implementation of a 80mm refractor telescope in a 2-u cubesat

Paper number

IAC-16,B4,2,3,x33235

Coauthor

Dr. Angel Colin, Universidad Autonoma de Nuevo Leon, Mexico

Coauthor

Dr. Pedro Valdes-Sada, Universidad de Monterrey, Mexico

Coauthor

Dr. Lorenzo Olguin, Universidad de Sonora, Mexico

Coauthor

Dr. Roberto Vazquez, Instituto de Astronomia UNAM, Mexico

Coauthor

Mr. Agustín López-Pérez, Instituto Tecnológico de Ensenada, Mexico

Coauthor

Mr. Jose-Angel Cardona, Universidad Autonoma de Nuevo Leon, Mexico

Coauthor

Mr. Marcelo Villareal-Méndez, Universidad Autonoma de Nuevo Leon, Mexico

Coauthor

Ms. Eunice Padilla, Universidad Autonoma de Nuevo Leon, Mexico

Coauthor

Mr. Brandon Calamaco, Universidad Autonoma de Nuevo Leon, Mexico

Coauthor

Prof. Antonio Gómez-Roa, Universidad Autónoma de Baja California, Mexico

Coauthor

Dr. Bárbara Bermudez, Universidad Autonoma de Nuevo Leon, Mexico

Year

2016

Abstract

\begin{document}

Nowadays, miniaturized satellites play an important roll not only in the academics, but also in scientific projects for observing, monitoring and imaging because of small instruments can be integrated into the payload. On the other hand, the emerging technologies are also used for both education and research to reinforce the future of space engineering [1-3].
 
      The cost for constructing small satellites is very low compared with those of the standard sizes; for instance, a space telescope for astronomical science could exceed the cost in several magnitude orders compared with a small cubesat.
 
       In this paper, we propose the implementation of a refractor telescope (80mm, f/5) into a 2U-Cubesat, which will be used for photometric studies of point-sources such as planets, the brightest stars and asteroids.
  
	The system uses a 1600X1220 CCD camera, coupled to an achromatic lens of 80mm of diameter at f/5. The images are transmitted by a XTEND900, operating from 902 to 928 MHz at 9600 bauds. Attitude control is made by a 3-axis mechanical gyroscope for its positioning to the point-sources. The maximum power consumption of the full system is around 15 Watts. A ground optical telescope of 8 inches at f/10, is configured for tracking the satellite by means the received coordinates from a GPS installed on the satellite.

	This project is supported by Agencia Espacial Mexicana (AEM), through a grant number: AEM-2014-1-248438.\\

Keywords: Cubesat; Telemetry; Photometry.\\

{\bfseries References.}\\

[1] Walker R., et al., ESA Hands-on Space Education Project Activities for University Students: Attracting and Training the Next Generation of Space Engineers, IEEE EDUCON, Education Engineering, 1699-1708, (2010).

[2] Thakker Purvesh and Shiroma Wayne A., Emergence of Pico-and nanosatellites for atmospheric research and technology testing, American Institute of Aeronautics and Astronautics, Inc., Virginia, USA, (2010).

[3] Sandau Rainer, et al., Inventive ideas for micro/nano-satellites the MIC3 report, International Academic of Astronautics, Paris, France, (2015).\\

\end{document}

Abstract document

IAC-16,B4,2,3,x33235.brief.pdf

Manuscript document

IAC-16,B4,2,3,x33235.pdf (🔒 authorized access only).

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