{"title":"Synchronized Initiation of Two Cylindrical Rotating Detonation Engines","authors":"Rinpei Sakata, Masahiro Inada, Noboru Itouyama, Ken Matsuoka, Jiro Kasahara, Akira Kawasaki, Akiko Matsuo, Ikkoh Funaki","doi":"10.2514/1.b39459","DOIUrl":"https://doi.org/10.2514/1.b39459","url":null,"abstract":"Journal of Propulsion and Power, Ahead of Print. <br/>","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2024-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141501011","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
For several decades, researchers have successfully computed surface burnback to perform complex analyses and simulations related to the combustion of solid propellants. Many of these methods are heuristic or empirical, lacking a rigorous foundation, whereas others introduce numerical issues not related with the involved physics. This paper establishes a common theoretical and numerical core that bases the general study of burnback problems even in the case of designing nonconventional propellants. It starts with Piobert’s statement as a first principle, derives that the eikonal formulation holds for propellants with heterogeneous and anisotropic recession rates, and gives a general mathematical structure for both situations. Then, several configurations found by rocket designers are numerically solved in order to show the efficiency and the accuracy of the theory. The main conclusion is that a direct numerical integration of the eikonal equation using a time marching method is enough in terms of computational efficiency and accuracy to track the combustion surface of any anisotropic and heterogeneous solid propellant.
{"title":"General Burnback Analysis for Anisotropic and Heterogeneous Solid Propellants","authors":"J. Tizón, Efrén M. Benavides","doi":"10.2514/1.b39444","DOIUrl":"https://doi.org/10.2514/1.b39444","url":null,"abstract":"For several decades, researchers have successfully computed surface burnback to perform complex analyses and simulations related to the combustion of solid propellants. Many of these methods are heuristic or empirical, lacking a rigorous foundation, whereas others introduce numerical issues not related with the involved physics. This paper establishes a common theoretical and numerical core that bases the general study of burnback problems even in the case of designing nonconventional propellants. It starts with Piobert’s statement as a first principle, derives that the eikonal formulation holds for propellants with heterogeneous and anisotropic recession rates, and gives a general mathematical structure for both situations. Then, several configurations found by rocket designers are numerically solved in order to show the efficiency and the accuracy of the theory. The main conclusion is that a direct numerical integration of the eikonal equation using a time marching method is enough in terms of computational efficiency and accuracy to track the combustion surface of any anisotropic and heterogeneous solid propellant.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2024-06-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141383388","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Christopher Glaser, Jouke Hijlkema, Jean-Yves Lestrade, Jérôme Anthoine
Journal of Propulsion and Power, Ahead of Print.
推进与动力杂志》，印刷版前。
{"title":"Enhancing Hybrid Rocket Engine Regression Rates: The Stepped Helix Design","authors":"Christopher Glaser, Jouke Hijlkema, Jean-Yves Lestrade, Jérôme Anthoine","doi":"10.2514/1.b39258","DOIUrl":"https://doi.org/10.2514/1.b39258","url":null,"abstract":"Journal of Propulsion and Power, Ahead of Print. <br/>","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2024-06-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141252841","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Christopher T. Lyne, Miron F. Liu, Joshua L. Rovey
Journal of Propulsion and Power, Ahead of Print.
推进与动力杂志》，印刷版前。
{"title":"Tandem Energy-Analyzer/Mass-Spectrometer Measurements of an Ionic Liquid Ion Source","authors":"Christopher T. Lyne, Miron F. Liu, Joshua L. Rovey","doi":"10.2514/1.b39396","DOIUrl":"https://doi.org/10.2514/1.b39396","url":null,"abstract":"Journal of Propulsion and Power, Ahead of Print. <br/>","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2024-05-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141168248","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Kristyn B. Johnson May, Justin Weber, Don Ferguson, Andrew Nix, Todd G. Sidwell
Limit cycle oscillation (LCO) detonation wave behaviors are presented and analyzed for test times exceeding 20 s in a water-cooled rotating detonation engine (RDE). LCO detonation waves exhibit cyclic acceleration and deceleration, resulting in oscillating wave spacing at unique process conditions. In previous RDE studies, similar behaviors have been studied as microsecond-scale instabilities leading to ascending or descending modal transitions. In the current work, however, LCO waves are considered a persistent wave mode, occupying unique portions of the operational envelope adjacent to those of their equally spaced counterparts. These occurrences of LCO waves are repeatable, enduring behaviors. A method to generate shifted contour surfaces specifically intended to extract and analyze wave spacing variation through time, termed limit cycle oscillation visualization (LCOV) surfaces, is presented. LCOV surfaces transform data into the reference frame of a primary traveling wave and are used to analyze quasi-steady, short-timescale, and transitional LCO modes. Results are leveraged to understand the relationship between fill height, wave strength, local wave acceleration, and subsequent LCO wave spacing for individual wave sets. Quasi-steady LCO waves display wave spacing oscillations between equal spacing values associated with [Formula: see text] wave across runs exceeding 18 s.
