Six-degree-of-freedom simulations of the space shuttle orbiter entry with control hysteresis were conducted on the NASA Langley Research Center interactive simulator known as the automatic reentry flight dynamics simulator. These simulations revealed that the vehicle can tolerate control hysteresis producing a + or - 50 percent change in the nominal aileron roll characteristics and an offset in the nominal characteristics equivalent to a + or - 5 deg aileron deflection with little increase in the reaction control system's fuel consumption.


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    Titel :

    Aileron roll hysteresis effects on entry of space shuttle orbiter


    Beteiligte:
    Powell, R. W. (Autor:in)

    Erscheinungsdatum :

    1977-07-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch