Only Question 2 but use 1 for reference

Question 1 Simplified differential equations describing the pitching dynamics of the Apollo 11 Lunar Lander are 0(t) = 4(t) Iq(t) = u(t) where t is time in s, 6(t) is the pitch angle in rad, qft) is the pitch rate in rad/s, u(t) is the pitch moment input, and I = 16, 922 kg-m is the pitch moment of inertia (which is assumed here to be constant). Take the initial conditions (0) = 0 and 90) = 0, which corresponds to the lander being in its nominal upright orientation for touchdown. At least in the short term, suppose we want to reorient the lander to change the trajectory such that 8(t) = 0d and q(t) = 0 for all ts