A rotor system for a rotorcraft has a hub rotatable about an axis and a plurality of blades coupled to the hub for rotation therewith about the axis. Each blade is capable of rotation about a pitch axis relative to the hub, and a ring couples adjacent blades to each other.

A rotorcraft includes a main rotor system coupled to a mast and a rotor assembly. The rotor assembly includes a yoke comprising a rotor coupling, a first damper mount attached to the rotor coupling, a rotor extension configured to couple to the rotor coupling and comprising a second damper mount, a damper coupled to the first and second damper mounts, and a fairing enclosing the damper and the yoke.

A rotorcraft includes a main rotor system coupled to a mast and a rotor assembly. The rotor assembly includes a yoke comprising a rotor coupling, a first damper mount attached to the rotor coupling, a rotor extension configured to couple to the rotor coupling and comprising a second damper mount, a damper coupled to the first and second damper mounts, and a fairing enclosing the damper and the yoke.

Embodiments are directed to systems and methods for deploying an outboard rotor blade of proprotor pylon to act as an extended lifting surface. Blade control actuators may provide primary rotor flight control as well as providing fold linkage actuation when fold locks are disengaged. During cruise flight, the blade control actuator may provide feathering inputs to the extended rotor blade, wherein the amplitude and frequency of feathering inputs are tuned to mitigate undesirable wing and fuselage dynamic modes thereby enhancing aircraft stability. The deployed rotor blades also improve the total lifting area of the aircraft, which may increase aircraft range and efficiency.

Embodiments are directed to systems and methods for deploying an outboard rotor blade of proprotor pylon to act as an extended lifting surface. Blade control actuators may provide primary rotor flight control as well as providing fold linkage actuation when fold locks are disengaged. During cruise flight, the blade control actuator may provide feathering inputs to the extended rotor blade, wherein the amplitude and frequency of feathering inputs are tuned to mitigate undesirable wing and fuselage dynamic modes thereby enhancing aircraft stability. The deployed rotor blades also improve the total lifting area of the aircraft, which may increase aircraft range and efficiency.

A damper assembly includes a housing defining at least one or more cavities. A piston is in operable communication with the housing. A rod end is operatively coupled to the piston, the rod end having at least two cartridges.

A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub, a plurality of proprotor blades and a plurality of blade support assemblies coupling the proprotor blades with the hub. Each blade support assembly includes a flapping bearing coupled to the hub and a yoke having first and second longitudinal sections with outboard grip members and an inboard arcuate section connecting the first and second longitudinal sections and coupled to the flapping bearing. A lead-lag damper is coupled between the hub and an inboard station of the respective proprotor blade. A twist shank is coupled between the outboard grip members of the yoke and an outboard station of the respective the proprotor blade. The twist shank defines a virtual lead-lag hinge outboard of the yoke and coincident with the respective pitch change axis.

A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub, a plurality of proprotor blades and a plurality of blade support assemblies coupling the proprotor blades with the hub. Each blade support assembly includes a flapping bearing coupled to the hub and a yoke having first and second longitudinal sections with outboard grip members and an inboard arcuate section connecting the first and second longitudinal sections and coupled to the flapping bearing. A lead-lag damper is coupled between the hub and an inboard station of the respective proprotor blade. A twist shank is coupled between the outboard grip members of the yoke and an outboard station of the respective the proprotor blade. The twist shank defines a virtual lead-lag hinge outboard of the yoke and coincident with the respective pitch change axis.

An example of a rotor-state determining method for a rotor system includes, by a flight control computer, collecting data from a first sensor positioned on a first component of the rotorcraft, wherein the first sensor is isolated from movement of a rotor blade, collecting data from a second sensor positioned on a second component of the rotor system, wherein the second sensor detects movement of the rotor blade, filtering the data collected by the first sensor to remove noise from the data collected by the first sensor, filtering the data collected by the second sensor to remove noise from the data collected by the second sensor, calculating a difference between the filtered first data and the filtered second data to determine a parameter of the rotor blade, and responsive to the motion of the rotor blade, taking a corrective action.

A damping valve for a hydraulic damper comprises a valve housing comprising an inlet chamber and an outlet chamber. A valve seat is arranged between the inlet chamber and the outlet chamber. A valve element having a cylindrical first portion is slidably received in a cylindrical bore of the valve housing. A second portion of the valve element has a valve surface for selectively engaging and disengaging the valve seat to allow passage of hydraulic fluid between the inlet chamber and the outlet chamber. A spring element is mounted within the valve housing for biasing the valve element into engagement with the valve seat.