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.
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