Landing Approach Automatic Flight Control System Design via Reduced Order Optimal Control Law

Abstract

A set of optimal feedback gains is used as a basis for designing a practical longitudinal automatic flight control system for the landing approach task. A procedure is developed to give a good first-cut design. The procedure is systematic and straightforward. The procedure is used to design two control systems for a DC-8 aircraft. In one case it is assumed that pitch, rate, normal acceleration, and longitudinal airspeed are continuously measured on board the aircraft. The second system is similar to the first with the exception that longitudinal airspeed is deleted as one of the measured variables. These systems are compared with a high-performance automatic flight control system that was designed using classical control techniques. The procedure is also used to design two control systems for a hypothetical aircraft with direct lift control capability.

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Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1973
Accession Number
AD0760125

Entities

People

  • Jerry D. Pfleeger

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Aircrafts
  • Computer Programs
  • Control Surfaces
  • Control Systems
  • Data Rate
  • Differential Equations
  • Digital Computers
  • Equations
  • Equations Of Motion
  • Flight Control Systems
  • Frequency
  • Glide Slope
  • Mathematical Models
  • Measurement
  • Probability
  • Wind Shear

Readers

  • Aviation Safety and Air Traffic Management
  • Computational Modeling and Simulation
  • Marine Hydrodynamics