Jb cg 0 0 50 At time t = 0) a satellite has zero angular velocity and inertial-to-body attitude given by q; (0) = [0 0 0 1]T, where the quaternion has scalar part LAST. The satellite's inertial matrix Jem is given by [100 0 0 60 kg m? (1) 0 0 Do the following: 1. Calculate a constant value of the angular velocity that that will re-orient the spacecraft to q}(t1) [0 1 0 0T for ti = 1200 seconds 2. Calculate the attitude history q: (t) that will take the satellite from q: (0) = {0 0 0 1]T to q: (+1) = [0 1 0 0T with the constant angular velocity above = Jb cg 0 0 50 At time t = 0) a satellite has zero angular velocity and inertial-to-body attitude given by q; (0) = [0 0 0 1]T, where the quaternion has scalar part LAST. The satellite's inertial matrix Jem is given by [100 0 0 60 kg m? (1) 0 0 Do the following: 1. Calculate a constant value of the angular velocity that that will re-orient the spacecraft to q}(t1) [0 1 0 0T for ti = 1200 seconds 2. Calculate the attitude history q: (t) that will take the satellite from q: (0) = {0 0 0 1]T to q: (+1) = [0 1 0 0T with the constant angular velocity above =