An adjustable control link for transferring rotor shaft rotation to a rotating swashplate, the adjustable control link includes an elongate element rotatable with the rotor shaft, the elongate element having a first end. A structure has an opening and a second end. At least one cam component is disposed within the opening and is rotatable relative to the structure about a central axis of the opening. A pin is configured to couple the elongate element to the at least one cam component. The pin is eccentrically rotatable about the central axis to move the first end of the elongate element relative to the second end of the structure.

A double-ring rotary wing spherical cabin aircraft includes a spherical cabin; an upper protective cover; a lower protective cover; a rotary wing fixing ring connected between inner circles of the upper and lower protective covers, and mounted with a gyroscope and a rotatable attitude-adjusting ring; an upper rotary wing rotor and a lower rotary wing rotor rotationally mounted on the rotary wing fixing ring; and a control system. The spherical cabin is rotationally mounted in the attitude-adjusting ring. Two attitude-adjusting articulated shafts opposite to each other are connected between the attitude-adjusting ring and the rotary wing fixing ring. Two cabin articulated shafts opposite to each other are connected between the spherical cabin and the attitude-adjusting ring. The attitude-adjusting articulated shaft and the cabin articulated shaft are in transmission connection with an attitude-adjusting motor. The attitude-adjusting motor and the gyroscope are electrically connected to the control system.

A double-ring rotary wing spherical cabin aircraft includes a spherical cabin; an upper protective cover; a lower protective cover; a rotary wing fixing ring connected between inner circles of the upper and lower protective covers, and mounted with a gyroscope and a rotatable attitude-adjusting ring; an upper rotary wing rotor and a lower rotary wing rotor rotationally mounted on the rotary wing fixing ring; and a control system. The spherical cabin is rotationally mounted in the attitude-adjusting ring. Two attitude-adjusting articulated shafts opposite to each other are connected between the attitude-adjusting ring and the rotary wing fixing ring. Two cabin articulated shafts opposite to each other are connected between the spherical cabin and the attitude-adjusting ring. The attitude-adjusting articulated shaft and the cabin articulated shaft are in transmission connection with an attitude-adjusting motor. The attitude-adjusting motor and the gyroscope are electrically connected to the control system.

A coaxial split torque gearbox comprises a first pinion meshed with a first gear; a second pinion attached to the first gear and meshed with a first bull gear, the first bull gear operable for transferring torque to cause a first rotor to rotate; and a third pinion attached to a second gear and meshed with a second bull gear, the second bull gear operable for transferring torque to cause a second rotor to rotate, the second gear being meshed with the first gear, and a number of teeth of the first gear being different than a number of teeth of the second gear.

A coaxial split torque gearbox comprises a first pinion meshed with a first gear; a second pinion attached to the first gear and meshed with a first bull gear, the first bull gear operable for transferring torque to cause a first rotor to rotate; and a third pinion attached to a second gear and meshed with a second bull gear, the second bull gear operable for transferring torque to cause a second rotor to rotate, the second gear being meshed with the first gear, and a number of teeth of the first gear being different than a number of teeth of the second gear.

Flying body including body portion and a plurality of propellers radially disposed to be laterally symmetrical from body portion is provided with: a plurality of motors respectively rotating the plurality of propellers; a plurality of power storage packs respectively supplying currents to the plurality of motors; and sub power storage pack connected to the plurality of power storage packs by power wirings, respectively. The same number of motors of the plurality of motors are installed on each of the left and right sides, and the same number of power storage packs of the plurality of power storage packs are installed on each of the left and right sides. Sub power storage pack is installed on a lateral center line of body portion.

A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades.

A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades.

A negative hinge offset rotor head for a coaxial helicopter, the rotor head having two or more flapping rotor blades having outer and inner tips, the inner tips rotatably attached to a hinge attachment rotated by a driveshaft where the driveshaft is positioned between the rotor blades and the rotor blades' respective hinge attachment.

A negative hinge offset rotor head for a coaxial helicopter, the rotor head having two or more flapping rotor blades having outer and inner tips, the inner tips rotatably attached to a hinge attachment rotated by a driveshaft where the driveshaft is positioned between the rotor blades and the rotor blades' respective hinge attachment.