Yaw Axis Stability Augmentation System Flight Test Report
Final rept. 1 Jun 1972-30 Nov 1973
HONEYWELL INC MINNEAPOLIS MN GOVERNMENT AND AERONAUTICAL PRODUCTS DIV
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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.