Multivariable Control Law Design for the AFTI/F-16 with a Failed Control Surface Using a Parameter-Adaptive Controller.

Abstract

Multivariable control laws are designed for the Advanced Fighter Technology Integration F-16 (AFTI/F-16). Both fixed gain and adaptive Proportional plus Integral (PI) controllers are designed for a plant were the number of outputs are not equal to the number of inputs (rectangular plant). Simulations are conducted for a healthy and a failed aircraft model. The failure consists of reducing the left elevator by 50%. When the fixed gain controller is used for the flight control system, the simulation reveals the fact that the aircraft failure causes the output responses to diverge. If provided with a persistently exciting input the adaptive controller prevents the aircraft failure simulation from diverging and going unstable. However, additional testing and/or tuning of the adaptive controller is required to determine and enhance the stability of the adaptive controller.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1987
Accession Number
ADA189848

Entities

People

  • Julio E. Velez

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Adaptive Systems
  • Aircraft Models
  • Aircrafts
  • Algorithms
  • Closed Loop Systems
  • Control Surfaces
  • Control Systems
  • Control Systems Engineering
  • Engineering
  • Failure Mode And Effect Analysis
  • Flight Control Systems
  • Horizontal Stabilizers
  • Multiple Input Multiple Output
  • Open Loop Systems
  • Plastic Explosives
  • Simulations
  • Surfaces

Fields of Study

  • Engineering

Readers

  • Aviation Science / Aeronautics.
  • Control Systems Engineering.