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Mechanical fatigue and spectrum analysis of small-satellite structure

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Abstract

Mechanical fatigue due to environmental loads and spectrum analysis due to launch loads of the primary structure of a low cost, low-earth orbit small satellite intended for earth observation missions are presented. The payload of the satellite under consideration is a precise optical unit to image the earth’s surface having a mass of 45 kg. 3-D Finite Element Model for the satellite structure is generated by applying substructure method. Modal analysis is required to determine natural frequencies of the satellite and define its mode shape. Then, ranking of mode shapes according to specific constraint is performed. Harmonic analysis at resonance frequencies with the highest ranking is done and cumulative fatigue damage analysis is performed. Spectrum analysis is performed for Small Sat structure to verify the satellite structure reliability under all dynamic random vibration loads applied during transportation and launch cases.

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Authors and Affiliations

  1. Emirates Aviation College, Aerospace and Academic Studies, ALGarhoud Area, P.O. Box 53044, Dubai, UAE

    Gasser Farouk Abdelal

  2. Aerial Photograph Division Program, National Authority of Remote Sensing and Space Science, 23 Jozef Broz Teto Street, Behind CAIRO International Airport, Elnozha Elgededah, P.O. 11769, Cairo, Egypt

    Nader Abuelfoutouh & Ahmed Hamdy

Authors
  1. Gasser Farouk Abdelal
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  2. Nader Abuelfoutouh
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  3. Ahmed Hamdy
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Correspondence to Gasser Farouk Abdelal.

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Abdelal, G.F., Abuelfoutouh, N. & Hamdy, A. Mechanical fatigue and spectrum analysis of small-satellite structure. Int J Mech Mater Des 4, 265–278 (2008). https://doi.org/10.1007/s10999-008-9064-4

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  • DOI: https://doi.org/10.1007/s10999-008-9064-4

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