Title
Description

This scenario uses Eulerfs rotational equations of motion to simulate the
attitude dynamics of a rigid spacecraft with optional body-fixed, constant
torques. Eulerfs rotational equations of motion is found in most of the
textbooks on spacecraft dynamics

Inputs

Ixx, Iyy, Izz Principal moments of inertia
M1,M2,M3 External torque acting in the b1 direction

Initial Condition

w1, w2, w3: Spacecraft angular velocities
q1, q2, q3, q4: Quaternions