Fluidic Servoactuators for Three-Axis Fluidic Stability Augmentation System

Abstract

This report covers the developmental work accomplished on a program to furnish three fluidic servoactuators for a three-axis fluidic stability augmentation system (FSAS). The servoactuators, designed to the specification for a helicopter flight control system, are classified as 'experimental' but were designed to meet safety-of-flight requirements since they were intended for flight test in a hydraulic SAS. A servoactuator controlled by a two-stage fluidic servovalve was analyzed and designed. The servoactuator hardware was fabricated and bench tested. The servoactuator bench testing, using a load simulator, showed that the fluidic servoactuator meets all of the basic acceptance test requirements. The salient features are maximum force output of 100 lb, position frequency response flat to 7 Hz when operating with MIL-H-5606 oil supplied at 1000 psig, and a quiescent flow of 0.6 gpm.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1970
Accession Number
AD0876123

Entities

People

  • Thomas S. Honda

Organizations

  • General Electric

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms
  • Sensors

DTIC Thesaurus Topics

  • Acceptance Tests
  • Actuators
  • Army Aviation
  • Assembly
  • Contracts
  • Control Systems
  • Dynamic Response
  • Fabrication
  • Flight Control Systems
  • Fluidics
  • Frequency
  • Frequency Response
  • Manufacturing
  • Simulators
  • Test And Evaluation
  • Test Facilities
  • Test Methods

Fields of Study

  • Physics

Readers

  • Electrical Engineering
  • Petroleum Engineering
  • Robotics and Automation.