Exercise 5.1. The longitudinal aircraft equations of motion, in linear state space form, are given by...

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Exercise 5.1. The longitudinal aircraft equations of motion, in linear state space form, are given by Usp Xu Xw 0 -g cos 00 X Usp q Zu Zw U -g sino W + Loe de = M Mw Ma 0 q Mo 0 01 0 0 where the forward speed change up, vertical speed change w, pitch rate change q and pitch angle change 0 are the state variables; elevator deflection 6 is the control variable. If the flight path angle y is defined as = = 0 W Uo and the normal acceleration at the center of gravity location is given by Leg = w - Uq where U is the constant, nominal forward velocity, obtain the C and D matrices for the above state description if 1. y is taken as the output variable, and 2. a is taken as the output variable. Z Exercise 5.1. The longitudinal aircraft equations of motion, in linear state space form, are given by Usp Xu Xw 0 -g cos 00 X Usp q Zu Zw U -g sino W + Loe de = M Mw Ma 0 q Mo 0 01 0 0 where the forward speed change up, vertical speed change w, pitch rate change q and pitch angle change 0 are the state variables; elevator deflection 6 is the control variable. If the flight path angle y is defined as = = 0 W Uo and the normal acceleration at the center of gravity location is given by Leg = w - Uq where U is the constant, nominal forward velocity, obtain the C and D matrices for the above state description if 1. y is taken as the output variable, and 2. a is taken as the output variable. Z