A SELF-ADAPTIVE AIRCRAFT PITCH RATE CONTROL SYSTEM EMPLOYING DIFFERENCE EQUATIONS FOR PARAMETER IDENTIFICATION

Abstract

In a high performance aircraft in Mach number, angle of attack and altitude can cause a large variation in the short-period transfer function. To provide the pilot with a constant pitch rate control characteristic an airborne computer, with inputs of elevator deflection angle and pitch rate is used to identify and track changes in the elevator effectiveness. Simulation with an aircraft whose elevator effectiveness varied over a range of 240:1 showed that the desired loop gain was maintained within a factor of two for both pilot command inputs and for random wind gust disturbances of root-mean-square magnitude 20 ft/sec. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1967
Accession Number
AD0665126

Entities

People

  • Ian S. Parry

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • C4I
  • Ground and Sea Platforms
  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Accuracy
  • Adaptive Control Systems
  • Adaptive Systems
  • Air Force
  • Aircrafts
  • Airframes
  • Atmospheric Motion
  • Computer Programs
  • Computers
  • Control Systems
  • Difference Equations
  • Differential Equations
  • Digital Computers
  • Equations Of Motion
  • Mach Number
  • Resonant Frequency
  • Supersonic Transport Aircraft

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Aerodynamics/Aeronautics.
  • Aviation Science / Aeronautics.