There's plenty of additional constraints on interplanetary trajectories. Of course the ones you mentioned first are the most driving constraints.
Concerning the others you mentioned maximum number of reignitions is a very valid constraint depending on the engine used. I would think that the G limit is not that much of a factor, as it's safe to assume the highest loads by far occur during launch and not during the actual transfer.
Here are a few more I could think of:
Usually, the satellite is designed for a specific thermal environment, which means that some trajectories are excluded because they pass through eclipse for too long or too often. Especially in the case of electric propulsion, eclipses are usually avoided as much as possible, since EP needs a lot of power, which requires sunlight for the solar array to generate power. Furthermore the high thermal loads introduced by going traveling through an eclipse can be something that needs to be avoided.
Attitude Control System Limits
The attitude control system has hard limits on the torque they're able to produce (and for how long, with regards to momentum dumping
This means that some trajectories or manoeuvres will not be possible since they require the spacecraft to rotate too quickly or for too long. Apart from the actual trajectory being flown which requires rotation of the spacecraft in order to point the thrusters in the required direction, things such as solar array orientation and communication with the earth may also require torques that are outside of the limits of the reaction wheels.
A precise estimation of the position of the satellite is needed for determining correcting manoeuvres. This is not done continuously but intermittently. When the position is being determined the thruster is usually turned off as to eliminate the uncertainties resulting from misalignment, actual thrust level vs. nominal thrust level,... This makes it possible to determine the state of the satellite much more accurately.