This thesis investigates the application of a singular perturbation method in the design of a complete (lateral and longitudinal) multivariable, error-actuated, tracking, computer-operated digital flight controller. The aircraft model used to test the method is a hypothisized computer aided design proposed by Lockheed with augmented flight control surfaces including horizontal and vertical canards, and jet-flaps. Separate lateral and longitudinal controllers are designed for each of three flight conditions - 0.6 Mach, sea level; 0.9 Mach, 30,000 ft. altitude; and 2.3 Mach, 40,000 ft. altitude. The lateral and longitudinal controllers for each flight condition are then combined, yielding a controller for each of the three flight conditions capable of accomplishing lateral and longitudinal maneuvers. The controllers are tested by commanding seven decoupled six degree-of-freedom maneuvers and one coupled three degree-of-freedom maneuver. Figures of Merit (rise time, percent overshoot, and settling time) are presented for the decoupled maneuvers. Tests are conducted to find a single controller capable of commanding all of the decoupled maneuvers over the entire range of the three flight conditions examined.
Design of a Complete Multivariable Digital Flight Control System
1982
202 pages
Report
Keine Angabe
Englisch
Aeronautics & Aerodynamics , Computer Aided Design, CAD , Flight control systems , Computer aided design , Augmentation , Canard configuration , Degrees of freedom , Digital systems , Aircraft models , Horizontal orientation , Maneuvers , Perturbations , Sea level , Theses , Tracking , Vertical orientation , Computer operated
Multivariable Digital Flight Control Design of the X-29A
NTIS | 1984
|Robust multivariable flight control
TIBKAT | 1994
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