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.