Two designs are presented for control systems for the NASA Transport System Research Vehicle (TSRV) using integral Linear Quadratic Gaussian (LQG) methodology. The first is an integrated longitudinal autopilot/autothrottle design and the second design is an integrated lateral autopilot/yaw damper/sideslip controller design. It is shown that a systematic top-down approach to a complex design problem combined with proper application of modern control synthesis techniques yields a satisfactory solution in a reasonable period of time.
Design of Integrated Pitch Axis for Autopilot/Autothrottle and Integrated Lateral Axis for Autopilot/Yaw Damper for NASA TSRV (Transport System Research Vehicle) Airplane Using Integral LQG (Linear Quadratic Gaussian) Methodology
1990
152 pages
Report
No indication
English
Avionics , Aircraft , Aircraft control , Automatic pilots , Control systems design , Lateral control , Linear quadratic gaussian control , Longitudinal control , Transport aircraft , Controllers , Pitch (Inclination) , Axes (Reference lines) , Damping , Flight control , Research aircraft , Sideslip , Throttling , Yaw
PRECISION OPERATOR FOR AN AIRCRAFT AUTOTHROTTLE OR AUTOPILOT SYSTEM
European Patent Office | 2024
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