[Q&A+] Moon Bases Locations, Lunar Internet, Sun's Companion
BONUS QUESTION STARTS AT 13:51
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Could the Sun have a binary companion, are we the only observers in the Universe, will lunar bases be close to each other? And in Q&A+, could we grow crops in asteroid regolith?
00:00 Intro
00:23 [@SantiagoT75] Can the Sun be orbiting another star we just haven’t yet noticed?
04:54 [@silasmiller4417] Are we really the only true observer in the Universe?
07:25 [@terryhardaway3285] How hard would it be to put the ISS in lunar orbit or on the Moon?
10:00 [@Space_Whales42] How close do you think the Chinese base on the moon will be to the American base?
12:14 [@Noonyuh] What sort of internet bandwidth should we expect on our moon bases?
13:51 [@Squigglyboi] Did they test growing crops in asteroid regolith?
17:01 Outro
Full livestream: https://www.youtube.com/live/jtVVWzfyB0w
Comments (5)
Great binary star answer Fraser 👍😊
Apart from the fact that there's a lot of stuff in higher orbits than the ISS, couldn't you still take it to Lunar orbit very slowly and it wouldn't cost so much. Wouldn't just a quartet of modified crew dragons be enough? So not as expensive as you said.
@Hobie, (rough estimate) it would take roughly 80-110 metric tons of propellant with the staggering ~70% efficient ion propulsion system + the energy which you could get from solar+RTG. The ISS can produce up to 120kW and the energy required for this trip would be ~1GW. So lets assume 70% efficiency and 50% of ISS power which comes to about 2.7 years of continuous thrust. The propellant is really the biggest expense. What we really need is a way to accelerate mass to a much higher velocity or created a lot of photons in a particular direction at these efficiencies. Also, please call me out if you see something I am missing here.
Couldn't the ISS (or a specially-built station) be moved use a low-energy transfer into lunar orbit with much less delta-V? And why not the lunar north pole? Lack of suitable craters?
I'm j