Thermal Deformation Analysis of Micro satellite Structure

Gasser Abdelal, Ayman Atef

Research output: Contribution to conferencePaper

Abstract

Mounting accuracy of satellite payload and ADCS (attitude determination and control subsystem) seats is one of the requirements to achieve the satellite mission with acceptable performance. Components of mounting inaccuracy are technological inaccuracies, residual plastic deformations after loading (during transportation and orbital insertion), elastic deformations, and thermal deformations during orbital operation. This paper focuses on estimation of thermal deformations of satellite structure. Thermal analysis is executed by applying finite-difference method (IDEAS) and temperature profile for satellite components case is evaluated. Then, Perform thermal finite-element analysis applying the finite-difference model results as boundary conditions; and calculate the resultant thermal strain. Next, applying the resultant thermal strain, perform finite-element structure analysis to evaluate structure deformations at the payload and ADCS equipments seats.
Original languageEnglish
Pages351-372
Number of pages22
Publication statusPublished - May 2005
Event11th International Conference on Aerospace sciences & Aviation Technology, ASAT - Cairo, Egypt
Duration: 01 May 200501 May 2005

Conference

Conference11th International Conference on Aerospace sciences & Aviation Technology, ASAT
CountryEgypt
CityCairo
Period01/05/200501/05/2005

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    Abdelal, G., & Atef, A. (2005). Thermal Deformation Analysis of Micro satellite Structure. 351-372. Paper presented at 11th International Conference on Aerospace sciences & Aviation Technology, ASAT, Cairo, Egypt.