Design of a Multiple Input-Multiple Output Flight Control System Containing Uncertain Parameters.

Abstract

A quantitative feedback synthesis technique is used to design a lateral flight controller for a horizontal translation maneuver. The technique, which is performed in the frequency domain, uses feedback to achieve the desired system response despite parameter variation. A computer program generates an aircraft model for several flight conditions. The aircraft model includes canards (vertical and horizontal), ailerons, rudders, maneuvering flaps and jet flaps. These models are simplified to three input-three output systems. A single controller is designed for all of the flight conditions. Robustness is accomplished by considering parameter variation throughout the design method. The design is simulated and the results presented. The method used is presented. A discussion of the results is presented, including suggestions on improvements to the design. Recommendations for further investigations are provided.

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1984
Accession Number
ADA174510

Entities

People

  • David L. Segner

Organizations

  • Wright Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Control Surfaces
  • Air Force
  • Aircrafts
  • Applied Mathematics
  • Artificial Intelligence
  • Closed Loop Systems
  • Computational Science
  • Computer Programs
  • Computer Simulations
  • Control Surfaces
  • Control Systems
  • Differential Equations
  • Feedback
  • Flight Control Systems
  • Frequency
  • Multiple Input Multiple Output
  • Plastic Explosives

Fields of Study

  • Physics

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Aerodynamics/Aeronautics.
  • Computational Modeling and Simulation