# How much delta v is required to keep a low Lunar orbital station stable?

I'm interested in studying where in Lunar orbit a station could be deployed. Due to mascons, Lunar orbits below about 200km will eventually decay according to this answer. Presumably, if the goal of such a station were to just be in Lunar orbit, then an orbit above 200km is preferred. However, if the goal were also to land, or conduct closer surface reconnaissance, lower orbits might be preferred.

What is the relationship between orbital altitude and delta V per day to maintain orbital stability? For simplicity I'm happy to assume a circular, equatorial orbit (although a polar orbit would make more sense for landing).