Fe Gas jet Inertial reference Fig.3 The angle that describes the satellite orientation must be measured wrt the inertial reference as shown (the vertical line in Fig Q3). Now suppose that the gas jet produces a torque force F about the centre of mass of the satellite as shown and consider small disturbance torques on the system, primarily arising from solar pressure acting on any asymmetry in the solar panels. If I = the moment of inertia of the satellite about its centre of mass, Mc = the control torque applied by the thruster, MD = the disturbance torque and is the reference angle, then: a. b. Produce a SMD model of the system considering the gyroscopic coupling of two rotating masses (say discs ..hint hint!) coupled by a rotational spring which has a constant k, and a rotational damper with a constant b By using the equation T = I.a, show that the total gyroscopic torque on the satellite system is given by two simultaneous equations defined as: C. Mc+MD = I + b d201 dt +k(01-02), and dt d202 (de dt 12 + b d02d01) + k (0 - 0) = 0 dt dt Regardless of whether the satellite is in a stationary geo-orbit or not, explain why the inertia reference must have zero angular acceleration.