A parametric study of the effect of discharge energy on PPT performance

A. Rezaeiha; Mehdi Anbarloui; Mohammad Farshchi

A parametric study of the effect of discharge energy on PPT performance

A. Rezaeiha, Mehdi Anbarloui, Mohammad Farshchi

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution › Academic › peer-review

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Abstract

Pulsed Plasma Thruster (PPT) is one of the promising space propulsion devices for the micro- and nano-satellites as the following advantages: simplicity, lightweight, robustness, and low power consumption. Moreover, PPT can generate very small impulse bits with high specific impulse. Therefore PPT has great advantages as a precision attitude control. Although μPPTs and their relevant issues have been investigated to a certain degree in recent years, but as a result of the fact that PPT performance is a function of a lot of different parameters like geometrical dimensions, discharge energy, capacitor characteristics, etc and also because of its sophisticated physics; it is felt that issues related to developing an optimized μPPT needs to be investigated in greater detail for a PPT with smaller dimensions and better performance. Therefore, following the development of a laboratory benchmark rectangular breech-fed PPT, a wide range parametric study has been conducted on investigating the effect of discharge energy on PPT performance. The PPT impulse bit varied from about 0.4 mN-s to more than 1.3 mN-s while discharge energy changed from less than 10 J to more than 50 J. Specific impulse also increased from 200 s to 110 s. This paper reviews the results of the mentioned parametric study in brief.

Original language	English
Title of host publication	28th International Symposium on Space Technology and Science (ISTS), Okinawa, Japan, June, 05-12, 2011
Number of pages	6
Publication status	Published - 2011
Externally published	Yes
Event	28th International Symposium on Space Technology and Science, ISTS2011 - Okinawa, Japan Duration: 5 Jun 2011 → 12 Jun 2011 Conference number: 28 https://www.ists.or.jp/2013/

Conference

Conference	28th International Symposium on Space Technology and Science, ISTS2011
Abbreviated title	ISTS
Country/Territory	Japan
City	Okinawa
Period	5/06/11 → 12/06/11
Internet address	https://www.ists.or.jp/2013/

Keywords

Plasma propulsion
Space thruster
Small satellite

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ISTS2011-b-02Final published version, 1.45 MBLicence: CC BY

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title = "A parametric study of the effect of discharge energy on PPT performance",

abstract = "Pulsed Plasma Thruster (PPT) is one of the promising space propulsion devices for the micro- and nano-satellites as the following advantages: simplicity, lightweight, robustness, and low power consumption. Moreover, PPT can generate very small impulse bits with high specific impulse. Therefore PPT has great advantages as a precision attitude control. Although μPPTs and their relevant issues have been investigated to a certain degree in recent years, but as a result of the fact that PPT performance is a function of a lot of different parameters like geometrical dimensions, discharge energy, capacitor characteristics, etc and also because of its sophisticated physics; it is felt that issues related to developing an optimized μPPT needs to be investigated in greater detail for a PPT with smaller dimensions and better performance. Therefore, following the development of a laboratory benchmark rectangular breech-fed PPT, a wide range parametric study has been conducted on investigating the effect of discharge energy on PPT performance. The PPT impulse bit varied from about 0.4 mN-s to more than 1.3 mN-s while discharge energy changed from less than 10 J to more than 50 J. Specific impulse also increased from 200 s to 110 s. This paper reviews the results of the mentioned parametric study in brief.",

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year = "2011",

language = "English",

booktitle = "28th International Symposium on Space Technology and Science (ISTS), Okinawa, Japan, June, 05-12, 2011",

note = "28th International Symposium on Space Technology and Science, ISTS2011, ISTS ; Conference date: 05-06-2011 Through 12-06-2011",

url = "https://www.ists.or.jp/2013/",

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TY - GEN

T1 - A parametric study of the effect of discharge energy on PPT performance

AU - Rezaeiha, A.

AU - Anbarloui, Mehdi

AU - Farshchi, Mohammad

N1 - Conference code: 28

PY - 2011

Y1 - 2011

N2 - Pulsed Plasma Thruster (PPT) is one of the promising space propulsion devices for the micro- and nano-satellites as the following advantages: simplicity, lightweight, robustness, and low power consumption. Moreover, PPT can generate very small impulse bits with high specific impulse. Therefore PPT has great advantages as a precision attitude control. Although μPPTs and their relevant issues have been investigated to a certain degree in recent years, but as a result of the fact that PPT performance is a function of a lot of different parameters like geometrical dimensions, discharge energy, capacitor characteristics, etc and also because of its sophisticated physics; it is felt that issues related to developing an optimized μPPT needs to be investigated in greater detail for a PPT with smaller dimensions and better performance. Therefore, following the development of a laboratory benchmark rectangular breech-fed PPT, a wide range parametric study has been conducted on investigating the effect of discharge energy on PPT performance. The PPT impulse bit varied from about 0.4 mN-s to more than 1.3 mN-s while discharge energy changed from less than 10 J to more than 50 J. Specific impulse also increased from 200 s to 110 s. This paper reviews the results of the mentioned parametric study in brief.

AB - Pulsed Plasma Thruster (PPT) is one of the promising space propulsion devices for the micro- and nano-satellites as the following advantages: simplicity, lightweight, robustness, and low power consumption. Moreover, PPT can generate very small impulse bits with high specific impulse. Therefore PPT has great advantages as a precision attitude control. Although μPPTs and their relevant issues have been investigated to a certain degree in recent years, but as a result of the fact that PPT performance is a function of a lot of different parameters like geometrical dimensions, discharge energy, capacitor characteristics, etc and also because of its sophisticated physics; it is felt that issues related to developing an optimized μPPT needs to be investigated in greater detail for a PPT with smaller dimensions and better performance. Therefore, following the development of a laboratory benchmark rectangular breech-fed PPT, a wide range parametric study has been conducted on investigating the effect of discharge energy on PPT performance. The PPT impulse bit varied from about 0.4 mN-s to more than 1.3 mN-s while discharge energy changed from less than 10 J to more than 50 J. Specific impulse also increased from 200 s to 110 s. This paper reviews the results of the mentioned parametric study in brief.

KW - Plasma propulsion

KW - Space thruster

KW - Small satellite

UR - https://www.ists.or.jp/2011/

M3 - Conference contribution

BT - 28th International Symposium on Space Technology and Science (ISTS), Okinawa, Japan, June, 05-12, 2011

T2 - 28th International Symposium on Space Technology and Science, ISTS2011

Y2 - 5 June 2011 through 12 June 2011

ER -

A parametric study of the effect of discharge energy on PPT performance

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Conference

Keywords

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