DESIGN OF A SUB-OPTIMAL SELF-ADAPTIVE PITCH-RATE CONTROL SYSTEM FOR HIGH-PERFORMANCE AIRCRAFT.

Abstract

A technique for achieving pitch-rate control of a high-performance aircraft is developed. The resultant controller successfully adapts itself to variable aircraft parameters. The technique uses a sub-optimal approximation to the feedback gains of the optimal controller, which is a function of the aircrafts' changing dynamics. A Taylor's Series expansion in terms of the variable aircraft parameters is used to approximate the optimal feedback gains which are found by the use of a quadratic cost functional. The result is a control system which is easy to design and implement. The technique is demonstrated in the design of a control system for the F-105 Fighter Bomber. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1968
Accession Number
AD0838820

Entities

People

  • Frank T. Rooney

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Bomber Aircraft
  • Closed Loop Systems
  • Control Systems
  • Dynamics
  • Feedback
  • Fighter Aircraft
  • Fighter Bombers
  • Military Aircraft
  • Vehicles

Readers

  • Adaptive Control and Estimation with Uncertainty in Dynamic Systems.
  • Aerodynamics/Aeronautics.
  • Marine Hydrodynamics