"Assume lots of delta V"
If you're using chemical rockets that would mean propellent mass comparable or greater than the asteroid mass. A quick chart:
Exhaust velocity for hydrogen/oxygen is about 4.4 km/s. 3/4.4 = ~ln(2). So every 3 km/s added to the delta V budget about doubles over all mass.
It's quite plausible to have solar powered hall thrusters with an exhaust velocity of 30 km/s. However given Hall thrusters and solar panels of reasonable mass, acceleration is excruciatingly slow even for a relatively low mass asteroid.
Hasnain, Lamb and Ross wrote a paper Capturing Near Earth Asteroids Around Earth.
Hasnain, Lamb and Ross look at two delta Vs:
1) Delta V to nudge an asteroid's heliocentric orbit so the rock passes through the earth's sphere of influence.
2) Once in Earth's sphere influence, the delta V to make the hyperbolic orbit an elliptical capture orbit about the earth.
There are near earth asteroids that already pass close to the earth/moon system. If nudged early enough in their orbit they can be made to pass through the earth's sphere of influence with relatively little delta V. And there is a lot of time to accomplish the nudge so high ISP ion engines can be used to accomplish the first step.
Once in earth's sphere of influence and if the moon is in the right position, a lunar swing by can be used to shed velocity making a hyperbolic orbit into an elliptical capture orbit.
Above is an illustration how a lunar swing by can drop an asteroid's velocity from around 2 km/s in the lunar neighborhood to 1.2 km/s which is below earth's escape velocity at that distance from earth.
If I understand the Keck Report correctly, they say it could take .17 km/s to park a rock in an earth capture orbit and they say it could be done with Hall Thrusters.
On the bottom of page 15 of the Keck Report they talk about safety. They specify retrieving a small carbonaceous asteroid that would burn up harmlessly in the upper atmosphere should it go off course and impact the earth.
The also specify parking the rock in a loose lunar orbit so it'd be a good distance from earth, another safeguard against impact.
These safety measures work against your scenario of an ore body in low earth orbit.
Also to get from a loose escape orbit to a low earth orbit takes a lot of delta V. A general rule of thumb going from coplanar orbits with a low thrust trajectory is subtract high orbit velocity from low orbit velocity. See Adler's answer to my question General guideliness for modeling a low thrust ion spiral
So this means you need a delta V budget in the neighborhood of 6 or 7 km/s to spiral down to LEO. If using chemical that would mean using about quadruple the mass of the asteroid in propellent. If using ion I'm guessing it would take centuries to spiral down.
So I'd say it's not plausible to park an asteroid in LEO.
It is plausible, in my opinion, to park a rock at EML2. Which would be a great place for a water rich carbonaceous asteroid. A potential propellent source at EML2 would be a possible game changer.