I need help with I and II please

Spacecraft Attitude Dynamics A spacecraft is orbiting around the Earth in a circular orbit. Its orientation relative to the orbital frame is described by three angles: (roll, pitch, yaw)- (p,0,v). The linearized attitude dynamics are given by +3( 1)02 where the moments of inertia of the spacecraft are (Ie, Iy, I.) (20,18, 15) kg.m2], and u (ui, u2, us) is the vector of control input torque to be used for attitude regulation. The orbit is a R 300 [km] circular orbit. The orbital rate wo (in rad/s) can be computed using ab = where the gravitational parameter for Earth is GMe, Guniversal gravitational constant, and Me is the mass of the Earth. Take as -C Me 3.9860044 18E5[km3/s2] The torque limit is lu.l s 1 [N.m] (smaller value, if possible, is preferred). Notice that the pitch dynamics are decouple from the roll-yaw dynamics. Therefore, you m ay first consider only the pitch dynamics for analysis and design. Then consider the