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Fluidic Vortex Valve Servoactuators — An Advancement in Helicopter Flight Control Systems
ISSN: 0148-7191, e-ISSN: 2688-3627
Published February 01, 1969 by SAE International in United States
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An experimental fluidic servoactuator system recently developed for the U. S. Army Aviation Materials Laboratory is described. These actuators, developed for the pitch, roll, and yaw channels of a helicopter stability augmentation system, utilized a vortex valve amplifier circuit to replace the more conventional spool valve, actuator combination.
Vortex amplifiers with high turndown ratio, good linearity and low hysteresis were developed using MIL-H-5606 hydraulic fluid. Test results for the actuator system showed excellent static and dynamic performance.