Apollo mission design emphasized operational flexibility that supported premature return to Earth. However, that design was tailored to use expendable hardware for short expeditions to low-latitude sites and cannot be applied directly to an evolutionary program requiring long stay times at arbitrary sites. This work establishes abort performanc e requirements for representative onorbit phases of missions involvin g rendezvous in lunar-orbit, lunar-surface and at the Earth-Moon libr ation point. This study submits reference abort delta-V requirements and other Earth return data (e.g., entry speed, flight path angle) and also examines the effect of abort performance requirements on propul sive capability for selected vehicle configurations.


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    Title :

    Abort Options for Human Lunar Missions between Earth Orbit and Lunar Vicinity


    Contributors:

    Conference:

    2006 AAS/AIAA Space Flight Mechanics Meeting ; 2005 ; Tampa, FL, United States


    Publication date :

    2005-01-22


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English




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