A numerical example is given of a previously proposed methodology for the evaluation of in-flight thrust measurement uncertainty, using data extracted from a performance report comparing two different missile prototypes under a variety of flight conditions. Attention is given to the data for the AGM-68B Air Launched Cruise Missile, which is powered by the F107 dual-spool, mixed flow turbofan engine. Assessments are made of the definition of the measurement process, instrumentation error estimation, the propagation of errors to thrust calculation, mathematical model errors, the in-flight thrust error component, and correction to standard conditions. It is concluded that in-flight thrust measurement uncertainty limits can be evaluated from measurement system error analysis results and test data for the missile evaluation process presently described.


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    Titel :

    Application of in-flight thrust determination uncertainty


    Beteiligte:
    Adams, G. R. (Autor:in) / Thompson, J. W., Jr. (Autor:in) / Abernethy, R. B. (Autor:in) / Biesiadny, T. (Autor:in) / Havey, C. T. (Autor:in) / Steurer, J. W. (Autor:in) / Ascough, J. C. (Autor:in) / Williams, D. D. (Autor:in)

    Erscheinungsdatum :

    01.01.1983


    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Keine Angabe


    Sprache :

    Englisch




    Application of In-Flight Thrust Determination Uncertainty

    Havey, C. T. / Williams, D. D. / Adams, G. R. et al. | SAE | 1983



    Uncertainty of in-flight thrust determination

    Abernethy, Robert B. / Adams, Gary R. / Steurer, John W. et al. | NTRS | 1986