Thermal Management Question in Spacecraft

In summary, we discussed a question about thermal management in spacecraft, specifically calculating the size of a radiator needed for an instrument that dissipates 10W and needs to be kept below -20°C while orbiting Mars. Using a formula, we found that the size of the radiator should be about 0.105m^2.
  • #1
Tanzim Kawnine
1
0
Hello guys,

Below I am presenting a question related to thermal management in spacecraft . Perhaps many of you might find it interesting! And this could be a real-life problem for thermal engineering in a spacecraft . So, the question is following:

An instrument dissipates 10W and, in order for its detector to operate effectively, must be kept below -20°C. Its baseplate has a contact area of 175mm by 125mm and is bolted to a radiator with a chotherm interface. If the spacecraft is orbiting Mars (at a sun distance of 1.5 AU) and the radiator is facing the planet, estimate the size of radiator required. Assume the following :
• Albedo of Mars is 0.29 and its temperature is -60°C. The solar constant is
1369 W/m2
• The interface conductance between the unit and the radiator is 250 W/(m^2)*K
• Emissivity of the radiator is 0.8, absorptivity is 0.08


Also, An uncertainty margin of 10°C is to be used!

I found out the size of the radiator should be about 0.105 m^2.
What about yours? I would appreciate your help here. Thanks in advance.

Regards
TK
 
Physics news on Phys.org
  • #2
Thread closed temporarily for Moderation...
 
  • #3


Hi TK,

Interesting question! To calculate the size of the radiator required, we can use the following formula:

Q = A * (T_h - T_c) / (1/ε - 1/α)

Where:
Q = heat dissipated by the instrument (10W)
A = contact area of the baseplate (175mm * 125mm = 0.021875m^2)
T_h = temperature of the baseplate (assumed to be -20°C)
T_c = temperature of the radiator (assumed to be the same as Mars' temperature, so -60°C)
ε = emissivity of the radiator (0.8)
α = absorptivity of the radiator (0.08)

Plugging in these values, we get:

10 = 0.021875 * (-20 - (-60)) / (1/0.8 - 1/0.08)

Solving for A, we get A = 0.105m^2.

So, it looks like your calculation is correct! Good job. It's important to also consider the uncertainty margin of 10°C, so the actual size of the radiator may need to be slightly larger to account for this.

Does anyone else have a different approach or calculation? Let's discuss!
 

FAQ: Thermal Management Question in Spacecraft

1. How important is thermal management in spacecraft?

Thermal management is crucial in spacecraft as it ensures that the internal temperature is regulated, preventing sensitive components from overheating or freezing. It also helps maintain the overall structural integrity of the spacecraft.

2. How is thermal management achieved in spacecraft?

Thermal management in spacecraft is achieved through a combination of passive and active systems. Passive systems include insulation, coatings, and radiators, while active systems involve the use of heaters, coolers, and heat pipes.

3. How does the vacuum of space affect thermal management?

The vacuum of space makes thermal management more challenging as there is no air to transfer heat through convection. Instead, heat is mainly transferred through radiation, which is typically less efficient. This requires careful design and efficient use of materials to ensure proper thermal regulation.

4. What are the consequences of inadequate thermal management in spacecraft?

Inadequate thermal management in spacecraft can lead to critical failures and malfunctions, such as electronic components overheating or freezing, which can cause system shutdowns or permanent damage. It can also affect the performance and lifespan of the spacecraft.

5. How is thermal management tested and evaluated in spacecraft?

Thermal management in spacecraft is tested and evaluated through various methods, including thermal vacuum testing, thermal cycling, and thermal analysis using computer simulations. These tests help ensure that the spacecraft can withstand the extreme temperatures and thermal conditions of space.

Back
Top