Fault-Tolerant Actuation Concept for a Research Test Aircraft.

Abstract

The fault-tolerant actuation system uses 4 active electrical control paths to control a dualized hydraulic actuator. A simple failure management system operates in conjunction with some of the inherent features of the basic system to provide a failure tolerance level of dual fail-operate for the electrical control paths. The concept is characterized by its fundamental simplicity and inherent ability to tolerate failures. The concept has application to fixed wing as well as rotary wing aircraft. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1980
Accession Number
ADA093113

Entities

People

  • Delbert E. Haskins

Organizations

  • Bell Flight

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Energy and Power Technologies
  • Sensors

DTIC Thesaurus Topics

  • Actuators
  • Aircrafts
  • Circuit Boards
  • Control Systems
  • Electronics
  • Fail Safe
  • Failure Mode And Effect Analysis
  • Helicopters
  • Hydraulic Actuators
  • Measurement
  • Power Supplies
  • Rotary Wing Aircraft
  • Solenoid Valves
  • Test And Evaluation
  • Test Equipment
  • Test Stands
  • Vehicles

Readers

  • Aerospace Engineering
  • Electrical Engineering
  • Robotics and Automation.