Thermal characterisation analysis and modelling techniques for CubeSat-sized spacecrafts

Ali, Anwar; Ullah, Khalil; Rehman, Hafeez Ur; Bari, Inam; Reyneri, Leonardo

doi:10.1017/aer.2017.108

Cited by 8 publications

(6 citation statements)

References 3 publications

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“…The plot shows the external temperature radiating from the AraMiS cube surface. Temperature in the inner region will be greater and will depend on the thermal resistance between the point of generation and the outer surface [35]. Case 2b: This case is similar to case 2a, but in this case the energy conversion and storage in batteries (γ = 0.23 * 0.8 i.e.…”

Section: Spacecraft Analysis Under Thermal Equilibriummentioning

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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Section: Spacecraft Analysis Under Thermal Equilibriummentioning

confidence: 99%

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

et al. 2020

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“…Thermal model of a system can be achieved as a combination of thermal capacitors and thermal resistances [31]. Consider an object that consists of N-materials stacked together as shown in Figure 20 Transient thermal model consists of thermal resistances and thermal capacitances related with the body materials of the object as shown in Figure 20(b).…”

Section: Pdm Thermal Modelmentioning

confidence: 99%

Modular Design and Thermal Modeling Techniques for the Power Distribution Module (PDM) of a Micro Satellite

Ali

Ali²,

Tong

et al. 2020

IEEE Access

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The power distribution module (PDM) is one of the vital modules onboard small satellites and its design governs the performance of all the subsystems including communication, attitude determination & control, navigation, payload, etc. The paper presents the design of the PDM developed for the Pakistan National Student Satellite-1 (PNSS-1). The main focus of the design is modularity, redundancy, design reuse and miniaturization using commercial off the shelf (COTS) components. PDM is the submodule of electric power system (EPS) which converts the power distribution bus (PDB) voltage level (unregulated 28V) into the secondary voltage levels and to distribute these voltages to loads according to their requirements. In order to improve reliability and to overcome various failures, redundancy is provided at all levels. No single component failure in PDM disables or degrades its intended functions that may lead to mission failure. Latch-up protection circuit is designed for the CMOS processor and at the end a thermal model is presented for the PDM unit.

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“…Thermal modeling of the PCB has been considered as an effective way to evaluate the capability of thermal diffusion of the PCB and to estimate components' temperature [1][2][3][4][5][6][7][8][9][10][11][12][13][14]. Historically, some modeling methods of analyzing the effective thermal conductivity of the PCB structure were investigated, such as the method of deriving the lumped thermal conductivity of the PCB [1,2] and the method of deriving the discrete thermal conductivity of orthogonal anisotropy (x, y, z direction in Cartesian coordinate) based on the PCB wiring diagram [3,4].…”

Section: Introductionmentioning

confidence: 99%

“…Historically, some modeling methods of analyzing the effective thermal conductivity of the PCB structure were investigated, such as the method of deriving the lumped thermal conductivity of the PCB [1,2] and the method of deriving the discrete thermal conductivity of orthogonal anisotropy (x, y, z direction in Cartesian coordinate) based on the PCB wiring diagram [3,4]. In recent years, equivalent thermal-resistance models of the PCB [5][6][7] have been also researched. Two analytical thermal-resistance models and design optimization methods were proposed for optimizing the layout of PCB vias and thermal pads under the IC [5].…”

Section: Introductionmentioning

confidence: 99%

“…Two analytical thermal-resistance models and design optimization methods were proposed for optimizing the layout of PCB vias and thermal pads under the IC [5]. Based on the layerwise equivalent thermal resistance of the nanosatellite PCB, both the detailed and simplified modeling methods for thermal analysis of the PCB have been typically proposed [6,7].…”

Section: Introductionmentioning

confidence: 99%

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Improved Numerical-Analytical Thermal Modeling Method of the PCB With Considering Radiation Heat Transfer and Calculation of Components’ Temperature

Zhang

2021

IEEE Access

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The previous work relating to the numerical-analytical coupling method for steady-state thermal analysis of the laminated PCB structure is first briefly reviewed. The Fourier-series analytical solution of temperature and the finite volume method were linked together for thermally modeling the PCB. For further modeling the PCB with components, thermal-resistance parameters of the components are then used for correlating components' temperatures with the variable arrays in the coupling equations. For further considering radiation heat transfer between the PCB and the ambient, an iterative method is proposed. The radiation-equivalent heat transfer coefficient for each surface cell and each component can be updated during the iteration. Moreover, for improving the efficiency, the multigrid strategy is integrated in the coupling method for generating discrete cells of three levels in the metal layer and PCB surface region. To testify the iterative method, the model of a simple one-layer structure is compared with that built in COMSOL Multiphysics. The modeling results of the PCB of a phantom DC-DC power supply under radiation heat transfer are also given and discussed, and the modeling accuracy is approximately derived based on Richardson's extrapolation.

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Thermal characterisation analysis and modelling techniques for CubeSat-sized spacecrafts

Cited by 8 publications

References 3 publications

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

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

Modular Design and Thermal Modeling Techniques for the Power Distribution Module (PDM) of a Micro Satellite

Improved Numerical-Analytical Thermal Modeling Method of the PCB With Considering Radiation Heat Transfer and Calculation of Components’ Temperature

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