The Phoenix mission is designed to study the arctic region of Mars. To achieve this goal, the spacecraft must be delivered to a narrow corridor at the top of the Martian atmosphere, which is approximately 20 km wide. This paper will discuss the details of the Phoenix orbit determination process and the effort to reduce errors below the level necessary to achieve successful atmospheric entry at Mars. Emphasis will be placed on properly modeling forces that perturb the spacecraft trajectory and the errors and uncertainties associated with those forces. Orbit determination covariance analysis strongly influenced mission operations scenarios, which were chosen to minimize errors and associated uncertainties.


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    Title :

    Orbit Determination for the 2007 Mars Phoenix Lander


    Contributors:

    Conference:

    2008 AIAA/AAS Astrodynamics Specialists Conference ; 2008 ; Honolulu, HI, United States


    Publication date :

    2008-08-18


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :


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