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 force generator includes a hub, which is rotatable about an axis thereof, an elongate member coupled to the hub such that the elongate member is rotatable with the hub and extends radially outwardly away from the hub and the axis along a radial dimension defined with respect to the axis and a mass, which is movably disposed along the elongate member and is adjustable to multiple radial mass positions relative to the hub.

A force generator includes a hub, which is rotatable about an axis thereof, an elongate member coupled to the hub such that the elongate member is rotatable with the hub and extends radially outwardly away from the hub and the axis along a radial dimension defined with respect to the axis and a mass, which is movably disposed along the elongate member and is adjustable to multiple radial mass positions relative to the hub.

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.

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.

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 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 helicopter is described comprising a fuselage elongated along a first axis and extending between a nose and a tail boom; a tailplane with a pair of first aerodynamic surfaces elongated along a second axis; the first and second axis define a first plane; the helicopter comprises a pair of elements transversal to the first aerodynamic surfaces; and a pair of second aerodynamic surfaces generating respective second aerodynamic forces, connected to first elements, and facing and spaced from respective first aerodynamic surfaces; each second aerodynamic surface comprises one first root end connected to the respective said element, a second free end spaced from said tail boom, a first leading edge, a first trailing edge opposite to said first leading edge, a first chord at said first root end and a second chord at said second free end parallel to said first axis; the first and the second chord define a second plane tilted with respect to said first plane.