Thermal design, analysis, and testing of the first Turkish 3U communication CubeSat in low earth orbit

This paper describes the passive thermal control analysis and design for a small satellite in low Earth orbit. The main objective of the thermal control system is to guarantee the proper operation against the harsh environment in space.The European Student Earth Orbiter satellite was chosen to carry out this study. The paper introduces an alternative means for the thermal control system to be passive by using tapes, coatings, radiators, and multi-layer insulation applied to the satellite to control radiation heat exchange between the satellite and its environment. For this purpose, a finite-difference model was developed using a commercial software package. Results obtained from the simulations were introduced, analyzed, and partially verified for both extreme hot and cold cases.The results show that all the components inside the satellite, structural, and solar panels were within their temperature limits. The most critical components in the hot case are the battery and gyro box with temperature safety margins of 1.83 °C and 2.47 ℃, respectively. The most critical components in the cold case are reaction wheel 2 and uCAM with temperature safety margins of 4.62 ℃ and 4.73 ℃, respectively. The battery on panel 6 has a temperature safety margin of 6.64 ℃.

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“…The heat balance equation for node i coupled with nodes j through N can be written as Eq. ( 1) [39,40].…”

Section: Thermal Energy Balancementioning

confidence: 99%

“…The term Qe is the emitted heat to space [W] given by The term Qexternal,i is external loads (solar, albedo, and planetary heat rate) [W], given by Eq. ( 3) [40].…”

Section: Thermal Energy Balancementioning

confidence: 99%

Passive thermal control design and analysis of a university-class satellite

El‐Hefnawy¹,

Elmaihy

Elweteedy

2022

J Therm Anal Calorim

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“…14 [71]. Furthermore, given the small size (∼5 cm x 5 cm) of the antenna, the thermal gradients in the system are relatively small (e.g., maximum 0.4 • C•cm −1 ) [20], [21], [47], [71].…”

Section: Multiphysics Analysis: Performance Over Temperaturementioning

confidence: 99%

Optimized Design and Multiphysics Analysis of a Ka-Band Stacked Antenna for CubeSat Applications

Simone

Lodi

Curreli

et al. 2021

IEEE J. Multiscale Multiphys. Comput. Tech.

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Nowadays, the use of CubeSats for telecommuni-1 cations and interplanetary missions is ever-increasing, thanks 2 to their appealing low-cost character, as well as the space 3 environment, which poses challenging multiphysics constraints 4 on the antenna design. In this framework, the use of Ka-band 5 for communication is explored. We present the design of a 6 stacked patch antenna working across the down-and uplink 7 Ka-bands. Materials and geometry of the radiator have been 8 selected by accounting for the trade-off between electromagnetic, 9 thermal and mechanical requirements. The design of the antenna 10 is performed with a particle swarm optimization algorithm 11 developed to control the bandwidth and matching. A bandwidth of 5.53@33.185 GHz has been obtained, with a gain around 8 13 dB. Furthermore, a multiphysics thermal analysis is performed 14 to verify the operational stability of the optimized array, mounted 15 on a 1U satellite, in a case-study mission. The temperature 16 patterns in the array are evaluated during the orbital period, 17 and the influence of the operative temperature on the antenna 18 responses and gain was considered. We found that the thermal 19 loads can affect the antenna matching. However, thanks to the optimized design, the proposed stacked antenna can operate from 21 -100 • C to 100 • C, with an almost constant gain. Finally, following 22 a damage-tolerant approach, the level of mechanical deformation, 23 which could be induced on the communication system, was 24 studied. The stress analysis reveals that the stacked geometry 25 can be used in a space mission. From the investigation of the 26 strain and displacement field, we found a negligible impact on 27 the antenna performances. 28 Index Terms-CubeSat, multiphysics, Particle Swarm Opti-29 mization, stacked antenna, thermal stresses, Ka-band 30 I. INTRODUCTION 31 CubeSats are low-cost, cube-shaped (10 cm x 10 cm x 10 cm) 32 nano-satellites (1-10 kg) used for remote sensing, telecommu-33 nications, deep-space communication and interplanetary mis-34 sions [1]-[6]. Despite being firstly conceived for educational 35 purposes, the cost-effective features of CubeSats lead to the 36 wide adoption of these spacecraft systems [1], [2], [4]. In the

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“…Two extreme scenarios with: 1 extreme hot; and 2 extreme cold temperatures were taken into account. Bulut (2021) presented a TCS of TURKSAT-3USAT. He analyzed the thermal model of the CubeSat using ThermXL and ESATAN-TMS thermal analysis tools.…”

Section: Introductionmentioning

confidence: 99%

“…Bulut (2021) presented a TCS of TURKSAT-3USAT. He analyzed the thermal model of the CubeSat using ThermXL and ESATAN-TMS thermal analysis tools.…”

Section: Introductionmentioning

confidence: 99%

Establishing reduced thermal mathematical model (RTMM) for a space equipment: an integrative review

Akbulut

Ertas

2022

AEAT

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Purpose The purpose of this study is to, first, provide an overview of the previously conducted works related to thermal analysis of space equipment, including battery packages, especially lithium (Li)-ion ones. Second, the need for a reduced thermal mathematical model (RTMM) and a procedure devising it is defined. Finally, an experimental steady-state temperature distribution test is conducted to finalize the RTMM study. Design/methodology/approach This study was carried out as part of a development project for thermal analysis of Li-ion battery packages used in a space equipment. The study presents certain stages of the design of the battery pack in parallel with battery technology development. Following a literature review, a numerical thermal analysis is conducted; then interface thermal conductance values are found out by means of the first law of thermodynamics; and the study is completed with the help of an experimental test. Findings The study provides key aspects for a successful battery-package thermal design for a space equipment. Additionally, the study summarizes the experimental results used in the RTMM process and the computed thermal conductance values between node couples. Practical implications Thermal analysis is important and vital in space equipment considering their harsh working conditions and environments. Hence, the study provides a RTMM for the thermal analysis of Li-ion battery packages, instead of a full finite element model, to save computational time and CPU usage. The findings are supported by experimental results. Hence, presented details can be used as guidelines for enterprises having a goal of battery package technology achievement, including design and manufacturing. Originality/value After providing a literature review of studies conducted on satellite subsystems including Li-ion batteries, this study presents a clear, complete and verified process of a RTMM for a Li-ion battery package in aero/space structures design. It presents details of building up a model and calculation methodology through an iterative procedure in which an optimization algorithm known as particle swarm optimization (PSO) was benefitted. In the RTMM, additionally, experimental temperature distributions obtained through thermal vacuum test were presented. It has been shown that the model can be used reliably in designing space equipments.

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Thermal design, analysis, and testing of the first Turkish 3U communication CubeSat in low earth orbit

Cited by 15 publications

References 33 publications

Passive thermal control design and analysis of a university-class satellite

Passive thermal control design and analysis of a university-class satellite

Optimized Design and Multiphysics Analysis of a Ka-Band Stacked Antenna for CubeSat Applications

Establishing reduced thermal mathematical model (RTMM) for a space equipment: an integrative review

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