{"title":"Limit Cycle Oscillating Detonation Wave Behavior Analysis Within a Rotating Detonation Engine","authors":"Kristyn B. Johnson May, Justin Weber, Don Ferguson, Andrew Nix, Todd G. Sidwell","doi":"10.2514/1.b39271","DOIUrl":"https://doi.org/10.2514/1.b39271","url":null,"abstract":"Limit cycle oscillation (LCO) detonation wave behaviors are presented and analyzed for test times exceeding 20 s in a water-cooled rotating detonation engine (RDE). LCO detonation waves exhibit cyclic acceleration and deceleration, resulting in oscillating wave spacing at unique process conditions. In previous RDE studies, similar behaviors have been studied as microsecond-scale instabilities leading to ascending or descending modal transitions. In the current work, however, LCO waves are considered a persistent wave mode, occupying unique portions of the operational envelope adjacent to those of their equally spaced counterparts. These occurrences of LCO waves are repeatable, enduring behaviors. A method to generate shifted contour surfaces specifically intended to extract and analyze wave spacing variation through time, termed limit cycle oscillation visualization (LCOV) surfaces, is presented. LCOV surfaces transform data into the reference frame of a primary traveling wave and are used to analyze quasi-steady, short-timescale, and transitional LCO modes. Results are leveraged to understand the relationship between fill height, wave strength, local wave acceleration, and subsequent LCO wave spacing for individual wave sets. Quasi-steady LCO waves display wave spacing oscillations between equal spacing values associated with [Formula: see text] wave across runs exceeding 18 s.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2024-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141114659","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
A multiscale approach to multi-emitter electrospray-ion source modeling has been developed to propagate emission site conditions into spatial domains viable for plume evolution simulations. This framework uses the particle-in-cell method to maintain a feasible computational complexity for consumer-grade hardware. Source models for individual emission sites are informed by an n-body single-emitter model. Molecular effects such as ion-cluster fragmentation are included. This model is used to predict array-level properties such as plume divergence angle, and to demonstrate the computational feasibility of modeling many emitters in parallel. This framework is used to quantify the relationship between array dimensions and space-charge- induced beam divergence. It is shown that including interparticle forces in plume expansion results in an increase in plume half angle by 8.1 deg for 80% and 9.8 deg for 90% of the emitter current for a commercial electrospray thruster. These data indicate that, at the array scale, space charge has a significant effect on plume evolution and must be considered in analysis of these systems.
{"title":"Propagating an Electrospray Emission Model to Array Scales Using Particle-in-Cell","authors":"Adler G. Smith, Elaine M. Petro","doi":"10.2514/1.b39400","DOIUrl":"https://doi.org/10.2514/1.b39400","url":null,"abstract":"A multiscale approach to multi-emitter electrospray-ion source modeling has been developed to propagate emission site conditions into spatial domains viable for plume evolution simulations. This framework uses the particle-in-cell method to maintain a feasible computational complexity for consumer-grade hardware. Source models for individual emission sites are informed by an n-body single-emitter model. Molecular effects such as ion-cluster fragmentation are included. This model is used to predict array-level properties such as plume divergence angle, and to demonstrate the computational feasibility of modeling many emitters in parallel. This framework is used to quantify the relationship between array dimensions and space-charge- induced beam divergence. It is shown that including interparticle forces in plume expansion results in an increase in plume half angle by 8.1 deg for 80% and 9.8 deg for 90% of the emitter current for a commercial electrospray thruster. These data indicate that, at the array scale, space charge has a significant effect on plume evolution and must be considered in analysis of these systems.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2024-05-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141118301","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Alex R. Keller, R. Mitchell Spearrin, Fabio A. Bendana
Journal of Propulsion and Power, Ahead of Print.
推进与动力杂志》，印刷版前。
{"title":"Shear Coaxial Methane–Oxygen Injector Mixing and Combustion Examined by Laser Absorption Tomography","authors":"Alex R. Keller, R. Mitchell Spearrin, Fabio A. Bendana","doi":"10.2514/1.b39463","DOIUrl":"https://doi.org/10.2514/1.b39463","url":null,"abstract":"Journal of Propulsion and Power, Ahead of Print. <br/>","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2024-05-13","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140929552","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Mengwen Qiao, Yixin Zhou, Guilin Liu, Zhongshan Deng, Lei Sheng, Lei Wang, Qian Wang, Jing Liu
Journal of Propulsion and Power, Ahead of Print.
