Three-Axis Fluidic Stability Augmentation System Flight Test Report
Flight Test rept. 1 Jan-17 Dec 1970
HONEYWELL INC MINNEAPOLIS MN GOVERNMENT AND AERONAUTICAL PRODUCTS DIV
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The report covers the flight test of a three-axis hydrofluidic stability augmentation system for a UH-1-type helicopter. The design goal was to improve the performance of the aircraft, without stabilizer bar, in the speed range of 60 to 120 kn. The system was installed in a UH-1C helicopter. The helicopters hydraulic power supply was used to power the FSAS controllers and servoactuators. The system improved the performance of the UH-1C helicopter in all three axes by increasing the damping, increasing the phugoid mode period, and producing a constant vehicle rate proportional to cyclic stick input.