Ablative Z-pinch Pulsed Plasma Thruster

T. E. Markusic; K. A. Polzin; J. Z. Levine; C. A. McLeavey; E. Y. Choueiri

Ablative Z-pinch Pulsed Plasma Thruster

T. E. Markusic, K. A. Polzin, J. Z. Levine, C. A. McLeavey, E. Y. Choueiri

Mechanical & Aerospace Engineering

Research output: Contribution to conference › Paper › peer-review

5 Scopus citations

Abstract

The Z-pinch configuration in gas-fed devices was adapted for an ablative Pulsed Plasma Thruster (PPT). The motivation stems from the promise of the Z-pinch configuration for increasing the thrustto- power ratio and mass utilization efficiency. A series of ablative Z-pinch PPTs were constructed and their performance measured using a swinging gate thrust stand and mass ablation measurements. Several iterations of the design lead to the selection of a thruster with an augmented "spike" inner electrode for more exhaustive testing. Peak performance parameters for this configuration were found to be: I_sp = 574 s, η_t = 7.5%, and T/P = 28 μN/W. In order to determine whether the plamsa was pinching, photographs of the discharge were acquired using a modified thruster having transparent Plexiglas propellant and mesh sidewalls. A current sheet structure leading to a plasma pinch was observed.

Original language	English (US)
State	Published - 2000
Event	36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2000 - Huntsville, AL, United States Duration: Jul 16 2000 → Jul 19 2000

Other

Other	36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2000
Country/Territory	United States
City	Huntsville, AL
Period	7/16/00 → 7/19/00

All Science Journal Classification (ASJC) codes

Space and Planetary Science
Energy Engineering and Power Technology
Aerospace Engineering
Control and Systems Engineering
Electrical and Electronic Engineering
Mechanical Engineering

Cite this

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title = "Ablative Z-pinch Pulsed Plasma Thruster",

abstract = "The Z-pinch configuration in gas-fed devices was adapted for an ablative Pulsed Plasma Thruster (PPT). The motivation stems from the promise of the Z-pinch configuration for increasing the thrustto- power ratio and mass utilization efficiency. A series of ablative Z-pinch PPTs were constructed and their performance measured using a swinging gate thrust stand and mass ablation measurements. Several iterations of the design lead to the selection of a thruster with an augmented {"}spike{"} inner electrode for more exhaustive testing. Peak performance parameters for this configuration were found to be: Isp = 574 s, ηt = 7.5%, and T/P = 28 μN/W. In order to determine whether the plamsa was pinching, photographs of the discharge were acquired using a modified thruster having transparent Plexiglas propellant and mesh sidewalls. A current sheet structure leading to a plasma pinch was observed.",

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year = "2000",

language = "English (US)",

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TY - CONF

T1 - Ablative Z-pinch Pulsed Plasma Thruster

AU - Markusic, T. E.

AU - Polzin, K. A.

AU - Levine, J. Z.

AU - McLeavey, C. A.

AU - Choueiri, E. Y.

PY - 2000

Y1 - 2000

N2 - The Z-pinch configuration in gas-fed devices was adapted for an ablative Pulsed Plasma Thruster (PPT). The motivation stems from the promise of the Z-pinch configuration for increasing the thrustto- power ratio and mass utilization efficiency. A series of ablative Z-pinch PPTs were constructed and their performance measured using a swinging gate thrust stand and mass ablation measurements. Several iterations of the design lead to the selection of a thruster with an augmented "spike" inner electrode for more exhaustive testing. Peak performance parameters for this configuration were found to be: Isp = 574 s, ηt = 7.5%, and T/P = 28 μN/W. In order to determine whether the plamsa was pinching, photographs of the discharge were acquired using a modified thruster having transparent Plexiglas propellant and mesh sidewalls. A current sheet structure leading to a plasma pinch was observed.

AB - The Z-pinch configuration in gas-fed devices was adapted for an ablative Pulsed Plasma Thruster (PPT). The motivation stems from the promise of the Z-pinch configuration for increasing the thrustto- power ratio and mass utilization efficiency. A series of ablative Z-pinch PPTs were constructed and their performance measured using a swinging gate thrust stand and mass ablation measurements. Several iterations of the design lead to the selection of a thruster with an augmented "spike" inner electrode for more exhaustive testing. Peak performance parameters for this configuration were found to be: Isp = 574 s, ηt = 7.5%, and T/P = 28 μN/W. In order to determine whether the plamsa was pinching, photographs of the discharge were acquired using a modified thruster having transparent Plexiglas propellant and mesh sidewalls. A current sheet structure leading to a plasma pinch was observed.

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M3 - Paper

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T2 - 36th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2000

Y2 - 16 July 2000 through 19 July 2000

ER -

Ablative Z-pinch Pulsed Plasma Thruster

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All Science Journal Classification (ASJC) codes

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