Heat dissipation from a satellite is principally by thermal infra-red radiation.
From:-
The heat exchange depends on several factors listed below. Solar absorptivity and infrared (IR) emissivity are surface optical properties referenced below and
www.nasa.gov
The heat exchange depends on several factors listed below. Solar absorptivity and infrared (IR) emissivity are surface optical properties referenced below and described further in Section 7.2.1: Sprayable Thermal Control Coatings, Tapes, and MLI. Thermal control of a spacecraft is achieved by balancing the energy flows as shown in Equation 1:
qsolar + qalbedo + qplanetshine + Qgen = Qstored + Qout,rad (1)
Where:-
- Qgen (heat generated by the spacecraft) depends on the power dissipation of spacecraft components.
- The amount of qsolar (solar heating) absorbed by the spacecraft depends on the solar flux, which is determined by the distance to the Sun, the surface area viewing the Sun (view factor), and the solar absorptivity of that surface.
- The amount of qalbedo (solar heating reflected by the planet) absorbed by the spacecraft depends on the planetary body, the surface area viewing the planet (view factor), and the solar absorptivity of that surface.
- The amount of qplanetshine (IR heating from the planet) absorbed by the spacecraft depends on the planetary body, the surface area viewing the planet (view factor), and the IR emissivity of that surface.
- Qout,rad (heat emitted via radiation) includes the surface area designated as radiator space, the IR emissivity of the surface, and the difference in temperature between the spacecraft radiator and the heat sink to which it is dissipating, typically and most effectively to deep space. Qout,rad also includes heat lost through insulation or other surfaces not specifically intended to function as radiators (i.e., parasitic losses).
- Qstored (heat stored by the spacecraft) is based on the thermal capacitance of the spacecraft.
The paper then goes on to describe many ways to facilitate the distribution and emission of heat from satellites.
So how much heat do we need to radiate?
Wikipedia tells me the following;-
"A single, relatively modest 36-megawatt data center rejects heat equivalent to the electricity consumption of roughly 40,000 homes. This substantial heat generation is primarily due to the energy consumed by the data center's operations."
Which seems to me to be an impossibly large amount of heat that would have to be radated into space from a satellite.
This NEC paper describes a typical satellite dissipating 300W of heat, which sounds a little less than the thermal output of the typical data centre. However they point out that space is at ~ -270 C, so if you have an efficient radiator, perhaps large amounts of thermal IR can be radiated. But surely not equivalent to 40000 houses?
So, either you divide the load up between hundreds or perhaps thousands of satellites, which sounds prohibitively expensive... or they have some technology that IS plausible to radiate that much heat. Or... they have some other technology that can do the work of the data centre while generating orders of magnitude less heat. 3D wafer-scale integration? Perhaps somethiing like Cerebras?
https://spectrum.ieee.org/cerebras-chip-cs3 . There has to be more to this than meets the eye at first look, or they would not have a remotely plausible story. It would be interesting to know how they propose to achieve the data centre in a satellite.
Well now. How about if the actual data centre is on the moon, with a direct laser network comms link to earth of the type that was recently demonstrated in the Artemis II mission. Then the earth-local satellites only need to work as comms nodes. The moon is 1.3 light seconds from earth, which isn't too bad. And the moon itself can serve as a directly attached heatsink, that you can dump the heat equivalent to 40000 homes into.