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

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)

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1976
Accession Number
ADA034543

Entities

People

  • R. B. Beale
  • R. V. Burton

Organizations

  • Honeywell International, Inc.

Tags

Communities of Interest

  • Sensors
  • Weapons Technologies

DTIC Thesaurus Topics

  • Actuators
  • Control Systems
  • Dynamic Response
  • Ejection
  • Ejection Seats
  • Fabrication
  • Feedback
  • Fluidic Amplifiers
  • Fluids
  • Frequency Response
  • Measurement
  • Mechanical Engineering
  • Production
  • Reliability
  • Rocket Engines
  • Simulations
  • Test And Evaluation

Fields of Study

  • Physics

Readers

  • Explosive Engineering.
  • Internal Combustion Engine (ICE) Technology.
  • Robotics and Automation.