推进与动力杂志》，印刷版前。
{"title":"Optimization and Testing of DC Electromagnetic Pump for Liquid Metal Space Use","authors":"Mengwen Qiao, Yixin Zhou, Guilin Liu, Zhongshan Deng, Lei Sheng, Lei Wang, Qian Wang, Jing Liu","doi":"10.2514/1.b39203","DOIUrl":"https://doi.org/10.2514/1.b39203","url":null,"abstract":"Journal of Propulsion and Power, Ahead of Print. <br/>","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2024-05-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140929557","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Leanne L. Su, Parker J. Roberts, Tate M. Gill, William J. Hurley, Thomas A. Marks, Christopher L. Sercel, Madison G. Allen, Collin B. Whittaker, Eric Viges, Benjamin A. Jorns
The performance of a magnetically shielded Hall thruster operating on xenon and krypton is characterized at discharge current densities up to 10 times greater than its nominal level. A thrust stand and far-field probe suite are employed to evaluate operation at 300 V discharge voltage and discharge currents from 15 to 125 A (xenon) and from 15 to 150 A (krypton). The thrust, specific impulse, and anode efficiency at the highest currents are found to be , , and respectively for xenon, and , , and for krypton. The thrust density at the highest conditions are shown to be six (xenon) and eight (krypton) times higher than the lowest current condition. A maximum in anode efficiency as a function of discharge current is observed for both gases. This is attributed to a trade between mass utilization, which increases to unity with current, and beam utilization, which gradually decreases with current. The dependence of these efficiency modes on current is discussed in the context of a series of first-principles scaling laws. The observation that efficiency only moderately decreases with current density is examined in the context of high-power electric propulsion development.
对使用氙和氪的磁屏蔽霍尔推进器在放电电流密度比额定值大 10 倍的情况下的性能进行了鉴定。在 300 V 放电电压和 15 至 125 A（氙）及 15 至 150 A（氪）放电电流条件下，使用推力台架和远场探针套件对运行情况进行了评估。在最高电流下，氙的推力、比冲和阳极效率分别为 1650±30 mN、2309±56 s 和 52.8±2.0%；氪的推力、比冲和阳极效率分别为 1839±18 mN、2567±48 s 和 55.0±1.6%。最高条件下的推力密度分别是最低电流条件下的 6 倍（氙）和 8 倍（氪）。根据放电电流的函数，两种气体的阳极效率都达到了最大值。这归因于质量利用率和束流利用率之间的权衡，质量利用率随电流的增加而增加，直至达到统一；束流利用率则随电流的增加而逐渐降低。这些效率模式对电流的依赖性在一系列第一原理缩放定律的背景下进行了讨论。在大功率电力推进发展的背景下，对效率仅随电流密度适度降低这一观察结果进行了研究。
{"title":"High-Current Density Performance of a Magnetically Shielded Hall Thruster","authors":"Leanne L. Su, Parker J. Roberts, Tate M. Gill, William J. Hurley, Thomas A. Marks, Christopher L. Sercel, Madison G. Allen, Collin B. Whittaker, Eric Viges, Benjamin A. Jorns","doi":"10.2514/1.b39324","DOIUrl":"https://doi.org/10.2514/1.b39324","url":null,"abstract":"<p>The performance of a magnetically shielded Hall thruster operating on xenon and krypton is characterized at discharge current densities up to 10 times greater than its nominal level. A thrust stand and far-field probe suite are employed to evaluate operation at 300 V discharge voltage and discharge currents from 15 to 125 A (xenon) and from 15 to 150 A (krypton). The thrust, specific impulse, and anode efficiency at the highest currents are found to be <span><math altimg=\"eq-00001.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mn>1650</mn><mo>±</mo><mn>30</mn><mtext> </mtext><mi>mN</mi></mrow></math></span><span></span>, <span><math altimg=\"eq-00002.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mn>2309</mn><mo>±</mo><mn>56</mn><mtext> </mtext><mi mathvariant=\"normal\">s</mi></mrow></math></span><span></span>, and <span><math altimg=\"eq-00003.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mn>52.8</mn><mo>±</mo><mn>2.0</mn><mo>%</mo></mrow></math></span><span></span> respectively for xenon, and <span><math altimg=\"eq-00004.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mn>1839</mn><mo>±</mo><mn>18</mn><mtext> </mtext><mi>mN</mi></mrow></math></span><span></span>, <span><math altimg=\"eq-00005.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mn>2567</mn><mo>±</mo><mn>48</mn><mtext> </mtext><mi mathvariant=\"normal\">s</mi></mrow></math></span><span></span>, and <span><math altimg=\"eq-00006.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mn>55.0</mn><mo>±</mo><mn>1.6</mn><mo>%</mo></mrow></math></span><span></span> for krypton. The thrust density at the highest conditions are shown to be six (xenon) and eight (krypton) times higher than the lowest current condition. A maximum in anode efficiency as a function of discharge current is observed for both gases. This is attributed to a trade between mass utilization, which increases to unity with current, and beam utilization, which gradually decreases with current. The dependence of these efficiency modes on current is discussed in the context of a series of first-principles scaling laws. The observation that efficiency only moderately decreases with current density is examined in the context of high-power electric propulsion development.</p>","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2024-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140833912","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Nathan D. Ballintyn, Alexis J. Harroun, Stephen D. Heister
Journal of Propulsion and Power, Ahead of Print.
推进与动力杂志》，印刷版前。
{"title":"Current Status of Liquid-Bipropellant Detonation-Based Propulsion Devices","authors":"Nathan D. Ballintyn, Alexis J. Harroun, Stephen D. Heister","doi":"10.2514/1.b39360","DOIUrl":"https://doi.org/10.2514/1.b39360","url":null,"abstract":"Journal of Propulsion and Power, Ahead of Print. <br/>","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":1.9,"publicationDate":"2024-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140833971","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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