The Space Shuttle Orbiter navigation system must be capable of determining its position and velocity throughout a variety of operational regimes. The design and operation of the entry through landing navigation system is described as it operates during a nominal end of mission from the orbital coasting phase throughout atmospheric flight and landing. Design and operation of the Kalman filter is described. Stabilization of the altitude channel prior to acquisition of external measurement data is described. Utilization of the Tactical Air Navigation (TACAN), barometric altimeter, and Microwave Scan Beam Landing System external measurement data is described. A comparison is made between predicted performance and the navigation accuracy observed during flight.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Titel :

    Space Shuttle Orbiter entry through landing navigation


    Beteiligte:

    Erscheinungsdatum :

    1982-01-01


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Space Shuttle Orbiter Landing Loads Optimization

    Purtle, L. / Fann, C. / Eich, P. et al. | British Library Conference Proceedings | 1995


    Space Shuttle Orbiter descent navigation

    MONTEZ, M. / MADDEN, M. | AIAA | 1982


    Space Shuttle Orbiter landing loads optimization

    Purtle, L.V. / Fann, C.P. / Eich, P.G. | Tema Archiv | 1995



    Microwave landing system for Space Shuttle Orbiter

    BLAZEK, G. / CARRIER, L. | AIAA | 1974