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MAE142_Lecture20

# MAE142_Lecture20 - Modes and Responses Mode Approximations...

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Modes and Responses Mode Approximations 3D Visualization Linear Model Response F-16 Spin MAE 142 NASA Image

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2 MAE 142 Body-Axis Motion Variables roll rate (p) pitch rate (q) yaw rate (r) z B y B x B surge velocity (u) fwd accel (ax) heave velocity (w) vertical accel (az) sway velocity (v) lateral accel (ay) Longitudinal Variables: ax, az, u, w, q, theta Lateral-Directional Variables: ay, v, p, r, phi, psi
3 MAE 142 F-16 Airplane Model Ignoring the position variables, the F-16 model has nine state variables and four control inputs. x t = [ u v w p q r ] Engine thrust [lb] Elevator deflection [rad] Aileron deflection [rad] Rudder deflection [rad] u t = [ T e a r ] Surge or forward speed [ft/s] Sway or side speed [ft/s] Heave or vertical speed [ft/s] Roll rate [rad/s] Pitch rate [rad/s] Yaw rate [rad/s] Bank angle [rad] Pitch angle [rad] Heading angle [rad]

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4 MAE 142 F-16 State Matrix (A) u v w p q r phi theta psi u-dot -0.0063 0 0.048 0 -18.4 0 0 -32.2 0 v-dot 0 -0.22 0 18.9 0 -747.5 32.2 0 0 w-dot -0.067 0 -0.75 0 716.4 0 0 -0.82 0 p-dot 0 -0.044 0 -2.35 0 0.41 0 0 0 q-dot 0 0 0.0012 0 -0.72 0 0 0 0 r-dot 0 0.016 0 -0.021 0 -0.31 0 0 0 phi-dot 0 0 0 1.0 0 0.026 0 0 0 theta-dot 0 0 0 0 1.0 0 0 0 0 psi-dot 0 0 0 0 0 1.0 0 0 0
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MAE142_Lecture20 - Modes and Responses Mode Approximations...

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