Concerning the design of a novel electromagnetic launcher for earth-to-orbit micro- and nanosatellite systems

Ugur Hasirci; Abdulkadir Balikci; Zivan Zabar; Leo Birenbaum

doi:10.1109/TPS.2010.2076289

Concerning the design of a novel electromagnetic launcher for earth-to-orbit micro- and nanosatellite systems

Ugur Hasirci, Abdulkadir Balikci, Zivan Zabar, Leo Birenbaum

Electrical and Computer Engineering

Research output: Contribution to journal › Article › peer-review

Abstract

This paper presents an alternative launcher design for Earth-to-orbit (ETO) micro- and nanosatellite systems. The main goal of the design is to reduce the cost of the launching operation. This paper also addresses the calculation of the energy required for the launching operation and the selection of a power source for the designed satellite launcher. The method introduced here proposes a vertical-takeoff electromagnetic launcher for ETO micro- and nanosatellite systems. The design specifications are 7-km/s muzzle velocity and 30000-gee acceleration for a 10-kg payload. It is expected that the proposed design would present a viable alternative to conventional launchers for ETO systems.

Original language	English (US)
Article number	5595026
Pages (from-to)	498-503
Number of pages	6
Journal	IEEE Transactions on Plasma Science
Volume	39
Issue number	1 PART 1
DOIs	https://doi.org/10.1109/TPS.2010.2076289
State	Published - Jan 2011

Keywords

Coilguns
electromagnetic launchers (EMLs)
microsatellite systems
nanosatellite systems
railguns

ASJC Scopus subject areas

Nuclear and High Energy Physics
Condensed Matter Physics

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10.1109/TPS.2010.2076289

Cite this

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title = "Concerning the design of a novel electromagnetic launcher for earth-to-orbit micro- and nanosatellite systems",

abstract = "This paper presents an alternative launcher design for Earth-to-orbit (ETO) micro- and nanosatellite systems. The main goal of the design is to reduce the cost of the launching operation. This paper also addresses the calculation of the energy required for the launching operation and the selection of a power source for the designed satellite launcher. The method introduced here proposes a vertical-takeoff electromagnetic launcher for ETO micro- and nanosatellite systems. The design specifications are 7-km/s muzzle velocity and 30000-gee acceleration for a 10-kg payload. It is expected that the proposed design would present a viable alternative to conventional launchers for ETO systems.",

keywords = "Coilguns, electromagnetic launchers (EMLs), microsatellite systems, nanosatellite systems, railguns",

author = "Ugur Hasirci and Abdulkadir Balikci and Zivan Zabar and Leo Birenbaum",

note = "Funding Information: Manuscript received January 11, 2010; revised April 2, 2010, June 30, 2010, and August 27, 2010; accepted August 30, 2010. Date of publication October 7, 2010; date of current version January 7, 2011. This work was supported in part by The Scientific and Technological Research Council of Turkey (T{\"U}B{\'Y}TAK) under Grant 107E107.",

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doi = "10.1109/TPS.2010.2076289",

language = "English (US)",

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AU - Hasirci, Ugur

AU - Balikci, Abdulkadir

AU - Zabar, Zivan

AU - Birenbaum, Leo

N1 - Funding Information: Manuscript received January 11, 2010; revised April 2, 2010, June 30, 2010, and August 27, 2010; accepted August 30, 2010. Date of publication October 7, 2010; date of current version January 7, 2011. This work was supported in part by The Scientific and Technological Research Council of Turkey (TÜBÝTAK) under Grant 107E107.

PY - 2011/1

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N2 - This paper presents an alternative launcher design for Earth-to-orbit (ETO) micro- and nanosatellite systems. The main goal of the design is to reduce the cost of the launching operation. This paper also addresses the calculation of the energy required for the launching operation and the selection of a power source for the designed satellite launcher. The method introduced here proposes a vertical-takeoff electromagnetic launcher for ETO micro- and nanosatellite systems. The design specifications are 7-km/s muzzle velocity and 30000-gee acceleration for a 10-kg payload. It is expected that the proposed design would present a viable alternative to conventional launchers for ETO systems.

AB - This paper presents an alternative launcher design for Earth-to-orbit (ETO) micro- and nanosatellite systems. The main goal of the design is to reduce the cost of the launching operation. This paper also addresses the calculation of the energy required for the launching operation and the selection of a power source for the designed satellite launcher. The method introduced here proposes a vertical-takeoff electromagnetic launcher for ETO micro- and nanosatellite systems. The design specifications are 7-km/s muzzle velocity and 30000-gee acceleration for a 10-kg payload. It is expected that the proposed design would present a viable alternative to conventional launchers for ETO systems.

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KW - electromagnetic launchers (EMLs)

KW - microsatellite systems

KW - nanosatellite systems

KW - railguns

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Concerning the design of a novel electromagnetic launcher for earth-to-orbit micro- and nanosatellite systems

Abstract

Keywords

ASJC Scopus subject areas

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