1969-02-01

Fluidic Vortex Valve Servoactuators — An Advancement in Helicopter Flight Control Systems 690536

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.

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