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EN
Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite
Abstract
Full electric propulsion system becomes popular recently and getting more common in the communication satellite industry. Full electric or hybrid propulsion selection causes results in significant reduction in satellite propellant mass. Conventional full chemical satellite propellant mass is roughly 2/3 of launch mass so this huge reduction in propellant mass changes satellite design and preferences. Depending on satellite size and launch vehicle performance, full electric satellite requires 3-4 times less propellant compared to full chemical satellite and 1-2 times less propellant compared to the hybrid system. Satellite launch mass can be reduced by 40% for full electric propulsion and 15% for hybrid propulsion hence launch cost can be decreased by 40% and 15 % with the benefit of reducing propellant mass. It is possible to extend satellite communication capacity average 30 transponders for full electric and average 10 transponders for a hybrid system by using the benefit of propellant mass reduction. It takes 4-8 months to reach geostationary orbit for full electric satellite but in a chemical propulsion satellite, it takes a few days. Satellite subjects to additional radiation due to this long trip and hence additional aging. Expected revenue loss is another issue and conventional insurance policy needs an amendment to be in line with electric propulsion technology. The development of full electric satellite lowers the cost per transponder significantly.
Keywords
Thanks
We would like to thank Turksat AS for its invaluable support.
References
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Details
Primary Language
English
Subjects
Software Engineering (Other)
Journal Section
Research Article
Publication Date
December 31, 2019
Submission Date
December 2, 2019
Acceptance Date
December 18, 2019
Published in Issue
Year 2019 Volume: 2 Number: 3
APA
Oz, İ., & Yılmaz, Ü. (2019). Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite. Sakarya University Journal of Computer and Information Sciences, 2(3), 124-133. https://doi.org/10.35377/saucis.02.03.654206
AMA
1.Oz İ, Yılmaz Ü. Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite. SAUCIS. 2019;2(3):124-133. doi:10.35377/saucis.02.03.654206
Chicago
Oz, İbrahim, and Ü.cezmi Yılmaz. 2019. “Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite”. Sakarya University Journal of Computer and Information Sciences 2 (3): 124-33. https://doi.org/10.35377/saucis.02.03.654206.
EndNote
Oz İ, Yılmaz Ü (December 1, 2019) Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite. Sakarya University Journal of Computer and Information Sciences 2 3 124–133.
IEEE
[1]İ. Oz and Ü. Yılmaz, “Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite”, SAUCIS, vol. 2, no. 3, pp. 124–133, Dec. 2019, doi: 10.35377/saucis.02.03.654206.
ISNAD
Oz, İbrahim - Yılmaz, Ü.cezmi. “Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite”. Sakarya University Journal of Computer and Information Sciences 2/3 (December 1, 2019): 124-133. https://doi.org/10.35377/saucis.02.03.654206.
JAMA
1.Oz İ, Yılmaz Ü. Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite. SAUCIS. 2019;2:124–133.
MLA
Oz, İbrahim, and Ü.cezmi Yılmaz. “Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite”. Sakarya University Journal of Computer and Information Sciences, vol. 2, no. 3, Dec. 2019, pp. 124-33, doi:10.35377/saucis.02.03.654206.
Vancouver
1.İbrahim Oz, Ü.cezmi Yılmaz. Design Tradeoffs in Full Electric, Hybrid and Full Chemical Propulsion Communication Satellite. SAUCIS. 2019 Dec. 1;2(3):124-33. doi:10.35377/saucis.02.03.654206
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