A contingency trajectory analysis was performed for NASA Ames Research Center’s (ARC’s) Lunar Atmosphere and Dust Environment Explorer (LADEE) spacecraft in case of a missed lunar orbit insertion (LOI) maneuver. Recovery trajectory options are shown to exist for all LADEE launch opportunities throughout a one year period. Recovery ΔV costs primarily depended on the spacecraft’s apogee location on or near the Sun-Earth weak stability boundary (WSB) and the time needed by the spacecraft to recover (e.g. to “wake up” from “safe” mode) to perform an escape prevention maneuver after the missed LOI.


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    Title :

    Contingency Trajectory Design for a Lunar Orbit Insertion Maneuver Failure by the LADEE Spacecraft


    Contributors:

    Conference:

    AIAA SPACE 2014 Conference and Exposition ; 2014 ; San Diego, CA, United States
    AIAA/AAS Astrodynamics Specialist Conference ; 2014 ; San Diego, CA, United States


    Publication date :

    2014-08-04


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :