Development of a Hydrofluidic Vernier Rocket Control System for Ejection Seat Stabilization.
Final rept. 1 Mar-1 Nov 76,
HONEYWELL INC MINNEAPOLIS MINN SYSTEMS AND RESEARCH CENTER
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A feasibility demonstration model of a fluidic thrust vector control FTVC system was designed, fabricated, and tested for pitch stabilization of ejection seats using the STAPAC vernier rocket. The control system includes a rate sensor, amplifier, attitude memory, and a position-controlled hydrofluidic servoactuator. The measured dynamic response of the control system closely matched the theoretical specifications for stable attitude control of the seat. The hardware was tested on a hydraulic rate table without rocket firing. Author