System, synthesized to extend radio command guidance to missions with over-the-horizon orbital injection requirements and its application to mission requiring direct powered ascent into 100-naut-mi circular parking orbit, free fall through 205° of parking orbit, and transfer burn to place vehicle on lunar trajectory or Hohmann transfer ellipse for synchronous orbit insertion; powered flight guidance equations using computation of required velocity and technique to implement cross-product steering with altimeter and accelerometer measurements are given; computer program, capable of performing error analysis of data processing scheme, was used to assess orbit determination capabilities of system.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Inertially augmented radio altimeter guidance system for space booster vehicles


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Henz, J.A. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1966


    Format / Umfang :

    7 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :




    Inertially Augmented Approach Couplers

    D. A. Tiedeman / F. B. Benson / L. V. Miller et al. | NTIS | 1979


    Inertially augmented approach couplers

    Tiedeman, D.A. / Benson, F.B. / Miller, L.V. et al. | Tema Archiv | 1979