FLUIDIC YAW DAMPER SYSTEM.
Final rept. 1 Mar 65-1 Sep 66,
HONEYWELL INC MINNEAPOLIS MN AERONAUTICAL DIV
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A fluidic yaw damper system, operating from jet engine bleed air, was designed, fabricated, and flight tested in an F101B aircraft. The purpose of the program was to demonstrate the capability of a fluid system to provide stability augmentation of a high-performance aircraft comparable to that provided by conventional electronic dampers. Major accomplishments involved 1 Matching a vortex rate sensor with an eight-stage proportional fluid amplifier to obtain the desired gain and response 2 development of a flueric gain changer which scheduled system gain as a nonlinear function of altitude 3 identification and resolution of pressure regulation, temperature compensation, and material problems relating to the use of high-pressure, high-temperature engine bleed air as a power source and 4 solution of interface, signal transmission, and response problems associated with driving a remotely located hydraulic actuator from the pneumatic system output. The system was flight tested over a representative flight envelope of the F101 aircraft and altitudes from ground level to 45,000 feet and Mach numbers from 0.3 to 1.25. Flight recordings and pilot observations showed that the fluid system provided adequate damping, turn coordination, and trim stability at all flight conditions.
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