Thermal fatigue analysis of small-satellite structure

Gasser Abdelal; Nader Abuelfoutouh; Ahmed Hamdy; Ayman Atef

doi:10.1007/s10999-007-9019-1

Thermal fatigue analysis of small-satellite structure

Gasser Abdelal, Nader Abuelfoutouh, Ahmed Hamdy, Ayman Atef

School of Mechanical and Aerospace Engineering

Research output: Contribution to journal › Article › peer-review

9 Citations (Scopus)

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 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 language	English
Pages (from-to)	145-159
Number of pages	15
Journal	International Journal of Mechanics and Materials in Design
Volume	3
Issue number	2
DOIs	https://doi.org/10.1007/s10999-007-9019-1
Publication status	Published - Feb 2007

ASJC Scopus subject areas

Materials Science (miscellaneous)

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10.1007/s10999-007-9019-1

http://link.springer.com/article/10.1007%2Fs10999-007-9019-1

Cite this

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title = "Thermal fatigue analysis of small-satellite structure",

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{\textquoteright} 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.",

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AU - Abdelal, Gasser

AU - Abuelfoutouh, Nader

AU - Hamdy, Ahmed

AU - Atef, Ayman

PY - 2007/2

Y1 - 2007/2

N2 - 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.

AB - 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.

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DO - 10.1007/s10999-007-9019-1

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EP - 159

JO - International Journal of Mechanics and Materials in Design

JF - International Journal of Mechanics and Materials in Design

IS - 2

ER -

Thermal fatigue analysis of small-satellite structure

Abstract

ASJC Scopus subject areas

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