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Secondary Species Emission and Behavior for Electrospray Thrusters.

紀錄類型:	書目-電子資源 : Monograph/item
正題名/作者:	Secondary Species Emission and Behavior for Electrospray Thrusters./
作者:	Uchizono, Nolan Michael.
出版者:	Ann Arbor : ProQuest Dissertations & Theses, : 2022,
面頁冊數:	157 p.
附註:	Source: Dissertations Abstracts International, Volume: 84-01, Section: B.
Contained By:	Dissertations Abstracts International84-01B.
標題:	Aerospace engineering. -
電子資源:	http://pqdd.sinica.edu.tw/twdaoapp/servlet/advanced?query=29253197
ISBN:	9798834011255

Secondary Species Emission and Behavior for Electrospray Thrusters.
Uchizono, Nolan Michael.

Secondary Species Emission and Behavior for Electrospray Thrusters. - Ann Arbor : ProQuest Dissertations & Theses, 2022 - 157 p.

Source: Dissertations Abstracts International, Volume: 84-01, Section: B.

Thesis (Ph.D.)--University of California, Los Angeles, 2022.

This item must not be sold to any third party vendors.

Electrospray propulsion devices employ strong electric fields to extract high velocity droplets and molecular ions from a liquid propellant. When these constituents strike downstream surfaces, impact processes can lead to the emission of a diverse set of secondary species, including electrons, atomic ions, molecular ions, and subsidiary droplets. The objective of this research is to examine the emission and transport of secondary species in electrospray thrusters to understand the effects on thruster life, performance, spacecraft interactions, and terrestrial facility effects. This dissertation presents theoretical, analytical, and experimental investigations of electrospray operation in vacuum facilities to show that secondary species emission (SSE) plays a significant role in the behavior of electrospray thrusters during ground testing. First, an analysis of SSE mechanisms and onset thresholds showed that SSE occurs in the regimes where electrospray thrusters commonly operate. Therefore, SSE must be carefully considered for accurate measurements and determination of performance and life. A series of experiments were conducted to investigate the consequence of SSE on electrospray thruster operation. A beam target biasing experiment was conducted to demonstrate the impact of SSE on thruster-to-facility coupling, which introduces significant uncertainty in thruster lifetime measurements. A novel "SSE probe" diagnostic was developed and used to obtain the first-ever angular distributions of positive and negative SSE yields for an electrospray thruster. An optical emission spectroscopy study was conducted to show that glow discharges observed in electrospray thrusters during vacuum operation are a consequence of SSE; this observation is in direct contrast to common postulations that glows are intrinsic to electrospray operation. Two analytical models were developed to study SSE impact on thruster performance and lifetime. The first model was a one-dimensional heat and mass flux analysis of an ionic liquid ion source, which showed that SSE-induced Ohmic dissipation can significantly affect thruster performance. The second model, named the "Electrospray SSE Control-volume Analysis for Resolving Ground Operation of Thrusters" (ESCARGOT) invokes conservation of charge to derive a set of governing equations that describes the emission and transport of secondary species throughout an electrospray thruster and testing facility. The model relies on geometric factors obtained from numerical simulations, and experimentally-obtained SSE yields to correct for SSE-induced current measurement uncertainty in thruster performance and life testing. Therefore, the ESCARGOT model serves as an important link to determine accurate in-space thruster life and performance predictions based on terrestrial qualification testing. Overall, this work reveals the critical importance of SSE to electrospray thruster performance, life, facility effects, and space interactions; and provides both experimental and modeling techniques to assess their impact for a range of operating and test conditions.

ISBN: 9798834011255Subjects--Topical Terms:

1002622
Aerospace engineering.
Subjects--Index Terms:

Electric propulsion

Secondary Species Emission and Behavior for Electrospray Thrusters.
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245 1 0 $a Secondary Species Emission and Behavior for Electrospray Thrusters.
260 1 $a Ann Arbor : $b ProQuest Dissertations & Theses, $c 2022
300 $a 157 p.
500 $a Source: Dissertations Abstracts International, Volume: 84-01, Section: B.
500 $a Advisor: Wirz, Richard E.
502 $a Thesis (Ph.D.)--University of California, Los Angeles, 2022.
506 $a This item must not be sold to any third party vendors.
520 $a Electrospray propulsion devices employ strong electric fields to extract high velocity droplets and molecular ions from a liquid propellant. When these constituents strike downstream surfaces, impact processes can lead to the emission of a diverse set of secondary species, including electrons, atomic ions, molecular ions, and subsidiary droplets. The objective of this research is to examine the emission and transport of secondary species in electrospray thrusters to understand the effects on thruster life, performance, spacecraft interactions, and terrestrial facility effects. This dissertation presents theoretical, analytical, and experimental investigations of electrospray operation in vacuum facilities to show that secondary species emission (SSE) plays a significant role in the behavior of electrospray thrusters during ground testing. First, an analysis of SSE mechanisms and onset thresholds showed that SSE occurs in the regimes where electrospray thrusters commonly operate. Therefore, SSE must be carefully considered for accurate measurements and determination of performance and life. A series of experiments were conducted to investigate the consequence of SSE on electrospray thruster operation. A beam target biasing experiment was conducted to demonstrate the impact of SSE on thruster-to-facility coupling, which introduces significant uncertainty in thruster lifetime measurements. A novel "SSE probe" diagnostic was developed and used to obtain the first-ever angular distributions of positive and negative SSE yields for an electrospray thruster. An optical emission spectroscopy study was conducted to show that glow discharges observed in electrospray thrusters during vacuum operation are a consequence of SSE; this observation is in direct contrast to common postulations that glows are intrinsic to electrospray operation. Two analytical models were developed to study SSE impact on thruster performance and lifetime. The first model was a one-dimensional heat and mass flux analysis of an ionic liquid ion source, which showed that SSE-induced Ohmic dissipation can significantly affect thruster performance. The second model, named the "Electrospray SSE Control-volume Analysis for Resolving Ground Operation of Thrusters" (ESCARGOT) invokes conservation of charge to derive a set of governing equations that describes the emission and transport of secondary species throughout an electrospray thruster and testing facility. The model relies on geometric factors obtained from numerical simulations, and experimentally-obtained SSE yields to correct for SSE-induced current measurement uncertainty in thruster performance and life testing. Therefore, the ESCARGOT model serves as an important link to determine accurate in-space thruster life and performance predictions based on terrestrial qualification testing. Overall, this work reveals the critical importance of SSE to electrospray thruster performance, life, facility effects, and space interactions; and provides both experimental and modeling techniques to assess their impact for a range of operating and test conditions.
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650 4 $a Applied physics. $3 3343996
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653 $a Electric propulsion
653 $a Electrospray propulsion
653 $a Facility effects
653 $a Ionic liquids
653 $a Secondary species emission
653 $a Surface impact effects
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690 $a 0215
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710 2 $a University of California, Los Angeles. $b Aerospace Engineering 0279. $3 2092189
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