Design a compensator using one stage of lead compensation

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Reference no: EM13227649

The heading control of a traditional bi-wing aircraft is represented by the block diagram shown.

1. Determine the minimum value of gain K when Gc(s)=K, so that the steady-state effect of a unit step disturbance Td(s)=1/s is less than or equal to 5% of the unit step (y(inf)=0.05).

2. Determine whether the system using the gain of part 1 is stable.

3. Design a compensator using one stage of lead compensation, so that the phase margin is 30degrees.

4. Design a two-stage lead compensator so that the phase margin is 55degrees.

Reference no: EM13227649

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