Direct Drive Control Valve for Fly-by-Wire Flight Control System Actuators

Abstract

The development of a high force linear motor suitable for directly actuating an aircraft hydraulic power control valve used on a flight control system actuator is described. A breadboard unit was fabricated and tested and met the 80 lb. midpoint force requirement with an input of 4.4 amperes (1.1 amps/coil). A modified F-4 aileron actuator incorporating the force motor and position LVDT's met the frequency response requirements. Three sets of brassboard equipment each consisting of a modified F-4 aileron actuator incorporating a new force motor and position LVDT's and an electronic control box were designed, fabricated and tested. One set was subjected to and satisfactorily completed flightworthiness tests. The remaining are available for flight testing.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1978
Accession Number
ADA062030

Entities

People

  • D. Hogan
  • J. E. Rinde

Organizations

  • General Electric

Tags

Communities of Interest

  • Advanced Electronics
  • Air Platforms
  • Space

DTIC Thesaurus Topics

  • Amplifiers
  • Assembly
  • Contracts
  • Control Systems
  • Electronics
  • Feedback
  • Flight Control Systems
  • Flux Density
  • Frequency
  • Frequency Analyzers
  • Measurement
  • Plastic Explosives
  • Test And Evaluation
  • Test Equipment
  • Test Fixtures
  • Transducers
  • Valves

Fields of Study

  • Physics

Readers

  • Aerospace Engineering
  • Electrical Engineering
  • Robotics and Automation.

Technology Areas

  • Microelectronics
  • Microelectronics - Microelectromechanical Systems