The problem of designing a manned space vehicle which must survive entry into the earth's atmosphere is discussed from the systems point of view. In the design of such a vehicle peak deceleration loads become an important consideration. This aspect of the problem together with the aerodynamic heating and landing point dispersion factors is considered for two classes of re-entry bodies: (1) returning low-altitude satellite, and (2) vehicles which re-entry at or near escape velocity such as circumlunar vehicles. Finally, the heat shielding problem is presented in detail along with some solutions. (Author)


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    Titel :

    Descent Trajectories for Manned Space Vehicles


    Beteiligte:
    R. L. Phillips (Autor:in)

    Erscheinungsdatum :

    1958


    Format / Umfang :

    1 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch




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