Table 2 Summary of features for different depot locations from19

From: Cryogenic propellant management in space: open challenges and perspectives

Location

Total propellant mass kg

Heat flux Wm2

Boil-off rate kg h1

chill-down mass kg/transfer

LEO

434696

2162

0.02 to 0.20

5.6

GEO

212696

1388

0.01 to 0.13

5.6

EML1

204871

1367

0.01 to 0.12

5.6

  1. The total propellant mass is based on fueling the commercial satellite servicing mission (CSS) vehicle and the Mars cargo mission (MC) vehicle every 6 months. The heat flux comes from the sun and the albedo of the Earth. The boil-off rates and chill-down masses are for hydrogen only.
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