초록 ▼

An apparatus for compensating for spatial phase angle phase errors in the flapping angle oscillations of a rotor blade is disclosed. The apparatus receives a measured aircraft roll and a measured aircraft pitch. Gyroscopic moments resulting from these measured rolls and pitches are determined, and c

An apparatus for compensating for spatial phase angle phase errors in the flapping angle oscillations of a rotor blade is disclosed. The apparatus receives a measured aircraft roll and a measured aircraft pitch. Gyroscopic moments resulting from these measured rolls and pitches are determined, and compensating gyroscopic moments are then generated and summed with commanded pitch and roll accelerations. Flapping angle phase lags of the rotor blade swashplate are added to the summed signals to cancel any flapping angle phase leads, caused by changes in aircraft or rotor blade speed caused by installation configurations of the rotor blade swashplate.

대표청구항 ▼

[ I claim:] [1.] An apparatus for controlling a tip path plane of a rotating rotor blade of an aircraft having rotor blade controls, the apparatus controlling the tip path plane to eliminate axis cross-coupling from the rotor blade controls of the aircraft, the apparatus comprising:(a) a rotor blade

[ I claim:] [1.] An apparatus for controlling a tip path plane of a rotating rotor blade of an aircraft having rotor blade controls, the apparatus controlling the tip path plane to eliminate axis cross-coupling from the rotor blade controls of the aircraft, the apparatus comprising:(a) a rotor blade swashplate;(b) at least three actuators for controlling a translation and a tilt angle of the rotor blade swashplate;(c) a fly-by-wire computer system for issuing position commands to the three actuators;(d) a first inputting channel for inputting first inputs, for use in determining a spatial phase angle at which flapping oscillations of the rotor blade obtain maximum values, the first inputs including:(1) a measured rotor blade speed;(2) a measured aircraft speed; and(3) measured rotor blade swashplate positions;(e) a second inputting channel for inputting second inputs, for use in determining gyroscopic moments on the rotor blade, the second inputs including:(1) measured changes in a pitch of the aircraft; and(2) measured changes in a roll of the aircraft;(f) a first determiner for determining a required translation and tilt angle of the rotor blade swashplate so that the maximum values of the resulting rotor blade flapping oscillations will occur in alignment with a vector sum of a desired angular acceleration of the aircraft;(g) a second determiner for determining specific positions of the three rotor blade swashplate actuators that will cause the rotor blade swashplate translation and tilt angle determined by the first determiner;(h) a third determiner for determining a changing phase shift of the maximum values of the rotor blade flapping oscillations as the measured rotor blade speed changes, the measured aircraft speed changes, and a rotor blade lift changes;(i) a first gyroscopic moment compensator for generating:(1) an aircraft-pitch gyroscopic moment compensation to aircraft roll, the aircraft-pitch gyroscopic moment compensation to aircraft roll cancelling any longitudinal gyroscopic moments generated by a roll rate of the aircraft; and(2) an aircraft-roll gyroscopic moment compensation to aircraft roll, the aircraft-roll gyroscopic moment compensation to aircraft roll cancelling any lateral gyroscopic moments generated by a roll rate of the aircraft; and(j) a second gyroscopic moment compensator for generating:(1) an aircraft-pitch gyroscopic moment compensation to aircraft pitch, the aircraft-pitch gyroscopic moment compensation to aircraft pitch cancelling any longitudinal gyroscopic moments generated by a pitch rate of the aircraft; and(2) an aircraft-roll gyroscopic moment compensation to aircraft pitch, the aircraft-roll gyroscopic moment compensation to aircraft pitch cancelling any lateral gyroscopic moments generated by a pitch rate of the aircraft.