A Three-Axis Fluidic Stability Augmentation System
Final technical rept. 15 Nov 1968-28 Oct 1970
HONEYWELL INC MINNEAPOLIS MN GOVERNMENT AND AERONAUTICAL PRODUCTS DIV
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The report covers the analysis, design, fabrication and laboratory tests of a three-axis hydrofluidic stability augmentation system for a UH-1-type helicopter. The design goal was to improve the handling qualities of the aircraft, without stabilizer bar, in the speed range of 60 to 120 knots. The control problem was analyzed and a system defined through use of analog computer simulation techniques. The defined system was mechanized into three separate controller packages, one for each axis. The system was subjected to temperature and vibration flightworthiness tests. The final tests conducted were closed- loop performance checks using an analog computer to simulate the aircraft dynamics.