Title
Description

In this project, to simulate a reorientation maneuver of a rigid spacecraft
using CMGs, a configuration of 3 single-gimbal control moment gyros (CMGs)
aligned with the principal axis was used. The illustration shows the CMG
configuration used.

CMG Assembly
Inputs

Ixx, Iyy, Izz                    Principal moments of inertia
J                                  CMG inertia
A                                  CMG ginbal rate
psi                                Commanded Euler angle
phi                          Commanded Euler angle
theta                             Commanded Euler angle

Initial Condition

w1, w2, w3:                 Spacecraft angular velocities
q1, q2, q3, q4:             Quaternions
Omega 1                     Gimbal rate of CMG 1
Omega 2                     Gimbal rate of CMG 2
Omega 3                     Gimbal rate of CMG 3