Design of an electric power system with incorporation of a phased array antenna for OLFAR

J.M. Klein, A. Budianu, Marinus Jan Bentum, S. Engelen, C.J.M. Verhoeven

Research output: Chapter in Book/Report/Conference proceedingConference contributionAcademicpeer-review

Abstract

The Orbiting Low Frequency Antennas for Radio Astronomy (OLFAR) project is investigating the feasibility of an orbiting low frequency radio telescope. The radio telescope is formed using a swarm of nano-satellites equipped with astronomical antennas, conceivably orbiting the Moon or the second Lagrange-point of the Earth-Moon system. In these orbits, when at the far-side of the Moon as seen from the Earth, the low frequency radio signals originating from Earth are deemed to be blocked by the Moon, considerably reducing the amount of interference. Such a telescope, with its unique vantage point, will open up a new field in astronomical research; yet the power demands, as well as the data rates involved are very challenging. This paper details the design of the highly integrated Electric Power System (EPS) of an OLFAR satellite. The most demanding power mode of the mission is during exchange and pre-processing of science data. In this mode, each individual satellite has an average power consumption of 30W. Similar power demand is expected during the orbit transfer phases, in which the main electric thruster has a duty cycle close to unity, and places additional constraints on the attitude control of the satellite. Such power levels, for extended periods of time, have rarely been shown in such a small form factor. A phased antenna array is used for the downlink, and is constructed from an array of small-patch antennas, in order to achieve sufficient data rates. In an OLFAR satellite, the collection surface of the solar array is shared with this antenna. The tracking mechanism of solar array and antenna uses electric motors, to allow tracking the Sun or the ground station in a three-axis controlled attitude mode. The phased antenna array in turn allows fine pointing when required. The design of the Electric Power System is based on a Maximum Power Point Tracker-fed battery bank, using solar deployable panels. Care is taken to reduce the number of charge-discharge cycles encountered by the batteries, allowing for an increase in the expected system lifetime. Also the thermal aspects of the power levels involved both in the solar cells, as well as the phased array have been addressed.
Original languageUndefined
Title of host publicationProceeding of the 64th IAC International Astronautical Congress
Place of PublicationBeijing, China
PublisherInternational Astronautical Federation (IAF)
Pages1-6
Number of pages6
ISBN (Print)1995-6258
Publication statusPublished - 26 Sep 2013
Event64th International Astronautical Congress, IAC 2013 - Beijing, China
Duration: 23 Sep 201327 Sep 2013
Conference number: 64

Publication series

Name
PublisherInternational Astronautical Federation (IAF)
ISSN (Print)1995-6258

Conference

Conference64th International Astronautical Congress, IAC 2013
Abbreviated titleIAC
CountryChina
CityBeijing
Period23/09/1327/09/13

Keywords

  • EWI-23826
  • METIS-300078
  • IR-87471

Cite this

Klein, J. M., Budianu, A., Bentum, M. J., Engelen, S., & Verhoeven, C. J. M. (2013). Design of an electric power system with incorporation of a phased array antenna for OLFAR. In Proceeding of the 64th IAC International Astronautical Congress (pp. 1-6). Beijing, China: International Astronautical Federation (IAF).
Klein, J.M. ; Budianu, A. ; Bentum, Marinus Jan ; Engelen, S. ; Verhoeven, C.J.M. / Design of an electric power system with incorporation of a phased array antenna for OLFAR. Proceeding of the 64th IAC International Astronautical Congress. Beijing, China : International Astronautical Federation (IAF), 2013. pp. 1-6
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abstract = "The Orbiting Low Frequency Antennas for Radio Astronomy (OLFAR) project is investigating the feasibility of an orbiting low frequency radio telescope. The radio telescope is formed using a swarm of nano-satellites equipped with astronomical antennas, conceivably orbiting the Moon or the second Lagrange-point of the Earth-Moon system. In these orbits, when at the far-side of the Moon as seen from the Earth, the low frequency radio signals originating from Earth are deemed to be blocked by the Moon, considerably reducing the amount of interference. Such a telescope, with its unique vantage point, will open up a new field in astronomical research; yet the power demands, as well as the data rates involved are very challenging. This paper details the design of the highly integrated Electric Power System (EPS) of an OLFAR satellite. The most demanding power mode of the mission is during exchange and pre-processing of science data. In this mode, each individual satellite has an average power consumption of 30W. Similar power demand is expected during the orbit transfer phases, in which the main electric thruster has a duty cycle close to unity, and places additional constraints on the attitude control of the satellite. Such power levels, for extended periods of time, have rarely been shown in such a small form factor. A phased antenna array is used for the downlink, and is constructed from an array of small-patch antennas, in order to achieve sufficient data rates. In an OLFAR satellite, the collection surface of the solar array is shared with this antenna. The tracking mechanism of solar array and antenna uses electric motors, to allow tracking the Sun or the ground station in a three-axis controlled attitude mode. The phased antenna array in turn allows fine pointing when required. The design of the Electric Power System is based on a Maximum Power Point Tracker-fed battery bank, using solar deployable panels. Care is taken to reduce the number of charge-discharge cycles encountered by the batteries, allowing for an increase in the expected system lifetime. Also the thermal aspects of the power levels involved both in the solar cells, as well as the phased array have been addressed.",
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year = "2013",
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Klein, JM, Budianu, A, Bentum, MJ, Engelen, S & Verhoeven, CJM 2013, Design of an electric power system with incorporation of a phased array antenna for OLFAR. in Proceeding of the 64th IAC International Astronautical Congress. International Astronautical Federation (IAF), Beijing, China, pp. 1-6, 64th International Astronautical Congress, IAC 2013, Beijing, China, 23/09/13.

