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With experience of the ISS and hopefully soon the Orion and SLS, it seems to me that a Lunar Orbital Station (LOS) could be the next step.

What are the main challenges of building and running a LOS compared to ISS? (radiation, eclipses, time delay, travel distance, gravity field...)

Could modules from the ISS be disconnected and tugged to Lunar orbit? Could the asteroid tug of the ARRM be used to do it?

What kind of orbit would be suitable for a LOS, given the heterogenous Lunar gravity field and the desire for logistics with Earth and the Lunar surface (esp. poles and far side)? What are the pros and cons of a Lagrange point 60,000 km away from the Moon compared to a Lunar orbit?

In what way would a Lunar orbital station be useful? Both before and after there is a Lunar lander available.

Roscosmos has a vague plan to build a LOS in the 2030's.

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Pros for LOS

It's possible lunar orbital infrastructure could make entering and leaving our earth moon neighborhood less difficult. It could also make access to the lunar surface less difficult.

The notions I'm tossing out are more or less science fiction but not prohibited but the laws of physics.

Earth Moon Lagragne 2 a.k.a. EML2 is a very interesting location. It is quite close to C3=0 yet close to the earth in terms of delta V as well as travel time. If getting to Mars or a near asteroid is the goal line, EML2 is on the 10 yard line, energetically speaking.

EML2 is also about 2.5 km/s from the moon. They may be rich volatile deposits at the lunar poles. If so, the lunar cold traps might supply EML2 with propellent as well as life support consumables.

But EML2 is only quasi stable. A staging platform at EML2 would be like a ball balanced on top of a hill. A slight nudge in any direction could send it rolling. So there is a station keeping expense to keep a station parked at EML2. EML2 station keeping wouldn't take much delta V, on the order of tens of meters per second. But even this small delta V can be expensive if your station is massive.

Retrograde lunar orbits can be stable, especially if the orbit is within 40,000 km of the lunar center. Get too close to the moon and the orbit can be destabilized by Mascons. If we parked a carbonaceous ivuna asteroid at a 40,000 km retrograde lunar orbit, it would be about .4 km/s from EML2. Such asteroids are thought to be rich in water and organic compounds. Another potential source of propellent and life support consumables.

Asteroidal mass could also be used for radiation shielding. An important consideration since lunar orbit doesn't enjoy protection from earth's magnetic field.

An asteroid parked in a high retrograde lunar orbit could also be a momentum bank for a tether:

enter image description here

In this illustration the asteroid is parked at a balance point 24,200 from the moon's center. Tether below is pulled taught by gravity that exceeds centrifugal force. Tether above the balance point is held aloft by centrifugal force. Releasing a payload from this tether top at the correct time could send a payload to a perigee just above geosynchronous orbit. Releasing a payload from this tether foot would send a payload to the lunar surface. On reaching the surface, a payload would need to shed 2.23 km/s for a soft landing. So this tether could substantially cut the delta V for parking in lunar orbit or reaching the lunar surface. I talk about this as well as other stations/tethers at my blog post Orbital Momentum as Commodity.

Answers to some of the your other questions

The I.S.S. isn't designed to be moved big distances. So I don't think hauling I.S.S. modules is an option.

Parking a rock in lunar orbit ARM style takes a large power source, ion thrusters, and software for the rock fetcher to rendezvous with an inanimate object. Doable in my opinion, but a Keck style vehicle doesn't presently exist.

In terms of delta V, time and distance, lunar orbit is more distant from the earth's surface. Getting stuff to LEO takes about 9 km/s. Getting stuff to lunar orbit from earth takes about 13 km/s.

So building a LOS would be harder than the ISS.

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  • $\begingroup$ If we are assuming we can pick up asteroids, that's a whole different world, in which a lunar base makes some more sense. Still, interesting answer. $\endgroup$
    – PearsonArtPhoto ♦
    Jul 22 '15 at 16:14
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    $\begingroup$ I remain enthustiastic about the ARM proposal even though I'm in a small minority. Among my circles Jon Goff and I are the only ones enthused about asteroid retrieval. I've gone over the Keck report several times. To me their assumptions seem very conservative and doable. Hall Thrusters are a tried and true technology. The Keck solar array wings are quite plausible, they assume a conservative alpha. $\endgroup$
    – HopDavid
    Jul 22 '15 at 16:30
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Building a Lunar orbiting station would be really hard. Maintaining it in orbit would require constant care, far more than is required in LEO. Getting supplies there would be difficult. The radiation environment is much worse than at Earth.

And there's the issue of what one would do with the station. I'm not convinced that there is any utility in a lunar station, aside from tourism and as a stopover point between lunar landing missions. Any science that can be done from lunar orbit could be either better done by an unmanned satellite, or done in Earth orbit.

I'm convinced that the time delay would not be a significant issue, nor would eclipses. Neither is much longer than on Earth. The ISS could be moved to lunar orbit if required, although I suspect the ISS would be better off remaining where it is, and just building a new station.

In the more credible science fiction books, lunar stations aren't used, but stations at the L4/L5 Earth/Lunar points are used. I think that would be a better option overall.

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  • $\begingroup$ "Maintaining it in orbit would require constant care, far more than required in LEO." Not necessarily true. A retrograde lunar orbit below 40,000 km but well above the mascons is stable. It would require less maintenance than the I.S.S. $\endgroup$
    – HopDavid
    Jul 21 '15 at 21:43
  • $\begingroup$ I wasn't aware of that, but it still doesn't give many benefits when compared to other types of orbits, perhaps a higher LEO orbit, for instance. Being further from the Moon just reduces the utility of such a station. $\endgroup$
    – PearsonArtPhoto ♦
    Jul 22 '15 at 15:07
  • $\begingroup$ See my answer where I suggest the station is an anchor mass at the balance point of a vertical tether. Speed of the tether foot is ωr where ω is angular velocity and r is tether foot's distance from moon's center. A higher orbit for the balance point results in a smaller ω. If the tether foot in my example were extended to within 100 km of the lunar surface, it would be moving about 30 meters/second with regard to the lunar surface. $\endgroup$
    – HopDavid
    Jul 22 '15 at 16:08

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