Evaluation of Moderate Angle of Attack Roll of a Dual Engine, Thrust Vectoring Aircraft Using Quantitative Feedback Theory
Abstract
This thesis develops an innovative approach to the design of a flight control system for performing the large-amplitude velocity vector roll maneuver at high angles of attack (AOAs). A six degree of freedom aircraft model is developed from the fundamental nine-state equations of motion using a modified linearization technique. The MIMO (multiple-input multiple-output) Quantitative Feedback Theory (QFT) robust control design technique is then used to jointly address the system nonlinearities present in this maneuver and the changes in the system parameters due to changes in flight condition, treating them as structured uncertainty in the design of a three-axis rate-commanded control system. The development of a weighting matrix, based on the fundamentals of the aileron-rudder interconnect, aids in this design process. Nonlinear six degree- of-freedom closed-loop control system simulations demonstrate the accuracy of the developed models, the validity of the QFT designed compensator and prefilter, and the successful initiation and arrest of the velocity vector roll maneuver.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1993
- Accession Number
- ADA274118
Entities
People
- Kevin E. Boyum
Organizations
- Air Force Institute of Technology