Changes in angle of attack in system were sensed indirectly by gages which responded to strains induced in wing structure. Output signals were amplified, filtered, and used to activate swashplate actuators. System provided significant reduction in blade loads and desirable changes in hub forces and moments.
Swashplate feedback control for tilt-rotor aircraft
1974-09-01
Miscellaneous
No indication
English
SWASHPLATE FOR A SINGLE-ROTOR AIRCRAFT AND OPERATING METHOD THEREOF
European Patent Office | 2022
|