CLLARE and Apollo compared
From CSTART Wiki
This page lists significant differences between the CLLARE and Apollo missions, with an emphasis on those differences which explain the drastically reduced cost of CLLARE.
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|Propellants||Cryogenic LOX/H2, vacuum specific impulse ~450s||Hypergolic Aerozine/Nitrogen tetroxide, vacuum specific impulse ~314s|
|Lunar lander||Open cab lander with life support provided by suit||Closed, pressurised lander with own life support system|
|Total launch mass||estimated 10000 kg||approximately 45000 kg|