A Quantitative Feedback Theory FCS Design for the Subsonic Envelope of the Vista F-16 Including Configuration Variation and Aerodynamic Control Effector Failures

Abstract

Fault tolerant flight control systems for combat aircraft are an alternative to excessively redundant aircraft designs or reconfigurable control laws. However, due to the range of flight conditions within a combat aircraft's operational flight envelope, the variety of its configurations, and the unavailability of an aerodynamic data base for damaged aircraft, designing fault tolerant systems is a complicated endeavor. Quantitative Feedback Theory is a robust control design technique especially well suited to manage the structured parametric uncertainty inherent in this problem, and consequently is applied as the primary design tool for this research. Furthermore, realistic failure models are developed for the VISTA F-16 and physical saturation constraints are applied to the control effectors. The ensuing fault tolerant design is subjected to realistic control inputs and validated with the applicable MILSTD specifications.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1995
Accession Number
ADA312406

Entities

People

  • Vicent J. Cacciatore

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • C4I

DTIC Thesaurus Topics

  • Air Force
  • Aircraft Design
  • Aircrafts
  • Closed Loop Systems
  • Control Surfaces
  • Control Systems
  • Control Systems Engineering
  • Databases
  • Engineering
  • Engineers
  • Feedback
  • Flight Control Systems
  • Multiple Input Multiple Output
  • Software Prototyping
  • Standards
  • Test And Evaluation
  • Two Dimensional

Fields of Study

  • Physics

Readers

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