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