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Unformatted text preview: Flight Control Systems Test #2 Dr. Bishop - Spring 2010 Instructions: 1. Take-home examination; 2. Due Thursday April 8, 2010 during class; 3. Outside references: class notes and Dorf & Bishop textbook; 4. Questions may be addressed to Dr. Bishop or the TAs only; 5. You may use M ATLAB or LabVIEW as necessary. UAS Controller Design In this problem we consider the yaw angle autopilot control design for an uninhabited aerial system (UAS). The response of a controlled UAS 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 G ( s ) =- s + + s 3 + ( - ) s 2 + (- + ) s . As shown in Figure 1, the input to the UAS is the rudder deflection, denoted by ( s ), and the output is the yaw angle, denoted by ( s ). The parameters of the UAS depend on the flight conditions and are assumed known. For this problem, letknown....
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This note was uploaded on 09/18/2011 for the course ASE Controls taught by Professor Bishop during the Spring '10 term at University of Texas at Austin.
- Spring '10