Say we have a Boeing 747 whose longitudinal flight dynamics for a given flight condition may...

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Say we have a Boeing 747 whose longitudinal flight dynamics for a given flight condition may be approximated using the following state equation (uncontrolled motion; thus no need to consider the inputs and 6): w LA. Xu Xw Zu Zw 0 -91 0 = Mu+MwZu Mw + MwZw Mq + Mo 0 9 0 0 -0.006868 0.01395 1 0. 0 LAO. -0.09055 -0.3151 0 773.98 -32.2] [AU] 0 W -0.4285 0 q 0 1 0J LAO 0.0001187 -0.001026 Solve for the following, each for (a) the Phugoid mode and (b) the short period mode for this flight condition. (a) Undamped natural frequency (b) Damped natural frequency (c) Damping ratio (d) Period, in seconds You may use Matlab but show your code and your steps. Say we have a Boeing 747 whose longitudinal flight dynamics for a given flight condition may be approximated using the following state equation (uncontrolled motion; thus no need to consider the inputs and 6): w LA. Xu Xw Zu Zw 0 -91 0 = Mu+MwZu Mw + MwZw Mq + Mo 0 9 0 0 -0.006868 0.01395 1 0. 0 LAO. -0.09055 -0.3151 0 773.98 -32.2] [AU] 0 W -0.4285 0 q 0 1 0J LAO 0.0001187 -0.001026 Solve for the following, each for (a) the Phugoid mode and (b) the short period mode for this flight condition. (a) Undamped natural frequency (b) Damped natural frequency (c) Damping ratio (d) Period, in seconds You may use Matlab but show your code and your steps.