Aldrin Non-Cycler.
Edit: Forgot that Aldrin Cyclers are for Earth-Mars
For context, this idea is only when there is plenty of fuel manufacturing on the moon.
An Aldrin Cycler is great, but you still need a spacecraft with enough fuel and delta V to rendevous and dock to it. If we have fuel manufacturing on the Moon, then wouldn't it be better to offload the delta V requirements onto the cycler itself. This is hence not a cycler, but rather an Earth-Moon shuttle. Naturally, for efficiency, we also take advantage of aerobraking to help slow the craft down.
The mission profile is as follows. A crew launches to a space station, along with cargo supplies. This could be in a single, or multiple launches. Once there, the crew and supplies are transfered into the transfer craft, which is almost completely full of Hydrogen and Oxygen fuel. This necessitates technology to stop it from boiling off.
The transfer craft undocks, positions itself, and conducts a Trans-lunar Injection (TLI) burn, and heads on its way to the Moon. Once at the Moon, it conducts a Lunar Orbit Insertion (LOI), and rendevous with a lunar space station in Low Lunar Orbit. This is very likely a polar orbit, so that the landers can ferry supplies and crew down to the South Pole base, and ship fuel back up to the lunar transfer craft, refueling it.
Once the transfer craft has been refueled, and the crew has rotated between the base and the space station, the craft undocks, conducts Lunar Orbit Departure (LOD), and heads back to Earth.
The craft would be in the shape of a slight cone, with the engines at the wider end. These engines, with nozzle extensions for vaccum efficiency, would retract within the cone, and be protected by a ceramic heat shield, with a second layer of active cryogenic cooling using liquid Hydrogen. The craft would enter the Earth's atmosphere wide end first, with the crew section at the thinner end. The trajectory would be such that it takes off enough speed that the craft skips off the atmosphere, and reaches an Apogee of 400-500km, where it can conduct a perigee raise maneuver (EPR), and enter a stable circular orbit, before rendevousing with the space station yet again. The crew can then return to Earth in the capsule/s that their replacement crew launched in a week earlier.
The transfer craft would be quite large, needing a fair amount of Delta V. I believe the amounts would be 3400m/s for TLI, 900m/s for LOI, 900m/s for LOD and at least 300m/s for Earth Perigee Raise. But, I believe that even with this mission profile, the benefits of not haivng to launch nearly as much fuel, and the reliance instead on lunar fuel supply, with its far smaller gravity well, would make for a cheaper mission profile.
All of this assumes an existing lunar fuel manufacturing, using deposits of water ice at the South Pole to produce Hydrogen and Oxygen fuel, presumably also using that fuel to propell the reusable lunar landers and maintain orbit for the lunar space station. This is hence clearly many decades off, which is why I post it here in Sci Fi