Thermal Analysis and Testing of Different Designs of LaB<sub>6</sub> Hollow Cathodes to Be Used in Electric Propulsion Applications

<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>L</mi><mi>a</mi><msub><mi>B</mi><mn>6</mn></msub></mrow></semantics></math>...

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Main Authors: Ugur Kokal, Nazli Turan, Murat Celik
Format: Article
Language:English
Published: MDPI AG 2021-08-01
Series:Aerospace
Subjects:
Online Access:https://www.mdpi.com/2226-4310/8/8/215
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spelling doaj-d2e1e104d56745bfa7731b094e85742d2021-08-26T13:24:50ZengMDPI AGAerospace2226-43102021-08-01821521510.3390/aerospace8080215Thermal Analysis and Testing of Different Designs of LaB<sub>6</sub> Hollow Cathodes to Be Used in Electric Propulsion ApplicationsUgur Kokal0Nazli Turan1Murat Celik2Department of Mechanical Engineering, Bogazici University, Istanbul 34342, TurkeyDepartment of Mechanical Engineering, Bogazici University, Istanbul 34342, TurkeyDepartment of Mechanical Engineering, Bogazici University, Istanbul 34342, Turkey<inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>L</mi><mi>a</mi><msub><mi>B</mi><mn>6</mn></msub></mrow></semantics></math></inline-formula> emitters are commonly used in hollow cathodes that are utilized in electric space propulsion systems. In order to obtain necessary surface current emission densities of 1–10 A/cm<sup>2</sup> for cathode operations, <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>L</mi><mi>a</mi><msub><mi>B</mi><mn>6</mn></msub></mrow></semantics></math></inline-formula> emitters require temperatures above 1500 °C. Hence, the design for <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>L</mi><mi>a</mi><msub><mi>B</mi><mn>6</mn></msub></mrow></semantics></math></inline-formula> cathodes presents thermal and mechanical challenges. In this paper, several design iterations for <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>L</mi><mi>a</mi><msub><mi>B</mi><mn>6</mn></msub></mrow></semantics></math></inline-formula> hollow cathodes are presented and thermal analyses are conducted for each design. Temperature and heat flux distributions that are obtained from thermal analyses are investigated. The designs are evaluated according to the required heat input to the emitter, and the radiative and conductive heat loss mechanisms. In addition to the thermal analyses, experimental tests are conducted for different cathode designs and, based on these tests, various modes of failure are determined. Revising the cathode design and the material selection iteratively to eliminate the encountered failure mechanisms, a novel cathode design is achieved. Experimental tests of this novel cathode are conducted and current-voltage characteristics are presented for different mass flow rates and for discharge currents between 0.5 and 12 A. Tests and analysis results show that the selection of materials and design are crucial for a sturdy and long lifetime cathode.https://www.mdpi.com/2226-4310/8/8/215electric propulsionhollow cathodeLaB6 emitterthermal analysis
collection DOAJ
language English
format Article
sources DOAJ
author Ugur Kokal
Nazli Turan
Murat Celik
spellingShingle Ugur Kokal
Nazli Turan
Murat Celik
Thermal Analysis and Testing of Different Designs of LaB<sub>6</sub> Hollow Cathodes to Be Used in Electric Propulsion Applications
Aerospace
electric propulsion
hollow cathode
LaB6 emitter
thermal analysis
author_facet Ugur Kokal
Nazli Turan
Murat Celik
author_sort Ugur Kokal
title Thermal Analysis and Testing of Different Designs of LaB<sub>6</sub> Hollow Cathodes to Be Used in Electric Propulsion Applications
title_short Thermal Analysis and Testing of Different Designs of LaB<sub>6</sub> Hollow Cathodes to Be Used in Electric Propulsion Applications
title_full Thermal Analysis and Testing of Different Designs of LaB<sub>6</sub> Hollow Cathodes to Be Used in Electric Propulsion Applications
title_fullStr Thermal Analysis and Testing of Different Designs of LaB<sub>6</sub> Hollow Cathodes to Be Used in Electric Propulsion Applications
title_full_unstemmed Thermal Analysis and Testing of Different Designs of LaB<sub>6</sub> Hollow Cathodes to Be Used in Electric Propulsion Applications
title_sort thermal analysis and testing of different designs of lab<sub>6</sub> hollow cathodes to be used in electric propulsion applications
publisher MDPI AG
series Aerospace
issn 2226-4310
publishDate 2021-08-01
description <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>L</mi><mi>a</mi><msub><mi>B</mi><mn>6</mn></msub></mrow></semantics></math></inline-formula> emitters are commonly used in hollow cathodes that are utilized in electric space propulsion systems. In order to obtain necessary surface current emission densities of 1–10 A/cm<sup>2</sup> for cathode operations, <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>L</mi><mi>a</mi><msub><mi>B</mi><mn>6</mn></msub></mrow></semantics></math></inline-formula> emitters require temperatures above 1500 °C. Hence, the design for <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>L</mi><mi>a</mi><msub><mi>B</mi><mn>6</mn></msub></mrow></semantics></math></inline-formula> cathodes presents thermal and mechanical challenges. In this paper, several design iterations for <inline-formula><math xmlns="http://www.w3.org/1998/Math/MathML" display="inline"><semantics><mrow><mi>L</mi><mi>a</mi><msub><mi>B</mi><mn>6</mn></msub></mrow></semantics></math></inline-formula> hollow cathodes are presented and thermal analyses are conducted for each design. Temperature and heat flux distributions that are obtained from thermal analyses are investigated. The designs are evaluated according to the required heat input to the emitter, and the radiative and conductive heat loss mechanisms. In addition to the thermal analyses, experimental tests are conducted for different cathode designs and, based on these tests, various modes of failure are determined. Revising the cathode design and the material selection iteratively to eliminate the encountered failure mechanisms, a novel cathode design is achieved. Experimental tests of this novel cathode are conducted and current-voltage characteristics are presented for different mass flow rates and for discharge currents between 0.5 and 12 A. Tests and analysis results show that the selection of materials and design are crucial for a sturdy and long lifetime cathode.
topic electric propulsion
hollow cathode
LaB6 emitter
thermal analysis
url https://www.mdpi.com/2226-4310/8/8/215
work_keys_str_mv AT ugurkokal thermalanalysisandtestingofdifferentdesignsoflabsub6subhollowcathodestobeusedinelectricpropulsionapplications
AT nazlituran thermalanalysisandtestingofdifferentdesignsoflabsub6subhollowcathodestobeusedinelectricpropulsionapplications
AT muratcelik thermalanalysisandtestingofdifferentdesignsoflabsub6subhollowcathodestobeusedinelectricpropulsionapplications
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