How would you figure out the fuel cost or delta V for spinning up a S/C to match the orbital period of 27.32 days (moon orbit)? Given that the S/C is initially not rotating about any axes.
For simplicity say the S/C is in an equatorial orbit and only needs to rotate about one axis. If the max torque is 40 N-cm, max thrust is 3N, total mass is 2kgs and ISP is 200s. Just the general equations are sufficient.