Three-Axis Fluidic Stability Augmentation System Flight Test Report

Abstract

The report covers the flight test of a three-axis hydrofluidic stability augmentation system for a UH-1-type helicopter. The design goal was to improve the performance of the aircraft, without stabilizer bar, in the speed range of 60 to 120 kn. The system was installed in a UH-1C helicopter. The helicopter's hydraulic power supply was used to power the FSAS controllers and servoactuators. The system improved the performance of the UH-1C helicopter in all three axes by increasing the damping, increasing the phugoid mode period, and producing a constant vehicle rate proportional to cyclic stick input.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 1971
Accession Number
AD0734343

Entities

People

  • Donald H. Sotanski
  • Harvey D. Ogren
  • Mark E. Ebsen

Organizations

  • Honeywell International, Inc.

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Accelerometers
  • Aerodynamic Characteristics
  • Aircrafts
  • Airframes
  • Computer Simulations
  • Contracts
  • Control Panels
  • Control Systems
  • Control Systems Engineering
  • Couplings
  • Fittings
  • Flight Testing
  • Governments
  • Instrument Panels
  • Level Flight
  • Measurement
  • Test Equipment

Fields of Study

  • Physics

Readers

  • Aviation Science / Aeronautics.
  • Robotics and Automation.