Various types of uncertainties are modeled and analyzed aiming at the uncertainty existing in the entry phase of hypersonic flight vehicle. Based upon the research on Monte Carlo simulation, to further improve the operability of uncertainty quantitative calculation, an uncertainty analysis approach over entry guidance is proposed based on confidence interval estimation, including the sensitivity analysis. Especially, this paper focuses on the influence of atmospheric model uncertainty on the impact points' dispersion of entry guidance. The confidence interval of impact points is calculated under atmospheric models with different confidence. Simulation results show that this approach can analyze the relative important order of uncertainty in the entry phase of hypersonic flight vehicle more accurately compared to traditional method.


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    Titel :

    Uncertainty analysis of entry guidance based on confidence interval estimation


    Beteiligte:
    Xiao Jiaping, (Autor:in) / Shen Zuojun, (Autor:in)


    Erscheinungsdatum :

    2016-08-01


    Format / Umfang :

    5600109 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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