Simulation of a CubeSat with internal heat transfer using Finite Volume Method

Filho, Edemar Morsch; Seman, Laio Oriel; Nicolau, Vicente de Paulo

doi:10.1016/j.applthermaleng.2021.117039

Cited by 10 publications

(2 citation statements)

References 25 publications

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“…The methodology used in this paper for conducting the thermal analysis of AlAinSat-1 is based on the finite element method (FEM) analysis, using Siemens NX's 3D Space Systems Thermal module. Such software has the advantage of facilitating the thermal analysis easily in addition to simulating an orbiting satellite easily [6,7]. The rest of this paper is organized as follows.…”

Section: Introductionmentioning

confidence: 99%

Thermal Analysis of AlainSat-1: A 3U Cubesat for Earth Observation

Wan Aasim,

Seyedzadeh,

Okasha

et al. 2024

E3S Web Conf.

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AlainSat-1 is a remote sensing CubeSat carrying earth observation payloads developed by student teams from three international universities. Planned for launch in 2023 it is a direct result from the collaborative effort between the IEEE Geoscience and Remote Sensing Society (GRSS) and the National Space Science and Technology Center (NSSTC) at UAE University. CubeSats are popular among the research and academic communities as a space platform from which to perform related research and academic work connected to space technologies due to their compact size, shorter development time, and relatively low cost. However, because most CubeSats are built using off-the-shelf components, their capacity to resist the harsh environments of space must be proven. Aside from ensuring that structural criteria are met, thermal analysis is critical for ensuring that components or payloads stay functioning in extreme hot or cold environments. The thermal analysis results of AlainSat-1’s finite element model (FEM) functioning under the projected thermal environment associated to its mission are presented in this study. Preliminary results from the analysis using SIEMENS NX show that temperature measurements are within an acceptable range. However, more modification of the simulated environment and FEM in terms of mesh sizes and radiative and conductive thermal couplings is needed before conclusive results may be obtained. The approved simulated results and parameters will be tested experimentally in a Thermal Vacuum Chamber. In addition, challenges identified throughout the analysis and their remedies are discussed.

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Section: Introductionmentioning

confidence: 99%

Thermal Analysis of AlainSat-1: A 3U Cubesat for Earth Observation

Wan Aasim,

Seyedzadeh,

Okasha

et al. 2024

E3S Web Conf.

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show abstract

“…The model has a more accurate geometry with respect to the Lumped Parameter Approach method which is commonly used in space thermal analyses, e.g., when simulating with the ESATAN software, the European Space Agency Lumped Parameter Approach software used for thermal analyses; for more information on ESATAN the reader can refer to [7]. Indeed, the FVTM offers better insight into the heat fluxes within the model as shown in [7][8][9]. In this work, the post-processing of the experimental data is presented, and the test data is compared with the FVTM results, proving the application of the novel method to be reliable.…”

Section: Introductionmentioning

confidence: 99%

HERMES CubeSat Payload Thermal Balance Test and Comparison with Finite Volume Thermal Model

et al. 2023

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Scientific payloads onboard CubeSats usually have complex geometries and occasionally narrower allowed temperature ranges with respect to the rest of the spacecraft. In these cases, the capability to correctly predict the thermal behaviour of the payload once in orbit is mandatory. To achieve this ability, a thermal balance test is required to correctly identify the thermal model of the payload. The test consists in the application of different external thermal boundary conditions together with the addition of heat dissipation to simulate the thermal load produced by active electronics during operation. Those experimental data are fundamental to validate the numerical thermal model and make its predictions reliable. This paper presents the configuration and procedures of the thermal balance test performed on the Demonstration Model of the payload to be embarked on each satellite of the HERMES constellation. The test data is compared with the results of a finite volume thermal model of the payload, proving the application of this method to be reliable for space thermal analyses. The obtained test results show the temperature jumps caused by the heat dissipation applied to active components. A weak correlation between the payload interface and internal equipment has been observed, thus proving that the payload is almost decoupled from the Service Module temperature variations. Based on test outcomes, some modifications in the payload design have been implemented, with the aim to lower the operative temperature on critical, temperature-sensitive equipment.

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CubeSat thermal analysis: evaluating models for thermal contact conductance

Blanchete,

Bah

2024

Heat Mass Transfer

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Simulation of a CubeSat with internal heat transfer using Finite Volume Method

Cited by 10 publications

References 25 publications

Thermal Analysis of AlainSat-1: A 3U Cubesat for Earth Observation

Thermal Analysis of AlainSat-1: A 3U Cubesat for Earth Observation

HERMES CubeSat Payload Thermal Balance Test and Comparison with Finite Volume Thermal Model

CubeSat thermal analysis: evaluating models for thermal contact conductance

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