EVALUATION OF A MECHANICAL SERVOACTUATOR FOR FLIGHT CONTROL SYSTEMS

Abstract

A prototype mechanical servo-actuator was tested under simulated loads to determine its suitability for use in powering flight control systems for helicopters. Tests included frequency response, step response, threshold, hysteresis, endurance, and emergency operation, and were compared with similar tests of a typical hydraulic servo. Recommendations are made regarding design changes for further investigation.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1965
Accession Number
AD0623111

Entities

People

  • O. A. Knuusi
  • W. R. Sage

Organizations

  • Lockheed Martin

Tags

Communities of Interest

  • Air Platforms
  • Energy and Power Technologies

DTIC Thesaurus Topics

  • Actuators
  • Aircrafts
  • Army Aviation
  • Contracts
  • Control Systems
  • Cyclic Loads
  • Flight Control Systems
  • Frequency
  • Frequency Response
  • Helicopters
  • Hydraulic Actuators
  • Hydraulic Cylinders
  • Measurement
  • Relief Valves
  • Schematic Diagrams
  • Test And Evaluation
  • Test Fixtures

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Control Systems Engineering.
  • Robotics and Automation.