Design of an electric power system with incorporation of a phased array antenna for OLFAR. / Klein, J.M.; Budianu, A.; Bentum, Marinus Jan; Engelen, S.; Verhoeven, C.J.M.

Proceeding of the 64th IAC International Astronautical Congress. Beijing, China : International Astronautical Federation (IAF), 2013. p. 1-6.

Research output: Chapter in Book/Report/Conference proceedingConference contributionAcademicpeer-review

TY - GEN

T1 - Design of an electric power system with incorporation of a phased array antenna for OLFAR

AU - Klein, J.M.

AU - Budianu, A.

AU - Bentum, Marinus Jan

AU - Engelen, S.

AU - Verhoeven, C.J.M.

PY - 2013/9/26

Y1 - 2013/9/26

N2 - The Orbiting Low Frequency Antennas for Radio Astronomy (OLFAR) project is investigating the feasibility of an orbiting low frequency radio telescope. The radio telescope is formed using a swarm of nano-satellites equipped with astronomical antennas, conceivably orbiting the Moon or the second Lagrange-point of the Earth-Moon system. In these orbits, when at the far-side of the Moon as seen from the Earth, the low frequency radio signals originating from Earth are deemed to be blocked by the Moon, considerably reducing the amount of interference. Such a telescope, with its unique vantage point, will open up a new field in astronomical research; yet the power demands, as well as the data rates involved are very challenging. This paper details the design of the highly integrated Electric Power System (EPS) of an OLFAR satellite. The most demanding power mode of the mission is during exchange and pre-processing of science data. In this mode, each individual satellite has an average power consumption of 30W. Similar power demand is expected during the orbit transfer phases, in which the main electric thruster has a duty cycle close to unity, and places additional constraints on the attitude control of the satellite. Such power levels, for extended periods of time, have rarely been shown in such a small form factor. A phased antenna array is used for the downlink, and is constructed from an array of small-patch antennas, in order to achieve sufficient data rates. In an OLFAR satellite, the collection surface of the solar array is shared with this antenna. The tracking mechanism of solar array and antenna uses electric motors, to allow tracking the Sun or the ground station in a three-axis controlled attitude mode. The phased antenna array in turn allows fine pointing when required. The design of the Electric Power System is based on a Maximum Power Point Tracker-fed battery bank, using solar deployable panels. Care is taken to reduce the number of charge-discharge cycles encountered by the batteries, allowing for an increase in the expected system lifetime. Also the thermal aspects of the power levels involved both in the solar cells, as well as the phased array have been addressed.

AB - The Orbiting Low Frequency Antennas for Radio Astronomy (OLFAR) project is investigating the feasibility of an orbiting low frequency radio telescope. The radio telescope is formed using a swarm of nano-satellites equipped with astronomical antennas, conceivably orbiting the Moon or the second Lagrange-point of the Earth-Moon system. In these orbits, when at the far-side of the Moon as seen from the Earth, the low frequency radio signals originating from Earth are deemed to be blocked by the Moon, considerably reducing the amount of interference. Such a telescope, with its unique vantage point, will open up a new field in astronomical research; yet the power demands, as well as the data rates involved are very challenging. This paper details the design of the highly integrated Electric Power System (EPS) of an OLFAR satellite. The most demanding power mode of the mission is during exchange and pre-processing of science data. In this mode, each individual satellite has an average power consumption of 30W. Similar power demand is expected during the orbit transfer phases, in which the main electric thruster has a duty cycle close to unity, and places additional constraints on the attitude control of the satellite. Such power levels, for extended periods of time, have rarely been shown in such a small form factor. A phased antenna array is used for the downlink, and is constructed from an array of small-patch antennas, in order to achieve sufficient data rates. In an OLFAR satellite, the collection surface of the solar array is shared with this antenna. The tracking mechanism of solar array and antenna uses electric motors, to allow tracking the Sun or the ground station in a three-axis controlled attitude mode. The phased antenna array in turn allows fine pointing when required. The design of the Electric Power System is based on a Maximum Power Point Tracker-fed battery bank, using solar deployable panels. Care is taken to reduce the number of charge-discharge cycles encountered by the batteries, allowing for an increase in the expected system lifetime. Also the thermal aspects of the power levels involved both in the solar cells, as well as the phased array have been addressed.

KW - EWI-23826

KW - METIS-300078

KW - IR-87471

M3 - Conference contribution

SN - 1995-6258

SP - 1

EP - 6

BT - Proceeding of the 64th IAC International Astronautical Congress

PB - International Astronautical Federation (IAF)

CY - Beijing, China

ER -

Klein JM, Budianu A, Bentum MJ, Engelen S, Verhoeven CJM. Design of an electric power system with incorporation of a phased array antenna for OLFAR. In Proceeding of the 64th IAC International Astronautical Congress. Beijing, China: International Astronautical Federation (IAF). 2013. p. 1-6