The report describes the design and flight tests of a hydrofluidic yaw stability augmentation system (SAS) for an OH-58A helicopter. The design objective was to improve stability characteristics in yaw for all flight conditions from hover to 120 kn. The yaw SAS, which initially featured only high-passed yaw rate feedback, was installed in an OH-58A helicopter and flight tested in 1972. Performance at forward flight speeds was satisfactory; but at hover, yaw rates were excessive. The system was then modified to add a straight-through yaw rate feedback term. Flight tests of this configuration were conducted from October-December 1973. Results were satisfactory. (Author)
Yaw Axis Stability Augmentation System Flight Test Report
1974
111 pages
Report
Keine Angabe
Englisch
Three-Axis Fluidic Stability Augmentation System
NTIS | 1971
|Three-axis fluidic/electronic automatic flight control system - flight test report
Tema Archiv | 1975
|