A flight control system for an aircraft includes a flight control computer operatively interconnected with a main rotor system and a translational thrust system of the aircraft. A selectively enabled integrated target and flight control system arranged in communication with the flight control computer. The integrated target flight and control system is configured to control pitch attitude and heading of the aircraft. When the integrated target and flight control system is enabled, at least partial operation of the aircraft is controlled in response to a pilot input via the flight control computer.

A stoppable rotor, which includes a first and second blade and rotates about a substantially vertical axis, is stopped with the first blade pointing forward and the second blade pointing backward while the aircraft is mid-flight. Anti-torque is provided using a set of one or more combination rotors in a first mode of operation in order to counter torque produced by the stoppable rotor when the stoppable rotor is rotating where the set of combination rotors rotate about a substantially longitudinal axis. Forward thrust is provided using the set of combination rotors in a second mode of operation when the stoppable rotor is not rotating.

While an aircraft is mid-flight, a braking start point associated with a stoppable rotor is calculated where the stoppable rotor includes a first and second blade and the stoppable rotor is configured to rotate about a substantially vertical axis. A process to stop the stoppable rotor is started, while the aircraft is mid-flight, when the stoppable rotor reaches the braking start point, where the stoppable rotor is stopped with the first blade pointing forward and the second blade pointing backward.

A rotor head is provided and includes a non-rotating frame, a rotating frame rotatable relative to the non-rotating frame and configured to impart motion to the rotating frame, a rotor hub assembly rotatable about a rotation axis and including a hub and blades extending outwardly from the hub and being pivotable about respective pitch axes thereof and rocker assemblies respectively associated with corresponding ones of the blades. Each rocker assembly is interconnected between the rotating frame and the corresponding one of the blades and configured to convert the motion imparted to the rotating frame into a pitching of one of the blades about the respective pitch axes and amplify the motion such that an angle of the pitching exceeds an angle that would be achieved if the corresponding one of the blades were connected directly to the rotating frame.

A bearing sleeve assembly includes a rigid inner element having a cylindrical inner diameter bore and an outer surface that is non-cylindrical. Also included is a rigid outer element spaced radially outwardly from the rigid inner element, the rigid outer element comprising a cylindrical member with a uniform cross-section that forms a ring with an inner-diameter surface and an outer-diameter surface, the outer element's inner-diameter surface and the non-cylindrical outer surface of the inner element defining a non-uniform annulus therebetween. Further included is an elastomeric core disposed between the rigid inner element and the rigid outer element within the non-uniform annulus, the elastomeric core having a first thickness at a first location and a second thickness at a second location, the first thickness being greater than the second thickness.

A rotary wing aircraft includes an airframe including an extending tail. The airframe includes a longitudinal axis that extends through the extending tail. The rotary wing aircraft also includes a main rotor assembly including at least one rotor hub supporting a plurality of rotor blades configured and disposed to rotate about a main rotor axis, at least one elevator arranged at the extending tail, and a control system operably connected to the main rotor assembly and the at least one elevator. The control system is configured and disposed to adjust each of a pitch rate and an attitude of the airframe by selectively adjusting a position of the at least one elevator.

A rotorcraft is provided and includes a fuselage. The fuselage includes drag generating portions, a main rotor assembly and an auxiliary propulsor having an expected propulsion efficiency. The auxiliary propulsor is disposed to ingest boundary layer flows and in wake regions associated with the drag generating portions and is provided with a corresponding increase in the expected propulsion efficiency thereof.

A diverter duct for a propeller includes a second duct element having a semi-annular wedge shape, which is pivotably coupled to the first duct element, a first drive structure configured to drive a pivoting of the second duct element relative to the first duct element and a second drive structure configured to drive a rotation of the first and second duct elements about an axis of rotation of the propeller.

A main rotor blade assembly for a rotary wing aircraft is provided including a main rotor blade root region, a main rotor blade inboard region arranged outboard of said main rotor blade root region, a main rotor blade main region arranged outboard of said main rotor blade inboard region, and a main rotor blade tip region arranged outboard of said main rotor blade main region. At least one of chord, twist, sweep, airfoil shape, and thickness/chord of the main rotor blade assembly has been optimized to achieve balanced high speed forward flight and hover relative to both efficiency and high thrust capability.

A lift fan position lock mechanism is disclosed. In various embodiments, a position lock mechanism includes a ring structure having a first surface, the ring structure including one or more detents defined in the first surface of the ring structure. For each detent, the lock mechanism includes a stationary magnet coupled fixedly to the ring structure at a location adjacent to the detent. The lock mechanism further includes a rotating magnet assembly comprising a magnet of opposite magnetic polarity to at least one of the stationary magnets and a mechanical stop structure of a size and shape to fit into a corresponding detent and engage mechanically with a surface defining at least one extent of said corresponding detent when the rotating magnet assembly is in a locked position.