초록 ▼

In a helicopter having a main rotor with blades controlled in pitch by servo flaps the servo flaps are arranged in advance of the leading edges of the blade to provide increased lift efficiency of the rotor system. The signals for controlling the pitches of the blade are generated by a computer impl

In a helicopter having a main rotor with blades controlled in pitch by servo flaps the servo flaps are arranged in advance of the leading edges of the blade to provide increased lift efficiency of the rotor system. The signals for controlling the pitches of the blade are generated by a computer implemented means responsive to pilot command signals and flight parameter signals and are transmitted from the stationary structure of the helicopter to the rotating structure through a non-mechanical stationary-to-rotary interface. An active stabilization system is associated with each rotor blade to overcome the instability previously associated with leading edge servo flaps and to reduce the complexity of the control signals needed to be produced by the control signal generating means.

대표청구항 ▼

In a helicopter, the combination comprising: a helicopter body, a rotor rotatable in one direction relative to said helicopter body about a generally vertical rotor axis, said rotor including a hub and a plurality of elongated blades connected with said hub, each of said blades extending generally r

In a helicopter, the combination comprising: a helicopter body, a rotor rotatable in one direction relative to said helicopter body about a generally vertical rotor axis, said rotor including a hub and a plurality of elongated blades connected with said hub, each of said blades extending generally radially outwardly from said hub and being movable relative to said hub about a blade pitch axis extending along its length, each of said blades having a leading edge and a trailing edge with respect to rotation of said rotor in said one direction, a leading edge servo flap carried by each of said blades for positioning that blade about its blade pitch axis, said servo flap being located in advance of said leading edge of its associated blade with respect to rotation of said rotor in said one direction, said servo flap extending for some distance along the length of its associated blade and being movable relative to that blade about a flap pitch axis positioned generally parallel to the blade pitch axis of that blade, means providing a number of selectably variable command signals describing a desired flight condition for said helicopter, means providing a number of flight parameter signals describing actual present state operating parameters of said helicopter, a computer implemented means for calculating for each of said blades and from said control signals and said flight parameter signals a multitude of blade control signals occurring successively throughout the course of each revolution of the associated one of said blades about said rotor axis and which control signals may vary in accordance with a variation pattern having an harmonic content above one per revolution of the rotor, and plurality of servo flap positioning means each associated with a respective one of said blades and each separate from the other of said servo flap positioning means for positioning the servo flap carried by the associated one of said blades about its flap pitch axis relative to that blade, each of said servo flap positioning means being a closed loop means including a comparing means for comparing the actual position of the associated blade about its pitch change axis to the desired position dictated by said blade control signal for the associated blade to produce an error signal, and means controlling the position of the associated servo flap about its flap pitch axis in response to said error signal.