Accession Number:

ADA058514

Title:

Stabilization Techniques for Improved Response of The F-15 Aircraft.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1978-06-01

Pagination or Media Count:

130.0

Abstract:

The purpose of this study was to show that by moving an aircrafts center-of-gravity aft of the aerodynamic neutral point, thus making it statically unstable, the use of a feedback control system produces a more responsive stable aircraft. Pitch rate, normal acceleration, and angle-of-attack rate were used as the feedback parameters in a pitch orientational control system having two feedback loops. The inner loop was used to improve the dynamic response characteristics and the outer loop to stabilize the aircraft. While all three types of feedback control were able to improve the aircraft response, the pitch rate feedback system had the least response variation between five different flight test conditions and provided the best overall system improvement. Author

Subject Categories:

  • Aerodynamics
  • Attack and Fighter Aircraft

Distribution Statement:

APPROVED FOR PUBLIC RELEASE