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.] A method of controlling a rotor blade swashplate to stabilize either a helicopter aircraft or a jet-powered tri-mode aircraft as the jet-powered tri-mode aircraft travels in a transitional mode, which is between a helicopter mode and a fixed-wing mode, the method comprising the foll

[ I claim:] [1.] A method of controlling a rotor blade swashplate to stabilize either a helicopter aircraft or a jet-powered tri-mode aircraft as the jet-powered tri-mode aircraft travels in a transitional mode, which is between a helicopter mode and a fixed-wing mode, the method comprising the following steps:detecting at least one of rotor blade speed, change in aircraft velocity, and installation configurations of a rotor blade swashplate of a rotor blade;compensating for at least one of changes in rotor blade speed, changes in aircraft velocity, and for installation configurations of a rotor blade swashplate of a rotor blade; andcompensating for gyroscopic moments on the rotor blade which are induced by at least one of an aircraft pitch rate and an aircraft roll rate, the step of compensating for gyroscopic moments on the rotor blade including the following substeps:measuring an aircraft roll of the aircraft;determining gyroscopic moments, which are generated by the measured aircraft roll of the aircraft, and which are placed on the rotor blade of the aircraft; andcontrolling a rotor blade swashplate, based on the determined gyroscopic moments.