Problem 1. Fig. 1 shows the roll-angle dynamics of an aircraft (1): roll-angle 0 = w w = -.875 - 207 w = roll-rate * = -

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Problem 1 Fig 1 Shows The Roll Angle Dynamics Of An Aircraft 1 Roll Angle 0 W W 875 207 W Roll Rate 1 (99.56 KiB) Viewed 24 times

Problem 1. Fig. 1 shows the roll-angle dynamics of an aircraft (1): roll-angle 0 = w w = -.875 - 207 w = roll-rate * = -507 +504 Tapplied torque where u is the control input. Define state vector as x = [0 w t], and yp = 0. a) Find state space model of the aircraft roll-angle dynamics. b) Write LQ-servo (without integral) simulation program such that is controlled to follow Odes using MATLAB (hint: G = Iqr(A,B,Q,R); [y,t,x] = Isim(sys,r,t,xo);). Assume that all initial conditions are zero and des = 11/6. c) Plot all state variables and input. [1] J. V. Vegte. Feedback Control Systems. Prentice Hall, New Jersey, 3rd edition, 1994.