Description
An attitude maneuver via momentum transfer based on the conservation of
angular momentum was simulated. In this project, 4 reaction wheels in
a pyramid configuration was used; this configuration provides redundancy
such that if one wheels become unable to operate for some reason,
the other three reaction wheels can provide control torque in all three
direction.
Inputs
Ixx,
Iyy, Izz Moments of inertia
J
Reaction wheel inertia
RW angle Tilt angle of reaction
wheel axis
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
Omega1 Angular velocity
of RW 1
Omega2 Angular velocity
of RW 2
Omega3 Angular velocity
of RW 3
Omega4 Angular velocity
of RW 4