Heat capacity estimation of the thermal buffer mass for temperature control of satellite electronic components in periodic operation

Kim, T.Y.

doi:10.1016/j.ast.2013.08.013

Cited by 7 publications

(3 citation statements)

References 3 publications

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“…In addition, the power supply is composed of numerous electronic components. According to foreign statistics, the reliability of electronic components decreases by 10% every time the temperature rises by 2 °C when they are working, and the service life is only 1/6 of 25 °C when the temperature rises by 50 ° C. Therefore, technical measures should be taken to limit the temperature rise of components [8][9][10].…”

Section: Analysis Of Product Thermal Effectmentioning

confidence: 99%

Study on the Influence of Product Thermal Effect on Thermal Vacuum Test

Ma,

Tian,

Song

et al. 2024

J. Phys.: Conf. Ser.

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Due to different applications, the size, shape and surface state of the power supply on spacecraft vary greatly, but they all need to experience a harsh environment, such as extreme vacuum, cold and hot alternation. Therefore, it is necessary to undergo the thermal vacuum test on the ground. During the thermal vacuum test, the aerospace power supply products with different surface states have different internal temperature rise effects due to their own emissivity and absorption during testing. The higher the temperature rise effect, the lower the product reliability. Therefore, in order to reduce the temperature rise effect of products in the process of thermal vacuum test, the temperature rise effect of products with different surface states or the same surface state can be reduced by using different shading measures in the thermal vacuum test of products is analysed and verified by experiments. The test results show that the product with bright surface has lower temperature rise effect than the product with blackened surface, which can reduce the maximum temperature difference, enhance the uniformity of temperature field and enhance the reliability of the product. In addition, using measures such as covering the product with aluminized film or overhanging it can reduce the surface temperature difference, with the overhanging shade being more effective.

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Section: Analysis Of Product Thermal Effectmentioning

confidence: 99%

Study on the Influence of Product Thermal Effect on Thermal Vacuum Test

Ma,

Tian,

Song

et al. 2024

J. Phys.: Conf. Ser.

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“…Thermal terrestrial radiation for which the earth can be modelled as an equivalent black-body emitting at 255K [26] iv. Heating due to internal heat generation in electronic components (Joule's effect) [27] v. Heat capacity of the system [28] vi. Cooling due to heat radiation vii.…”

Section: Spacecraft Thermal Analysis In Space Environmentmentioning

confidence: 99%

“… The time required to rotate the satellite, initially without spin, with an angular velocity ω 0 is given by (28).…”

Section: B Analysis Of the Mechanical Momentum And The Spin-inducedmentioning

confidence: 99%

A Detailed Thermal and Effective Induced Residual Spin Rate Analysis for LEO Small Satellites

et al. 2020

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In space thermal environment, satellites are exposed to multiple heat sources which can deteriorate structural and equipment integrity over long periods of time. Normally radiators are used to release heat, but due to space and weight constraints, it is impossible to mount radiators on small satellites. This problem signifies the importance of thermal analysis of a satellite in every development stage, such as design, manufacturing and testing. The ultimate goal of this work is to analyze a small spacecraft in space thermal environment by considering the effect of various heat sources. Thermal equilibrium equation is achieved which is applied to spacecraft with different shapes and dimensions and temperature is measured for a range of absorption coefficient values (i.e. 0.5 ~ 0.9). Through an experimental setup a method is devised to measure the absorption coefficient of small satellites that can be used for exact temperature measurement. Secondly, the paper presents a preliminary analysis of induced spin produced by small satellites due to asymmetrical colors (different absorptance) of satellite outer surface. The substantial contributors for induced spin are considered and the estimated spin is measured. INDEX TERMS Satellites, Thermal analysis, Temperature, Absorption. I. INTRODUCTION Recently, there is a great emphasis on the development of small satellites by universities and SMEs (small and medium enterprisers) because they are simple, cheaper and easy to launch [1, 2]. In this regard, the first NanoSatellite was developed in 1999 by California Polytechnic State University (Cal Poly) in collaboration with Stanford University, called CubeSat with dimensions 10 × 10 × 10 cm 3 [3, 4]. This provided a new research area to universities and SMEs worldwide in the field of small satellites. Department of Electronics and Telecommunication (DET) at Politecnico di Torino is also working on a comprehensive NanoSatellite project called AraMiS [5], designing small satellites for Low Earth Orbit (LEO). The design process of AraMiS is based on the concept of tiles [6] and modules. The tiles and modules have different dimensions and technology to achieve any desired satellite structure. These modules can be reused for multiple missions that help in significant reduction of the overall budget, design,

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Advances in spacecraft thermal control

Consolo

Boetcher

2023

Advances in Heat Transfer

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Heat capacity estimation of the thermal buffer mass for temperature control of satellite electronic components in periodic operation

Cited by 7 publications

References 3 publications

Study on the Influence of Product Thermal Effect on Thermal Vacuum Test

Study on the Influence of Product Thermal Effect on Thermal Vacuum Test

A Detailed Thermal and Effective Induced Residual Spin Rate Analysis for LEO Small Satellites

Advances in spacecraft thermal control

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