The Department of Electrical Engineering at the United States Air Force Academy is attempting, through one of its senior design courses, to design, build, and fly a computer controlled aircraft. The Department of Aeronautics was asked to help design the flight control system to be implemented by the on-board digital computer. The project involved building and testing a wind tunnel model of the aircraft to determine its aerodynamic characteristics, performing mass tests on the actual aircraft to determine inertia characteristics, developing a 12 degree-of-freedom nonlinear aircraft simulation computer program, and designing the actual flight control system. This report describes only the last task. A complete flight control system for a small computer controlled aircraft was designed using only yaw rate, heading, lateral load factor, airspeed, altitude, and rate of climb feedback. This multi-input multi-output control problem was done using the classical root locus technique on a linearized system model. The simulation results revealed surprisingly good performance, considering the limitation on sensors.
Flight Control System for a Computer Controlled Aircraft with Limited Sensors
1985
63 pages
Report
Keine Angabe
Englisch
Avionics , Feedback , Flight control systems , Rate of climb indicators , Input output processing , Load distribution , Flight loads , Altitude , Computer aided design , Multiprocessors , Aerodynamic characteristics , Aircraft , Airspeed , Climbing , Control , Detectors , Digital computers , Electrical engineering , Equations , Equations of motion , Fortran , Inertia , Input , Kinematics , Limitations , Linearity , Locus , Models , Multiple operation , Onboard , Output , Rates , Simulation , Yaw , Root locus technique , Digital control
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