Accession Number:

ADA034543

Title:

Development of a Hydrofluidic Vernier Rocket Control System for Ejection Seat Stabilization.

Descriptive Note:

Final rept. 1 Mar-1 Nov 76,

Corporate Author:

HONEYWELL INC MINNEAPOLIS MINN SYSTEMS AND RESEARCH CENTER

Personal Author(s):

Report Date:

1976-12-01

Pagination or Media Count:

57.0

Abstract:

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

Subject Categories:

  • Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE