ESA Document - Emits - ESA

s
ground temperature [C]
sky temperature [K]
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-40
-60
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-140
Mars climate database (tau=0.5, Ls sector 90-120)
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0 2 4 6 8 10 12 14 16 18 20 22 24
local time [hr]
-82.5
-72.5
-62.5
-52.5
-42.5
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-22.5
-12.5
-2.5
2.5
12.5
22.5
32.5
42.5
52.5
62.5
72.5
82.5
ground temperature [C]
20
0
-20
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-80
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-140
Mars climate database (tau=0.5, Ls sector 0-30)
0 2 4 6 8 10 12 14 16 18 20 22 24
local time [hr]
Figure 4-30: Ground temperature versus local time and latitude
Mars climate database
sky temperature envelope (min-max) over one sol (Ls 30-60)
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150
140
130
120
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100
90
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60
-80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 80
latitude [deg.]
Mars climate database
sky temperature envelope (min-max) over one sol (Ls 90-120)
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150
140
130
120
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90
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HMM
Assessment Study
Report: CDF-20(A)
February 2004
page 282 of 422
-80 -70 -60 -50 -40 -30 -20 -10 0 10 20 30 40 50 60 70 80
latitude [deg.]
Figure 4-31: Sky temperature versus latitude (L), Sky temperature versus latitude (R)
4.3.4.2.3 Man-induced thermal loads
Thermal design shall manage all internal heat loads resulting from the human activities and
various dissipating equipments:
• Total mean heat load of 2.35 kW during day, 2.41 kW during night
• Metabolic dissipation is estimated to 110W (steady activity) per crew (x 3)
4.3.4.3 Baseline thermal design
4.3.4.3.1 Surface habitation thermal control
With no direct expertise in Europe available for such vehicle, the design block proposed is based
partly on the exploitation of foreign existing heritage: Apollo LM, LOK (derived Soyuz). Space
station fluid-loops technologies are applicable to a certain extent.
The thermal control philosophy adopted for such vehicle is standard and relies on the following
approach:
sky temperature [K]
-82.5
-72.5
-62.5
-52.5
-42.5
-32.5
-22.5
-12.5
-2.5
2.5
12.5
22.5
32.5
42.5
52.5
62.5
72.5
82.5