Space Shuttle Heat Transfer Question

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SUMMARY

The discussion centers on heat transfer mechanisms for the Space Shuttle, specifically focusing on emissivity in space and heat generation during re-entry. It is established that the emissivity of space is approximately 1.0, with a temperature around 2.4 Kelvin. The primary source of heat during re-entry is attributed to air compression rather than friction, with convection playing a significant role as the shuttle interacts with the high-velocity air. Solar radiation intensity at the top of the Earth's atmosphere is noted to be about 1500 W/m².

PREREQUISITES
  • Understanding of heat transfer principles, including radiation, conduction, and convection.
  • Familiarity with the Stefan-Boltzmann equation for calculating thermal radiation.
  • Knowledge of emissivity and its impact on thermal performance.
  • Basic concepts of atmospheric physics, particularly regarding air compression and temperature.
NEXT STEPS
  • Research the Stefan-Boltzmann equation and its applications in thermal radiation calculations.
  • Explore emissivity measurements for various materials used in aerospace engineering.
  • Study the principles of convective heat transfer in high-speed aerodynamics.
  • Investigate the effects of solar radiation on spacecraft design and thermal protection systems.
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Aerospace engineers, thermal analysts, and students studying heat transfer in space applications will benefit from this discussion.

anthonyj915
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From what I gathered in Heat transfer, an object in space, ie space shuttle, can only lose cabin heat through the means of radiation (no conduction or convection off the surface...) So how would one go about determining what the emissivity is in space. Obviously there will be objects that are hotter (sun) but there is a lot of nothing.

Anyone have some insight as to how to ball park that figure?

The other think i was thinking about, was on re-entry the space shuttle gets hot. What is causing this heat? I know its the friction between the air and the shuttle, but doesn't the air flowing past also aide in the Convection heat transfer?

Thanks
 
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The ball-park figure for space itself is Zero and you treat the sun separately and since it is so much hotter than objects such as the space shuttle, you just use the solar radiation flux (340w/m^2 iirc). For an object in orbit around the earth, you'd probably treat the Earth separately as well and use the S-B equation.

For re-entry, the heat is more from the compression of the air than from friction, so since the air itself is getting hot, the convection is what heats up the shuttle.
 
I believe the original post asks about the emissivity of space, which is probably about 1.0, and a ballpark figure for the temperature of space is about 0 (2.4 kelvin to be a little more precise). You will also need to know the emissivity of the shuttle itself, along with the surface area.
BTW, Isn't the intensity of solar radiation about 1500 w/m^2 at the top of the Earth's atmosphere?
As for heating during re-entry, even though the air molecules are traveling at a relatively slow speed (in Earth reference frame) which is consistent with them having a low temperature, from the shuttles' frame of reference, they are moving quite fast and hence have a very high temperature. In effect, the shuttle is surrounded by very hot gas and so it gets heated. Of course, the gas is mostly moving in a single direction, as compared to randomly for a "normal" hot gas.
 

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