions with respect to the main module.

Provided is a flight vehicle and in particular a flight vehicle in which a main module equipped with a device capable of carrying cargo, photographing, etc. may freely switch directions during flight while applying a posture independent of a thrust module because the thrust module is configured to freely perform roll and pitch motions with respect to the main module.

A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.

A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.

A coaxial rotor system for a rotorcraft includes a mast, a top rotor assembly and a bottom rotor assembly. The top rotor assembly is coupled to the distal end of the mast. The bottom rotor assembly includes a motor configured to provide rotational energy to the mast, thereby rotating the top rotor assembly. The bottom rotor assembly experiences a torque reaction force responsive to the motor rotating the mast such that the top and bottom rotor assemblies counter rotate.

A multi-rotor unmanned aerial vehicle (UAV) comprises: a fuselage; a plurality of rotor mechanisms disposed on the fuselage, each rotor mechanism including a rotor; and a plurality of connection mechanisms disposed on the fuselage. The plurality of connection mechanisms have a one-to-one correspondence with the plurality of rotor mechanisms, each connection mechanism corresponding to one of the plurality of rotor mechanisms. Each rotor mechanism is movably connected to the fuselage through the corresponding connection mechanism; and the plurality of rotor mechanisms are configured to be rotated with respect to the corresponding connection mechanisms to cause the plurality of rotor mechanisms to overlap with each other and form a rotor mechanism assembly.

A multi-rotor unmanned aerial vehicle (UAV) comprises: a fuselage; a plurality of rotor mechanisms disposed on the fuselage, each rotor mechanism including a rotor; and a plurality of connection mechanisms disposed on the fuselage. The plurality of connection mechanisms have a one-to-one correspondence with the plurality of rotor mechanisms, each connection mechanism corresponding to one of the plurality of rotor mechanisms. Each rotor mechanism is movably connected to the fuselage through the corresponding connection mechanism; and the plurality of rotor mechanisms are configured to be rotated with respect to the corresponding connection mechanisms to cause the plurality of rotor mechanisms to overlap with each other and form a rotor mechanism assembly.

A coaxial rotor system for a rotorcraft includes a mast, a top rotor assembly and a bottom rotor assembly. The top rotor assembly is coupled to the distal end of the mast. The bottom rotor assembly includes a motor configured to provide rotational energy to the mast, thereby rotating the top rotor assembly. The bottom rotor assembly experiences a torque reaction force responsive to the motor rotating the mast such that the top and bottom rotor assemblies counter rotate.