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Fluidic Vortex Valve Servoactuators An Advancement in Helicopter Flight Control Systems
- Format:
- Conference/Event
- Author/Creator:
- Vann, W. D., author.
- Conference Name:
- 1969 International Automotive Engineering Congress and Exposition (1969-01-13 : Detroit, Michigan, United States)
- Language:
- English
- Physical Description:
- 1 online resource
- Place of Publication:
- Warrendale, PA SAE International 1969
- Summary:
- 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
- Notes:
- Vendor supplied data
- Publisher Number:
- 690536
- Access Restriction:
- Restricted for use by site license
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