• Yerkebulan Nurgizat Computer Lab of Paris 6 (LIP ), Sorbonne University
  • Alan Dias Rizo Computer Lab of Paris 6 (LIP ), Sorbonne University


Ключевые слова:

Nanosatellite, solar sensors, vector


Nanosatellite (NS) began to perform complex missions that require high orientation. In this research, we developed a mathematical model of solar sensors to determine the orientation of a NS. Various moments of obtaining the angle of the sun's rays when they hit the solar sensors were presented. The test results of the solar sensors used to simulate various orbit scenarios are described in detail, and graphs of the solar sensor readings are plotted based on the results obtained.

The article deals with modeling the motion of a NS in orbit. The NS is equipped with 6 solar panels. The VTS software was used to simulate the motion of the NS. Also, in the study of determining the orientation, two different problems were considered, that is, when the satellite is in the shadow part of the earth and when it is in the solar part of the earth. For these tasks, a mathematical model for determining the orientation was built. This method is very relevant for the study of small spacecraft.

Биографии авторов

Yerkebulan Nurgizat, Computer Lab of Paris 6 (LIP ), Sorbonne University

Paris, France,

Alan Dias Rizo , Computer Lab of Paris 6 (LIP ), Sorbonne University

doctoral student, Lip6, Sorbonne University

Библиографические ссылки

[1] Ubbels, W.J.; Bonnema, A.K. Delfi-C3: A student NS as a test-bed for thin film solar cells and wireless onboard communication. In Proceedings of the 2nd International Conference on Recent Advances in Space Technologies, Istanbul, Turkey, 9–11 June 2005; pp. 167–172.

[2] Santoni, F.; Piergentili, F.; Donati, S.; Perelli, M.; Negri, A.; Marino, M. An innovative deployable solar panel system for Cubesats. Acta Astronaut. 2014, 95, 210–217. [CrossRef]

[3] Vertat, I.; Vobornik, A. E_cient and reliable solar panels for small CubeSat picosatellites. Int. J. Photoenergy 2014, 2014. [CrossRef]

[4] Young, D.; Cutler, J.W.; Mancewicz, J.; Ridley, A.J. Maximizing photovoltaic power generation of a space-dart configured satellite. Acta Astronaut. 2015, 111, 283–299.

[5] Rawashdeh, S.A.; Lumpp, J.E. Aerodynamic stability for CubeSats at ISS orbit. J. Small Satell. 2013, 2, 85–104.

[6] Armstrong, J.; Casey, C.; Creamer, G.; Dutchover, G. Pointing control for low altitude triple CubeSat space darts. In Proceedings of the 23rd Annual AIAA/USU Conference Small Satellite, Logan, UT, USA, 10–13 August 2009.

[7] Jenkins, A. The Sun’s position in the sky. Eur. J. Phys. 2013, 34, 633–652. [CrossRef]

[8] M Zahran. In Orbit Performance of LEO Satellite Electrical Power Subsystem - SW Package for Modelling and Simulation Based on MatLab . 7 GUI. 2006(January 2006):379{384, 2006.

[9] Hyung-Chul Lim, Hyo-Choong Bang, and Sang-Jong Lee. Adaptive Backstepping Control for Satellite Formation Flying With Mass Uncertainty. Journal of Astronomy and Space Sciences, 23(4):405{414, 2006.

[10]. Rodionov S.A. Osnovy optiki. Konspekt lekcij. –SPb: SPb GITMO (TU), 2000. -167s.

[11] VTS 3.5 User Manual (VTS-MU-G-69-SPB-7.3)

[12] CelesTrak: Current NORAD Two-Line Element Sets. Available at, (Accessed on 08/04/2021).

[13] Filho, Edemar Morsch, Seman, Laio Oriel, Rigo, Cezar Antônio, Nicolau, Vicente de Paulo, Ovejero, Raúl García, Leithardt, Valderi Reis Quietinho, 2020, Energies, Irradiation Flux Modelling for Thermal–Electrical Simulation of CubeSats: Orbit, Attitude and Radiation Integration doi:10.3390/en13246691




Как цитировать

Nurgizat, Y., & Dias Rizo , A. (2021). NANOSATELLITE MOTION SIMULATION FOR TESTING THE SUN SENSOR. Вестник КазАТК, 118(3), 34–42.



Автоматика, телемеханика, связь, электроэнергетика, информационные системы