A differential thrust vectoring system includes a first thruster, a second thruster, a main actuator, and a trim actuator. The system is configured such that actuation of the main actuator causes rotation of the thrusters together about an axis, whereas actuation of the trim actuator causes relative rotation of the first and second thrusters about the axis.

A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

The present disclosure is directed to a method for controlling rotors of a rotorcraft system comprising the steps of: receiving air velocity data, first and second rotors rotational angular velocity data, external air temperature data and rotorcraft altitude data by the control module; calculating air velocity over the plurality of blades based on the received data using the control module; calculating, based on the calculated air velocity, if one or more retreating blades of one of the first and second counterrotating rotors are generating insufficient lift; and sending one or more actuation signals from the control module to the electric motor and/or actuators of the other of the first and second counterrotating rotors to maintain a predetermined amount of lift.

Systems and methods relate to a vertical takeoff and landing (VTOL) platform that can include a stator and a rotor magnetically levitated by the stator. The rotor and stator can be annular, such that the rotor rotates about a rotational axis. The stator can include magnets that provide guidance, levitation, and drive forces to drive the rotor, as well as to control operation of rotor blades of the rotor that can be independently rotated to specific pitch angles to control at least one of lift, pitch, roll, or yaw of the VTOL platform. Various controllers can be used to enable independent and redundant control of components of the VTOL platform.

The application discloses a coaxial helicopter, the cyclic pitch-changing mechanism simultaneously adjusts the pitches of the upper and the lower rotor systems, to make uniformity cyclic pitch-changing adjustment of the upper and lower rotors, and make independent collective pitch adjustment of the upper rotor system; the differential pitch-changing mechanism and the cyclic pitch-changing mechanism jointly act on the lower rotor system, to perform differential collective pitch adjustment of the upper and lower rotor systems. The synchronous rotating mechanism drives the swashplate members to synchronously rotate along with the drive shaft. The application achieves a simpler hybrid pitch-changing control system of the coaxial rotor pitch, a plurality of flight operations of the coaxial aircraft are performed synchronously, and a plurality of flight control modes, such as semi-differential and full-differential in a variable speed or a fixed speed mode, are supported, and thus the present application has wider application space.

The application discloses a coaxial helicopter, the cyclic pitch-changing mechanism simultaneously adjusts the pitches of the upper and the lower rotor systems, to make uniformity cyclic pitch-changing adjustment of the upper and lower rotors, and make independent collective pitch adjustment of the upper rotor system; the differential pitch-changing mechanism and the cyclic pitch-changing mechanism jointly act on the lower rotor system, to perform differential collective pitch adjustment of the upper and lower rotor systems. The synchronous rotating mechanism drives the swashplate members to synchronously rotate along with the drive shaft. The application achieves a simpler hybrid pitch-changing control system of the coaxial rotor pitch, a plurality of flight operations of the coaxial aircraft are performed synchronously, and a plurality of flight control modes, such as semi-differential and full-differential in a variable speed or a fixed speed mode, are supported, and thus the present application has wider application space.

An exemplary length adjustable link includes a tube having an internal bore and internal surface, a first rod end having a first shaft disposed in a first end of the internal bore, a second rod end having a second shaft disposed in a second end of the internal bore, and a member threadably connecting the first rod end to the second rod end.

An exemplary length adjustable link includes a tube having an internal bore and internal surface, a first rod end having a first shaft disposed in a first end of the internal bore, a second rod end having a second shaft disposed in a second end of the internal bore, and a member threadably connecting the first rod end to the second rod end.

Disclosed is an apparatus (100) for an aerial transportation of a payload. The apparatus (100) includes a propeller unit (10) to provide a primary thrust whereas a plurality of propellers (50) is fitted around a body of the apparatus (100) to help in maneuvering and orientation control. The apparatus (100) employs gasoline as a primary source of energy that has a higher energy density than lithium polymer batteries. The apparatus (100) facilitates longer flight times. The apparatus (100) is useful for safe transportation of higher payloads and has vertical takeoff and land capability.