Helicopter with leading edge servo flaps for pitch positioning its rotor blades
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United States of America Patent
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-
Apr 25, 1995
Grant Date -
N/A
app pub date -
Aug 6, 1993
filing date -
Aug 6, 1993
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
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.
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