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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 ) =- νs + κγ + να s 3 + ( λ- α ) s 2 + (- αλ + γ ) s . As shown in Figure 1, the input to the UAS is the rudder deflection, denoted by Δ( s ), and the output is the yaw angle, denoted by Φ( s ). The parameters of the UAS depend on the flight conditions and are assumed known. For this problem, letknown....
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- Spring '10
- rudder deflection, step input, Dr. Bishop