[3eb7988a1663]

I believe that a modern GPU will burn out immediately. Chips for space are using ancient process nodes with chunky sized components so that they are more resilient to radiation. Deploying a 3nm process into space seems unlikely to work unless you surround it with a foot of lead.

[mike_hearn]

Or cooling water/oil?

[JumpCrisscross]

> Or cooling water/oil?

Oh. You surround it with propellant. In a propellant depot.

[mike_hearn]

Hah, kill three birds with one stone? The satellites double up as propellant depots for other space missions, that just happen to have GPUs inside? And maybe use droplet radiators to expel the low grade heat from the propellant. I wonder if that can be made safe at all. They use propellant to cool the engine skins so... maybe?

[shagie]

You're describing cryogenic fuels there and dumping heat into them. Dumping heat (sparks, electricity) into liquid oxygen would not necessarily be the best of ideas.

Dumping heat into liquid hydrogen wouldn't be explosive, but rather exacerbate the problem of boil off that is already one of the "this isn't going to work well" problems that needs to be solved for space fuel depots.

https://en.wikipedia.org/wiki/Orbital_propellant_depot

> Large upper-stage rocket engines generally use a cryogenic fuel like liquid hydrogen and liquid oxygen (LOX) as an oxidizer because of the large specific impulse possible, but must carefully consider a problem called "boil off", or the evaporation of the cryogenic propellant. The boil off from only a few days of delay may not allow sufficient fuel for higher orbit injection, potentially resulting in a mission abort.

They've already got the problem of that the fuel is boiled off in a matter of days. This is not a long term solution for a place to dump waste heat. Furthermore, it needs to be at cryogenic temperatures for it to be used by the spacecraft that the fuel depot is going to refuel.

> In a 2010 NASA study, an additional flight of an Ares V heavy launch vehicle was required to stage a US government Mars reference mission due to 70 tons of boiloff, assuming 0.1% boiloff/day for hydrolox propellant. The study identified the need to decrease the design boiloff rate by an order of magnitude or more.

0.1% boiloff/day is considered an order of magnitude to large now. That's not a place to shunt waste heat.

[mike_hearn]

Thanks, great answer.