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Thermal fatigue analysis of small-satellite structure

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Abstract

The small-satellite thermal subsystem main function is to control temperature ranges on equipments, and payload for the orbit specified. Structure subsystem has to ensure the satellite structure integrity. Structure integrity should meet two constraints; first constraint is accepted fatigue damage due to cyclic temperature, and second one is tolerable mounting accuracy at payload and Attitude Determination and Control Subsystem (ADCS) equipments’ seats. First, thermal analysis is executed by applying finite-difference method (IDEAS) and temperature profile for satellite components case is evaluated. Then, thermal fatigue analysis is performed applying finite-element analysis (ANSYS) to calculate the resultant damage due to on-orbit cyclic stresses, and structure deformations at the payload and ADCS equipments seats.

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Authors and Affiliations

  1. Egyptian Space Program, National Authority for Remote Sensing and Space Science (NARSS), 23 Jozef Broz Teto Street, Elnozha Elgededah, Cairo, 11769, Egypt

    Gasser Farouk Abdelal, Ahmed Hamdy & Ayman Atef

  2. Aerial Photograph Division Program, National Authority for Remote Sensing and Space Science (NARSS), 23 Jozef Broz Teto Street, Elnozha Elgededah, Cairo, 11769, Egypt

    Nader Abuelfoutouh

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

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Abdelal, G.F., Abuelfoutouh, N., Hamdy, A. et al. Thermal fatigue analysis of small-satellite structure. Int J Mech Mater Des 3, 145–159 (2006). https://doi.org/10.1007/s10999-007-9019-1

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  • DOI: https://doi.org/10.1007/s10999-007-9019-1

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