Accession Number:

ADA128579

Title:

A Lateral-Directional Controller for High-Angle-of-Attack Flight.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH

Personal Author(s):

Report Date:

1983-03-01

Pagination or Media Count:

199.0

Abstract:

A digital flight control system based on microprocessor technology has been designed, developed, and flight tested using the Avionics Research Aircraft ARA. The control system utilizes the existing microprocessor system available in the aircrafts fly-by-wire control system. The command and stability augmentation control law was developed using modern control theory and is incorporated into existing flight control computer programs. Development of the model and control law, the gain scheduling procedure, and the flight test results are presented. The objctive of the study was to provide lateral-directional stability during high-angle-of-attack flight and into the stall regime. Flight test results show that it is indeed possile to design a control system which will eliminate lateral-directional instabilities and do so at a level higher than the pilot was able to attain.

Subject Categories:

  • Numerical Mathematics
  • Computer Programming and Software
  • Computer Hardware

Distribution Statement:

APPROVED FOR PUBLIC RELEASE