I am working in a team designing a nano-satellite for a remote sensing mission. I am a computer engineering student so I am not really familiar with space stuff.

The problem is that we have been told that an overheating problem could occur, if we put the de-orbiter (gossamer sail) right next to the avionics EPS (Electrical Power System) as shown in the picture. what do you recommend to avoid such a problem? The satellite is a 3U (3 Unit) satellite with a mass around ~2 Kg. The mission is supposed to last 5 years. The altitude is 604.5 Km. The inclination is 98.43 degree. We don't use the sail to control and it's deployed as soon as it's in the nominal orbit

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    $\begingroup$ This would depend quite a bit on the choice of materials for the gossamer sail deorbiter. Also, is the sail deployed as soon as you're in your nominal orbit and you'll also use it to maintain attitude, or will it be tucked in for longer time? Could you please edit your question to include that info? Cheers! $\endgroup$ – TildalWave Dec 29 '14 at 14:47

Spacecraft thermal control analysis employs modelling programs that can analyze combinations of conduction, convection, and radiation heat transfer in complex structures. An example is Sinda by MCS Software. I have no association with MSC Software but I did work on thermal analysis problems for the Apollo Service Model in the early 1960s using primitive versions of what are now much more advanced (I am sure) software.

Complex structures are analyzed by developing thermal networks and are solved through analogies to electrical networks. Using these programs you can analyze a proposed system structure throughout a mission cycle including transient direct solar, earth emitted and earth reflected radiation as the satellite transits in an orbit in some orientation. The thermal models consider as well internal thermal generation. Conduction/radiation paths between components would be constructed from the proposed geometry. If the proposed component layout shows a thermal problem, i.e. some structure gets too hot or cold, you can examine the need to relocate the component, alter thermal pathways, or provide some means of thermal control. You can then re-analyze your changes.

For the Apollo service module verification of the thermal calculations was so important that a thermal simulator was built that housed a service module and simulated radiant thermal inputs to simulate various attitudes in orbit and lunar transcoast. Comparison between calculations and simulations was not too bad even then. Now I'm sure it would be much better.

I don't know the magnitude of your nano-satellite program but some thermal analysis is likely necessary using Sinda or some other equivalent to provide confidence that components can remain within satisfactory temperature ranges.

As a preliminary step take a look at the proposed layout, heat inputs, heat generation and do some simple analyses to see if there is some obvious likely problems.


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