Yaw Axis Stability Augmentation System Flight Test Report

Abstract

The report describes the design and flight tests of a hydrofluidic yaw stability augmentation system (SAS) for an OH-58A helicopter. The design objective was to improve stability characteristics in yaw for all flight conditions from hover to 120 kn. The yaw SAS, which initially featured only high-passed yaw rate feedback, was installed in an OH-58A helicopter and flight tested in 1972. Performance at forward flight speeds was satisfactory; but at hover, yaw rates were excessive. The system was then modified to add a straight-through yaw rate feedback term. Flight tests of this configuration were conducted from October-December 1973. Results were satisfactory.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1974
Accession Number
AD0784134

Entities

People

  • Donald Sotanski
  • Harvey Ogren
  • Leroy Genaw

Organizations

  • Honeywell International, Inc.

Tags

Communities of Interest

  • Air Platforms
  • Sensors

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • California
  • Contracts
  • Control Systems
  • Electrical Circuits
  • Flight Testing
  • Governments
  • Instrumentation
  • Pressure Regulators
  • Simulations
  • Specifications
  • Standards
  • Steady State
  • Switches
  • Test Fixtures
  • United States

Readers

  • Aerospace Engineering
  • Control Systems Engineering.