Question

The roll angle control of an airplane is achieved by using the torque developed by the ailerons, as shown below. A linear model of the roll control system for a small experimental aircraft is shown also below, where Vi(t) is the flow of fluid into a hydraulic cylinder. Given the following dynamic electrk-mechanical (aerodynamics) system. R, 1. Draw the pole-zero diagram once R,-?5. R/ 1, and C: 0.5. Hence confirm it by MATLAB ii. What do you think about the system behavior ?, is it damped or Marginally stable ? Or? ilil Find a good set of parameters to give an over damped behavior. v. For a unit impulse input, obtain the corresponding system output in time domain. For a unit step input, obtain the associated output in time domain. vi. Comment on the shape of the output in both cases of (w) and (v). vil. What is the root-locus of the this system? vil. Finally simulate the system in Matlab (Simulink) and confirm your results, for both (v) and

(please answer)

viii. Finally simulate the system in matlap (simulink) and confirm your results. for both (iv) and (v)

Answer 1

given beloo am hln Lo SC Sレ SC Sc & Given values 2S+22s+2

0、539-53ナ -6.83 -o-g-구구 -9,1七 -0.2 구6七