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    Astp (Sa-210) Launch Vehicle Operational Flight Trajectory. Part 3: Final Documentation

    Astp (Sa-210) Launch Vehicle Operational Flight Trajectory. Part 3: Final Documentation


    Trajectory data are presented for a nominal and two launch window trajectory simulations. These trajectories are designed to insert a manned Apollo spacecraft into a 150/167 km. (81/90 n. mi.) earth orbit inclined at 51.78 degrees for rendezvous with a Soyuz spacecraft, which will be orbiting at approximately 225 km. (121.5 n. mi.). The launch window allocation defined for this launch is 500 pounds of S-IVB stage propellant. The launch window opening trajectory simulation depicts the earliest launch time deviation from a planar flight launch which conforms to this constraint. The launch window closing trajectory simulation was developed for the more stringent Air Force Eastern Test Range (AFETR) flight azimuth restriction of 37.4 degrees east-of-north. These trajectories enclose a 12.09 minute launch window, pertinent features of which are provided 9in a tabulation. Planar flight data are included for mid-window reference. (Author)

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    Titel :

    Astp (Sa-210) Launch Vehicle Operational Flight Trajectory. Part 3: Final Documentation

    Beteiligte:
    A. B. Carter (Autor:in) / G. W. Klug (Autor:in) / N. W. Williams (Autor:in)
    Erscheinungsdatum :

    1975

    Format / Umfang :

    302 pages

    Medientyp :

    Report

    Format :

    Keine Angabe

    Sprache :

    Englisch

    Schlagwörter :

    Spacecraft Trajectories & Flight Mechanics , Manned Spacecraft , Apollo soyuz test project , Saturn 1b launch vehicles , Spacecraft trajectories , Computer techniques , Computerized simulation , Flight characteristics , Launch windows , Tables (Data)

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