Iz1. A spacecraft is launched into a low Earth orbit. The spacecraft principal moments of inertiaare IT = 98 kg.m², Iy 102 kg.m², I₂ = 150 kg.m². For stability, the launch vehicle deploysthe spacecraft such that it is in a major axis spin when released, with wz = 0.5 rad/s. Becauseno deployment is perfect, the spacecraft also has some angular velocity about the other twoprincipal axes, given by we = 0.1 rad/s, wy = 0.02 rad/s. Making appropriate approximations:(a) Describe the resulting spacecraft attitude motion if there are no disturbance torques.(b) Determine the nutation angle.(c) Determine the precession rate.

Given:Ix = 98 kg·m²Iy = 102 kg·m²Iz = 150 kg·m² = 0.1 rad/s = 0.02 rad/st = time period (for this…

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