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Thermal characterisation analysis and modelling techniques for CubeSat-sized spacecrafts

Published online by Cambridge University Press:  17 October 2017

Anwar Ali ,
Khalil Ullah ,
Hafeez Ur Rehman ,
Inam Bari  and
Leonardo M. Reyneri
Anwar Ali*
Affiliation:
Department of Electrical Technology, University of Technology (UoT), Nowshera, Pakistan
Khalil Ullah
Affiliation:
Department of Electrical Engineering, National University of Computers & Emerging Sciences, Peshawar, Pakistan
Hafeez Ur Rehman
Affiliation:
Department of Computer Science, National University of Computers & Emerging Sciences, Peshawar, Pakistan
Inam Bari
Affiliation:
Department of Electrical Engineering, National University of Computers & Emerging Sciences, Peshawar, Pakistan
Leonardo M. Reyneri
Affiliation:
Department of Electronics and Telecommunications, Politecnico di Torino, Torino, Italy
*
[email protected]
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Abstract

Recently, universities and Small and Medium Enterprises (SMEs) have initiated the development of nanosatellites because of their low cost, small size and short development time. The challenging aspects for these satellites are their small surface area for heat dissipation due to their limited size. There is not enough space for mounting radiators for heat dissipation. As a result, thermal modelling becomes a very important element in designing a small satellite. The paper presents detailed and simplified generic thermal models for CubeSat panels and also for the complete satellite. The detailed model takes all thermal resistances associated with the respective layers into account, while in the simplified model, the layers with similar materials have been combined and are represented by a single thermal resistance. The proposed models are then applied to a CubeSat standard nanosatellite called AraMiS-C1, developed at Politecnico di Torino, Italy. Thermal resistance measured through both models is compared, and the results are similar. The absorbed power and the corresponding temperature differences between different points of the single panel and complete satellite are measured. In order to verify the theoretical results, thermal resistance of the AraMiS-C1 and its panels are measured through experimental set-ups. Theoretical and measured values are in close agreement.

Keywords

satellitethermal modellingthermal resistancemodule
Type
Research Article
Information
The Aeronautical Journal , Volume 121 , Issue 1246 , December 2017 , pp. 1858 - 1878
Copyright
Copyright © Royal Aeronautical Society 2017 

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References

REFERENCES

1. Munakata, R. CubeSat design specifications, Rev.12, California State Polytechnic University, 2009.Google Scholar
2. De Los Rios, J.C., Roascio, D., Reyneri, L., Sansoè, C., Passerone, C., Del Corso, D., Bruno, M., Hernandez, A. and Vallan, A. Aramis: A fine-grained modular architecture for reconfigurable space missions, 1st Conference on University Satellite Missions, 24 January 2011, Rome, Italy.Google Scholar
3. Mughal, M.R., De Los Rios, J.C., Reyneri, L.M. and Ali, A. Scalable plug and play tiles for modular nanosatellites, 63rd International Astronautical Congress, 1–5 October 2012, Naples, Italy.Google Scholar
4. Mughal, M.R., Ali, A. and Reyneri, L.M. Plug-and-play design approach to smart harness for modular small satellites, Acta Astronautica, February 2014, 94, (2), pp 754-764.CrossRefGoogle Scholar
5. Speretta, S., Reyneri, L.M., Sanso´e, C., Tranchero, M., Passerone, C. and Del Corso, D. Modular architecture for satellites, 58th IAC, 24–28 September 2007, Hyderabad, India.Google Scholar
6. Ali, A., Reyneri, L.M., De Los Rios, J.C. and Ali, H. Innovative power management tile for nanosatellites, 63rd International Astronautical Congress, 1–5 October 2012, Naples, Italy.Google Scholar
7. Ali, A., Mughal, M.R., Ali, H. and Reyneri, L.M. Innovative power management, attitude determination and control tile for CubeSat standard nanosatellites, Acta Astronautica, March–April 2014, 96, pp 116-127.Google Scholar
8. Ali, A., Mughal, M.R., Ali, H., Reyneri, L.M. and Aman, M.N. Design, implementation, and thermal modeling of embedded reconfigurable magnetorquer system for nanosatellites, IEEE Transactions on Aerospace and Electronic Systems, October 2015, 51, (4), pp 2669-2679. doi: 10.1109/TAES.2015.130621.Google Scholar
9. Thermal analysis of spacecraft hardware guideline. NASA Design Guidelines. GD-AP-2302.Google Scholar
10. Ali, A. Power management, attitude determination and control systems of small satellites, PhD thesis, Politecnico di Torino, Italy Available at: http://porto.polito.it/2535715/.Google Scholar
11. Satellite thermal control engineering, prepared for SME 2004, European Space Agency, ESTEC, Thermal and Structure Division, Available at: http://www.tak2000.com/data/Satellite_TC.pdf.Google Scholar
12. Ohm's law in thermal domain, Available at: ftp://ftp.dei.polimi.it/outgoing/Massimo.Ghioni/Power%20Electronics%20/Thermal/Advanced%20Power%20Dissipation%20and%20Dynamic%20Thermal%20Analysis.pdf.Google Scholar
13. Fourier's law of heat conduction, Available at: http://www.me.umn.edu/courses/old_me_course_pages/me3333/essays/essay%203.pdf.Google Scholar
14. Richmond, J.A. Adaptive thermal modeling architecture for small satellite applications, Department of Aeronautics and Astronautics, May 2010, MIT, Cambridge, Massachusetts, US.Google Scholar
15. Moffitt, B.A. and Batty, J.C. Predictive thermal analysis of the combat sentinel satellite, Department of Mechanical and Aerospace Engineering, August 12-15, 2012, Utah State University, Logan, Utah, US.Google Scholar