ESA Document - Emits - ESA

s
HMM
Assessment Study
Report: CDF-20(A)
February 2004
page 384 of 422
• guaranteeing by adequate provision of thermal hardware for the whole mission (necessary
autonomy of the crew)
• fully verifying and testing the TCS on ground
4.5.5.2 Assumptions
4.5.5.2.1 Transfer, rendezvous and docking phases thermal environment
The same environment as for the transfer vehicle applies for the Mars Excursion vehicle
including the ascent vehicle. A conservative approach is to consider envelopes through worstcase
scenarios:
Solar flux [W/m 2 ] Planet albedo Planet IR [W/m 2 ]
Hot case (Earth LEO, WS, 1 AU) 1423 0.33 241
Hot case (Mars orbit, perihelion, 1.38 AU) 2 717 0.29 (subsolar) 470 (subsolar) to 30
Cold case (Mars orbit, aphelion, 1.66 AU) 3 493 0.29 (subsolar) 315 (subsolar) to 30
Table 4-57: Thermal cases definition
The docking has an envelope of maximal 4 days starting from the take off.
4.5.5.2.2 Martian thermal environment
The same environment as for the Habitation Module applies.
4.5.5.2.3 Martian ascent phase
Altitude (km)
600
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0
Altitude (km)
Velocity (km/s)
1
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Time (s)
4.5.5.2.4 Man-induced thermal loads
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3.5
3
2.5
2
1.5
Inertial Velocity (km/s)
Dynamic Pressure (Pa)
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0
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Time (s)
Figure 4-117: Flight Environment (from Trajectory analysis)
Dynamic Pressure (Pa)
Heat Flux (kW/m2)
The thermal design shall manage all internal heat loads resulting from the human activities and
various dissipating equipments:
• Total mean heat load of 582W during ascent and parking orbit phases, 931W during
rendezvous and docking phase.
• Metabolic dissipation is estimated to be 110W (steady activity) per crew (x 3)
160
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60
40
20
Heat Flux (kW/m2)