1.4-1. The satellite of Section 1.4 is connected in the closed-loop control system shown in Fig. P1.4-1. The torque is directly proportional to the error signal. LO(S)] is the commanded attitude angle. (a) Derive the transfer function (s)/(s), where (t) = (b) The state equations for the satellite are derived in Section 1.4. Modify these equations to model the closed-loop system of Fig. P1.4-1. Thrusters e(t) Thrusters