A pitch change link may include a shaft having a first end region and a second end region, and a bearing cartridge on at least one of the first end region and the second end region. The bearing cartridge may include a bearing and a bearing ring at least partially surrounding the bearing. The bearing ring may have a geometric symmetry and a cross section that is wider at a first end than at a second end, the first end may oppose the second end.

A tip gap control system for a ducted aircraft includes a flight control computer including a blade length control module configured to generate a blade tip actuator command and a proprotor system in data communication with the flight control computer. The proprotor system includes a duct and proprotor blades surrounded by the duct. Each of the proprotor blades includes an active blade tip movable into various positions including a retracted position and an extended position. The tip gap control system also includes one or more actuators coupled to the active blade tips. The one or more actuators move the active blade tips between the various positions based on the blade tip actuator command, thereby controlling a tip gap between the proprotor blades and the duct.

A tip gap control system for a ducted aircraft includes a flight control computer including a blade length control module configured to generate a blade tip actuator command and a proprotor system in data communication with the flight control computer. The proprotor system includes a duct and proprotor blades surrounded by the duct. Each of the proprotor blades includes an active blade tip movable into various positions including a retracted position and an extended position. The tip gap control system also includes one or more actuators coupled to the active blade tips. The one or more actuators move the active blade tips between the various positions based on the blade tip actuator command, thereby controlling a tip gap between the proprotor blades and the duct.

A control device controls an electric drive system mounted on an electric vertical takeoff and landing aircraft with a rotor, and including a drive motor that turns the rotor. The control device controls the electric drive system to operate selectively in any one operation mode of at least two operation modes: a normal mode and a functional test mode. In the normal mode, the control device controls the drive motor in accordance with a command from a body control device that controls the flight of the electric vertical takeoff and landing aircraft. In the functional test mode, the control device controls the drive motor in accordance with a command sent from outside according to a functional test program, or in accordance with the functional test program preset in the control device.

An aircraft rotor system including a hub having a hub axis about which the hub is configured to rotate; a plurality of rotor blades configured to extend from the hub and rotate about the hub axis, at least one of the rotor blades rotatable about a respective pitch change axis; wherein the hub is configured to be rotated about the hub axis only by the plurality of rotor blades. Another aspect includes a method of operating the rotor system.

A propelling system with variable aerodynamic controls is a system used to generate and control the flight forces of an aircraft. The system includes a stator, a rotor, a plurality of propelling units, and a control system. The stator serves as the stationary connection to the aircraft. The rotor revolves the propelling units about a central rotation axis. The control system enables the control of the propelling units. The propelling units generate the flight forces for the aircraft in the desired direction. In addition, each of the propelling units include a blade body, a shaft channel, a spar shaft, and at least one aileron assembly. The shaft channel receives the spar shaft within the blade body. The spar shaft connects the blade body to the rotor. The blade body passively corrects its angle of attack and supports the aileron assembly. The aileron assembly adjusts the pitch of the blade body.

A propelling system with variable aerodynamic controls is a system used to generate and control the flight forces of an aircraft. The system includes a stator, a rotor, a plurality of propelling units, and a control system. The stator serves as the stationary connection to the aircraft. The rotor revolves the propelling units about a central rotation axis. The control system enables the control of the propelling units. The propelling units generate the flight forces for the aircraft in the desired direction. In addition, each of the propelling units include a blade body, a shaft channel, a spar shaft, and at least one aileron assembly. The shaft channel receives the spar shaft within the blade body. The spar shaft connects the blade body to the rotor. The blade body passively corrects its angle of attack and supports the aileron assembly. The aileron assembly adjusts the pitch of the blade body.

The present invention relates to a device for directly controlling a blade which comprises a stator (1), at least one blade carrier (7) composed of at least one curved magnet (6), the blade carrier (7) being secured to at least one blade (3) and pivotally coupled to the rotor (8) for varying the alpha angle of said blades with the excitation of the stator (1). The stator (1) is a partially spherical stator, the stator core (1) being the intersection of the blade axis (22) and the rotor axis (20), said stator being radially close to the magnets (3) to control the rotation of the blades (3) around the blade axis (22). A magnetic ring (5) holds the blades (3) in a neutral position, the system can be compared to a cyclically controlled mechanical oscillator, the frequency, phase and amplitude of the oscillation being controlled by said stator. Device providing a compact, lightweight and robust solution for controlling the direction of an aircraft.

The present invention relates to a device for directly controlling a blade which comprises a stator (1), at least one blade carrier (7) composed of at least one curved magnet (6), the blade carrier (7) being secured to at least one blade (3) and pivotally coupled to the rotor (8) for varying the alpha angle of said blades with the excitation of the stator (1). The stator (1) is a partially spherical stator, the stator core (1) being the intersection of the blade axis (22) and the rotor axis (20), said stator being radially close to the magnets (3) to control the rotation of the blades (3) around the blade axis (22). A magnetic ring (5) holds the blades (3) in a neutral position, the system can be compared to a cyclically controlled mechanical oscillator, the frequency, phase and amplitude of the oscillation being controlled by said stator. Device providing a compact, lightweight and robust solution for controlling the direction of an aircraft.

An aircraft uses trajectory-based control algorithms for blade pitch (or twist). This approach greatly enhances the ability of the actuator to accurately achieve the desired blade pitch and to track the commanded pitch position. An actuator includes an electronic rotor blade controller that converts communicated or desired changes in pitch (or similar parameter) to actual physical effects that match the desired changes as closely as possible. The controller preferably includes a motor drive circuit, such as an h-bridge, a communication circuit for connection to external commands, and a processor with associated enabling circuitry (e.g. memory, I/O) to coordinate and implement the control.