Satellite: Flywheel : IÖ (t) = u(t) +w(t), Ji (t) = u(t), Measurement : y (t) = 8 ay (t) where 8 = satellite position angle, I = satellite moment of inertia (1000 kg/m²), = control torque, W = disturbance torque, v = flywheel (angular) speed, J = flywheel moment of inertia, y = measurement from the sensor, a = sensor constant (1 rad/sec), (1) Draw the block diagram of the feedback control system. (2) Suppose proportional control is used. Create a plot of the root locus with respect to the control gain, k, and characterize the stability of the closed loop system for different values of k.