The input to the satellite system of Fig. P1.4-1 is a step function c (t) = 5u(t)

The input to the satellite system of Fig. P1.4-1 is a step function θc (t) = 5u(t) in degrees. As a result, the satellite angle θ(t) varies sinusoidally at a frequency of 10 cycles per minute. Find the amplifier gain K and the moment of inertia J for the system, assuming that the units of time in the system differential equation are seconds.

Figure p1.4-1

Transcribed Image Text:

Thrusters (s) Amplifiers and thrusters K E(s) Error T(s) Torque Sensor 8(t) Fig. P1.4-1 Satellite H(s)=1+ - Js Thrusters e(s)