THERMAL DEFORMATION ANALYSIS OF MICROSATELLITE STRUCTURE | ||||
| International Conference on Aerospace Sciences and Aviation Technology | ||||
| Article 20, Volume 11, ASAT Conference, 17-19 May 2005, May 2011, Page 351-372 PDF (3.57 MB) | ||||
| Document Type: Original Article | ||||
| DOI: 10.21608/asat.2011.27156 | ||||
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| Authors | ||||
| Gasser Abdelal1; Ayman Atef2 | ||||
| 1Ph.D., Deputy Group Leader - Satellite Structure (EGYPTSAT-I), National Authority for Remote Sensing and Space Science (NARSS). | ||||
| 2Senior Structure Engineer - Satellite Structure (EGYPTSAT-I), National Authority for Remote Sensing and Space Science (NARSS). | ||||
| 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. | ||||
| Keywords | ||||
| Aerospace; Satellite; structure; thermal deformation; finite difference; Finite Element; and mounting accuracy | ||||
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