Summary of parametric investigation of parachute recovery system for Mars entry vehicle is presented; parameters investigated were entry vehicle velocity, entry angle, estimated atmospheric variations as of mid 1962 and parachute system weight; analysis shows that under most severe expected entry conditions four minute time of descent cannot be achieved using conventional parachute designs; three-stage system with first stage deployed at maximum dynamic pressure of 500 psf, weighing 17 lb, would provide minimum weight decelerator system.


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    Title :

    Recovery system for controlled descent through Martian atmosphere


    Additional title:

    Symposium Ballistic Missile Space Technology -- Trans


    Contributors:

    Conference:

    8th Symposium on Ballistic Missile and Space Technology ; 1963 Recovery



    Publication date :

    1963


    Size :

    29 pages


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English


    Keywords :