Thermal fatigue analysis of small-satellite structure

Gasser Abdelal, Nader Abuelfoutouh, Ahmed Hamdy, Ayman Atef

Research output: Contribution to journalArticlepeer-review

6 Citations (Scopus)


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 finitedifference 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.
Original languageEnglish
Pages (from-to)145-159
Number of pages15
JournalInternational Journal of Mechanics and Materials in Design
Issue number2
Publication statusPublished - Feb 2007

ASJC Scopus subject areas

  • Materials Science (miscellaneous)

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