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Unformatted text preview: Flight Control Systems Test #2 Dr. Bishop - Fall 2007 Instructions: 1. Take-home examination; 2. Due Friday November 9, 2007; turn in to Dr. Bishop or Nolan (WRW202) 3. Outside references: class notes and Dorf & Bishop textbook; 4. Questions may be addressed to Dr. Bishop or the TA only; 5. You may use M ATLAB or LabVIEW as necessary. UAV Yaw Controller Design In this problem we consider the yaw angle autopilot control design for an uninhabited aerial vehicles (UAV). The response of a controlled UAV must be accurate and fast in the presence of variations in airspeed and altitude . A simplified lateral dynamics model of the aircraft (assuming constant aerodynamic coefficients) in a level-flight cruise condition is given by ˙ β ( t ) = ω ( t ) + αβ ( t )- κδ ( t ) ˙ ω ( t ) =- γβ ( t )- λω ( t )- νδ ( t ) ˙ φ ( t ) = ω ( t ) where the states of the system are φ ( t ), ω ( t ), and β ( t ), the yaw angle, yaw angle rate, and angle of sideslip, respectively. The rudder deflection is de-angle rate, and angle of sideslip, respectively....
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This note was uploaded on 09/01/2010 for the course ASE 270L taught by Professor Dr.bishop during the Spring '10 term at University of Texas.
- Spring '10