國立虎尾科技大學 |

Thermal Analysis of Cubesat.

Record Type:	Language materials, manuscript : Monograph/item
Title/Author:	Thermal Analysis of Cubesat./
Author:	Min, Tay Jia.
Description:	1 online resource (77 pages)
Notes:	Source: Masters Abstracts International, Volume: 84-04.
Contained By:	Masters Abstracts International84-04.
Subject:	Aeronautics. -
Online resource:	click for full text (PQDT)
ISBN:	9798352686157

Thermal Analysis of Cubesat.
Min, Tay Jia.

Thermal Analysis of Cubesat. - 1 online resource (77 pages)

Source: Masters Abstracts International, Volume: 84-04.

Thesis (M.E.)--National University of Singapore (Singapore), 2022.

Includes bibliographical references

Due to the harsh space environment, satellites need to be designed to withstand the wide temperature range during sunlight and eclipse. The common method of designing satellites would require a detailed thermal model and analysis of the satellite in orbit to determine the in-flight temperatures of the satellite based on the planned satellite orbit, which would be used to determine test temperatures for ground tests. An iterative design and analysis process would be conducted to ensure the successful operation of the satellite in orbit, as repair works are impossible to carry out on satellites after launch and therefore, the cost of mission failure is very high. This method originated from large satellite development carried out by space agencies and is very time consuming. Small satellite development is done under much shorter timeframes and therefore requires an approach or method that is able to sufficiently detect any issues with the thermal design and characteristics of the satellite within the designated timelines. This requires shorter thermal analysis durations for faster design iteration. A single thermal analysis run using commercial software can take up to seven days. This is much longer compared to satellite structural analysis which only requires up to three hours to obtain results. This work studies the feasibility of standardization of test temperatures based on external structural panels, reducing the size of the thermal analysis problem by breaking down the thermal analysis to the unit level. Therefore, a parametric sensitivity study is carried out to understand the parameters which have a heavy influence on satellite temperatures. For satellite designs that keep within range of nominal values, standard test temperatures can be adopted with a margin. In addition, a mesh sensitivity, ray tracing and time step integration study is conducted to determine the suitable respective values for analysis. All of the work in this thesis is carried out on a 12U satellite.

Electronic reproduction.
Ann Arbor, Mich. :
ProQuest,
2024

Mode of access: World Wide Web

ISBN: 9798352686157Subjects--Topical Terms:

678940
Aeronautics.
Index Terms--Genre/Form:

554714
Electronic books.

Thermal Analysis of Cubesat.
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500 $a Source: Masters Abstracts International, Volume: 84-04.
500 $a Advisor: Huangwei, Zhang.
502 $a Thesis (M.E.)--National University of Singapore (Singapore), 2022.
504 $a Includes bibliographical references
520 $a Due to the harsh space environment, satellites need to be designed to withstand the wide temperature range during sunlight and eclipse. The common method of designing satellites would require a detailed thermal model and analysis of the satellite in orbit to determine the in-flight temperatures of the satellite based on the planned satellite orbit, which would be used to determine test temperatures for ground tests. An iterative design and analysis process would be conducted to ensure the successful operation of the satellite in orbit, as repair works are impossible to carry out on satellites after launch and therefore, the cost of mission failure is very high. This method originated from large satellite development carried out by space agencies and is very time consuming. Small satellite development is done under much shorter timeframes and therefore requires an approach or method that is able to sufficiently detect any issues with the thermal design and characteristics of the satellite within the designated timelines. This requires shorter thermal analysis durations for faster design iteration. A single thermal analysis run using commercial software can take up to seven days. This is much longer compared to satellite structural analysis which only requires up to three hours to obtain results. This work studies the feasibility of standardization of test temperatures based on external structural panels, reducing the size of the thermal analysis problem by breaking down the thermal analysis to the unit level. Therefore, a parametric sensitivity study is carried out to understand the parameters which have a heavy influence on satellite temperatures. For satellite designs that keep within range of nominal values, standard test temperatures can be adopted with a margin. In addition, a mesh sensitivity, ray tracing and time step integration study is conducted to determine the suitable respective values for analysis. All of the work in this thesis is carried out on a 12U satellite.
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538 $a Mode of access: World Wide Web
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773 0 $t Masters Abstracts International $g 84-04.
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