- 3 A Linearized Model Of A Cessna Citation Aircraft At An Altitude Of 5000 M And Velocity Of 128 2m Sec Is Given By 1 2 1 (15.18 KiB) Viewed 81 times
Angle of attack horizon Pitch angle Figure 1 Angle of attack and pitch angle. where x1 is the angle of attack (radians), 12 is the pitch angle (radians), 13 is pitch rate (rad/sec), and 14 is the altitude (m). The control input u is the elevator angle (in radians). The elevator is a control surface on the horizontal tail that can be angled down (positive angle) or angled up (negative angle). A positive elevator angle makes the plane tail rise, causing the aircraft to pitch down. Note that the autonomous system has two zero eigenvalues and is thus unstable. The dynamics given above correspond to the matrices A, B, in the state feedback problem (c.f. Slide 4, Ho state feedback control). Derive the remaining matrices (B1, C1) such that i) the regulated output z is the pitch angle and ii) the exogenous disturbance w is wind velocity which only affects the pitch rate (which it amplifies by a factor of 1.5). You may use D11 = 0.85 and D12 = 0.3. Design a Ho state feedback controller that minimizes the map from exogenous disturbance w to z. Provide your code and the optimal closed-loop norm. In addition, generate an artificial signal to mimic wind speed and simulate the closed-loop behavior. [6]