Investigation of a Low-Cost Servoactuator for HYSAS
Final rept. Apr 1977-Mar 1978
HONEYWELL INC ST LOUIS PARK MN AVIONICS DIV
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This document covers the design and testing of a fluidic input servoactuator to perform the series servoactuator function in a helicopter hydrofluidic stability augmentation system HYSAS. The servoactuator consists of a two-stage fluidic amplifier cascade driving a conventional spool valve that positions a spring-centered cylinder. Simplicity and minimum cost commensurate with essential servoactuator performance was the design goal. A breadboard model servoactuator was designed, fabricated, and bench tested to evaluate feasibility. Servoactuator performance objectives were met at nominal supply conditions, but not over the complete operational oil temperature range.
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