A power display of an aircraft having a main rotor system and a translational thrust includes a reference member, a first indicator arranged adjacent the reference member and operable to display a power being used by the main rotor system, and a second indicator arranged adjacent the reference member and operable to display a power being used by the translational thrust system.

A method of reducing the noise generated in-flight by a vortex wake caused by each first blade of a main rotor of a hybrid helicopter. The hybrid helicopter includes a main rotor, at least two wings and at least one propeller. The method enables a stabilized flight phase on the level or with a non-zero aerodynamic slope to be implemented by determining a first value of the pitch of the second blades of each propeller and an angle of incidence of the main rotor as function of the flight conditions, then by applying the first pitch value to each propeller and by applying the angle of incidence to the main rotor so as to direct the vortex wake to limit the noisy interactions between the vortex wake and the other first blades and/or the second blades.

A helicopter is described comprising: a tail boom; a fin projecting from the tail boom; and a tailplane arranged at the tail boom and transversal to the fin; at least one of the fin and the tailplane defining a first aerodynamic surface generating a first aerodynamic force; at least one first element transversal to the first aerodynamic surface; and a second aerodynamic surface generating a second aerodynamic force, connected to the first element, facing and spaced from the first aerodynamic surface; the second aerodynamic surface is spaced from the other of the fin and the tailplane.

A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a propeller that is at least configured to propel the rotary wing aircraft in forward flight condition, wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and a shrouded duct that is arranged in the aft region and that forms an inner air duct which accommodates at least partly the propeller, wherein the shrouded duct comprises a yaw and pitch stability enhancement unit for improving yaw and pitch stability of the rotary wing aircraft in the forward flight condition.

A manned or unmanned aircraft has a main body with a circular shape and a circular outer periphery. One or more rotor blades extend substantially horizontally outward from the main body at or about the circular outer periphery. In addition, one or more counter-rotation blades extend substantially horizontally outward from said main body at or about the circular outer periphery, but vertically offset from the main rotor blades.

A compound aircraft includes a convertible thruster that pivots between an anti-torque position, a forward thrust position, and intermediate positions. A pilot has two inceptors to control thruster rotor pitch in the anti-torque and forward thrust positions. A mixer mechanically blends the signals from the two inceptors during transition between the anti-torque and forward thrust positions. A transfer rod coaxial with the pivot axis of the convertible thruster conveys convertible thruster pitch commands from the pilot to a pitch control actuator. The pitch control actuator may be located partially within the rotor of an electric motor that rotates the convertible thruster rotor. The electric motor and pitch control actuator are unitary. Both the electric motor and pitch control actuator pivot with the convertible thruster. The pitch actuator output shaft is coaxial to and disposed within a hollow electric motor output shaft.

A rotary wing aircraft that extends along an associated roll axis between a nose region and an aft region. The rotary wing aircraft comprises a main rotor; a propeller that is at least configured to propel the rotary wing aircraft in forward flight condition, wherein the propeller forms a circular propeller disc in rotation around an associated rotation axis; and a shrouded duct that is arranged in the aft region and that forms an inner air duct which accommodates at least partly the propeller, wherein the shrouded duct comprises a yaw and pitch stability enhancement unit for improving yaw and pitch stability of the rotary wing aircraft in the forward flight condition.

Systems and methods for controlling a coaxial rotary-wing aircraft including a co-axial main rotor assembly and a pusher-propeller. One system includes an electronic controller configured to receive a reference velocity of the aircraft and receive a reference flight path angle of the aircraft. The electronic controller is also configured to simultaneously control the co-axial main rotor assembly and the pusher-propeller based on the reference velocity of the aircraft and the reference flight path angle of the aircraft, by simultaneously generating a commanded thrust of the pusher-propeller and a commanded thrust of the co-axial main rotor assembly using a multiple input, multiple output algorithm applying dynamic inversion.

An exemplary anti-torque system for a rotorcraft includes a fan located inside of a channel that extends inside of a fuselage from an inlet proximate a forward end of the tail boom to an outlet at an aft end of the tail boom, the outlet is oriented to direct airflow from the channel onto a rudder coupled to a trailing edge of a vertical stabilizer.

In an aspect, a vertical take-off and landing (VTOL) aircraft is disclosed. The VTOL aircraft includes at least a lift component affixed to the aft end of a boom, wherein the lift component is configured to generate lift. The VTOL includes a fuselage comprising a fore end and an aft end. Additionally, VTOL aircraft includes a tail affixed to the aft end of a fuselage. A tail includes a plurality of vertically projecting elements, wherein the plurality vertically projecting elements are affixed at the aft end of the boom and positioned outside of the wake from the at least a lift component.