Emerging small satellite market faces many challenges mainly to protect their payload during the launch. Satellite team has to share their finite element model to the launch vehicle team for the various analysis like launch vehicle dynamic characteristics, Coupled Load Analysis (CLA), dynamic envelop studies, etc. FE model contains sensitive details about the satellite, and dynamic condensation of the satellite is the only way to protect satellite details. This also helps in reducing the number of degrees of freedom of the satellite finite element model. Craig-Bampton technique is the most popular method to reduce the satellite into a mass and stiffness matrix with the required number of modes. Satellite team needs a physical node at critical locations to study the responses, and these nodes need to be retained while reduction. This paper examines the Craig-Bampton reduction method and discusses how to compute the response at various locations of the satellite. A frequency response analysis with reduced model and full model is also compared in this paper.


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    Titel :

    Challenges in the Dynamic Condensation and Internal Response Prediction of Small Satellites


    Weitere Titelangaben:

    Lect.Notes Mechanical Engineering


    Beteiligte:
    Priyadarsini, R.S. (Herausgeber:in) / Sundararajan, T. (Herausgeber:in) / Nath, Narendra (Autor:in) / Venkateswaran, K. P. (Autor:in) / Sundararajan, T. (Autor:in) / Geetha, S. (Autor:in)


    Erscheinungsdatum :

    2023-05-18


    Format / Umfang :

    6 pages





    Medientyp :

    Aufsatz/Kapitel (Buch)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




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