Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)最新文献
S. Bagy, B. Mohammadi, M. Meheut, M. Lallia, P. Coat
HAL is a multi-disciplinary open access archive for the deposit and dissemination of scientific research documents, whether they are published or not. The documents may come from teaching and research institutions in France or abroad, or from public or private research centers. L’archive ouverte pluridisciplinaire HAL, est destinée au dépôt et à la diffusion de documents scientifiques de niveau recherche, publiés ou non, émanant des établissements d’enseignement et de recherche français ou étrangers, des laboratoires publics ou privés. Aerodynamic shape optimization of aircraft engine nozzles based on Computer-Aided Design Simon Bagy, Mathieu Lallia, Pascal Coat, Bijan Mohammadi, Michaël Méheut
它是一个多学科的开放获取档案，用于科学研究文件的存储和传播，无论它们是否出版。这些文件可能来自法国或国外的教学和研究机构，也可能来自公共或私人研究中心。HAL开放多学科档案旨在存放和传播来自法国或外国教育和研究机构、公共或私人实验室的已发表或未发表的研究级科学文件。Simon Bagy, Mathieu Lallia, Pascal Coat, Bijan Mohammadi, michael meheut
{"title":"Aerodynamic shape optimization of aircraft engine nozzles based on Computer-Aided Design","authors":"S. Bagy, B. Mohammadi, M. Meheut, M. Lallia, P. Coat","doi":"10.2514/6.2020-2247","DOIUrl":"https://doi.org/10.2514/6.2020-2247","url":null,"abstract":"HAL is a multi-disciplinary open access archive for the deposit and dissemination of scientific research documents, whether they are published or not. The documents may come from teaching and research institutions in France or abroad, or from public or private research centers. L’archive ouverte pluridisciplinaire HAL, est destinée au dépôt et à la diffusion de documents scientifiques de niveau recherche, publiés ou non, émanant des établissements d’enseignement et de recherche français ou étrangers, des laboratoires publics ou privés. Aerodynamic shape optimization of aircraft engine nozzles based on Computer-Aided Design Simon Bagy, Mathieu Lallia, Pascal Coat, Bijan Mohammadi, Michaël Méheut","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"34 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78214777","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Ana Guerra-Langan, S. Araujo-Estrada, Arthur G. Richards, S. Windsor
Recent research suggests that the information obtained from arrays of sensors distributed on the wing of a fixed-wing small unmanned aerial vehicle (UAV) can provide information not available to conventional sensor suites. These arrays of sensors are capable of sensing the flow around the aircraft and it has been indicated that they could be a potential tool to improve flight control and overall flight performance. However, more work needs to be carried out to fully exploit the potential of these sensors for flight control. This work presents a 3 degrees-of-freedom longitudinal flight dynamics and control simulation model of a small fixed-wing UAV. Experimental readings of an array of pressure and strain sensors distributed across the wing were integrated in the model. This study investigated the feasibility of using machine learning to control airspeed of the UAV using the readings from the sensing array, and looked into the sensor layout and its effect on the performance of the controller. It was found that an artificial neural network was able to learn to mimic a conventional airspeed controller using only distributed sensor signals, but showed better performance for controlling changes in airspeed for a constant altitude than holding airspeed during changes in altitude. The neural network could control airspeed using either pressure or strain sensor information, but having both improved robustness to increased levels of turbulence. Results showed that some strain sensors and many pressure sensors signals were not necessary to achieve good controller performance, but that the pressure sensors near the leading edge of the wing were required. Future work will focus on replacing other elements of the flight control system with machine learning elements and investigate the use of reinforcement learning in place of supervised learning.
{"title":"Simulation of a Machine Learning Based Controller for a Fixed-Wing UAV with Distributed Sensors","authors":"Ana Guerra-Langan, S. Araujo-Estrada, Arthur G. Richards, S. Windsor","doi":"10.2514/6.2020-1239","DOIUrl":"https://doi.org/10.2514/6.2020-1239","url":null,"abstract":"Recent research suggests that the information obtained from arrays of sensors distributed on the wing of a fixed-wing small unmanned aerial vehicle (UAV) can provide information not available to conventional sensor suites. These arrays of sensors are capable of sensing the flow around the aircraft and it has been indicated that they could be a potential tool to improve flight control and overall flight performance. However, more work needs to be carried out to fully exploit the potential of these sensors for flight control. This work presents a 3 degrees-of-freedom longitudinal flight dynamics and control simulation model of a small fixed-wing UAV. Experimental readings of an array of pressure and strain sensors distributed across the wing were integrated in the model. This study investigated the feasibility of using machine learning to control airspeed of the UAV using the readings from the sensing array, and looked into the sensor layout and its effect on the performance of the controller. It was found that an artificial neural network was able to learn to mimic a conventional airspeed controller using only distributed sensor signals, but showed better performance for controlling changes in airspeed for a constant altitude than holding airspeed during changes in altitude. The neural network could control airspeed using either pressure or strain sensor information, but having both improved robustness to increased levels of turbulence. Results showed that some strain sensors and many pressure sensors signals were not necessary to achieve good controller performance, but that the pressure sensors near the leading edge of the wing were required. Future work will focus on replacing other elements of the flight control system with machine learning elements and investigate the use of reinforcement learning in place of supervised learning.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"30 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78242614","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
S. K. Jasra, G. Valentino, A. Muscat, D. Zammit-Mangion, R. Camilleri
This paper adopts an unsupervised learning technique, Principal Component Analysis (PCA) to analyze flight data. While the flight parameters for a stable approach have been established for a while, the paper reevaluates these flight parameters using PCA for a set of airports across the United States of America. Some flight parameters were found to be more sensitive to some airports. The parameters have been cross-checked with experts in the industry to better interpret their significance.
{"title":"Evaluation of Flight Parameters During Approach and Landing Phases by Applying Principal Component Analysis","authors":"S. K. Jasra, G. Valentino, A. Muscat, D. Zammit-Mangion, R. Camilleri","doi":"10.2514/6.2020-0674","DOIUrl":"https://doi.org/10.2514/6.2020-0674","url":null,"abstract":"This paper adopts an unsupervised learning technique, Principal Component Analysis (PCA) to analyze flight data. While the flight parameters for a stable approach have been established for a while, the paper reevaluates these flight parameters using PCA for a set of airports across the United States of America. Some flight parameters were found to be more sensitive to some airports. The parameters have been cross-checked with experts in the industry to better interpret their significance.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"93 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85552948","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Luis F. Silva, Francisco A. Yapor Genao, E. Pineda, P. Gustafson
The effect of material porosity on final part distortion and residual stresses in a selective laser sintering manufacturing simulation is presented here. A time-dependent thermomechanical model is used with the open-source FEA software CalculiX. Effective homogenized material properties for Inconel 625 are precomputed using NASA’s Micromechanics Analysis Code with Generalized Method of Cells (MAC/GMC). The evolving porosity of the material is estimated with each pass of the laser beam during simulation runtime. A comparison with a homogenous model and the evolving model shows that the evolving porous model predicts larger distortions with greater residual stresses.
{"title":"Evolving Material Porosity on an Additive Manufacturing Simulation with the Generalized Method of Cells","authors":"Luis F. Silva, Francisco A. Yapor Genao, E. Pineda, P. Gustafson","doi":"10.2514/6.2020-1124","DOIUrl":"https://doi.org/10.2514/6.2020-1124","url":null,"abstract":"The effect of material porosity on final part distortion and residual stresses in a selective laser sintering manufacturing simulation is presented here. A time-dependent thermomechanical model is used with the open-source FEA software CalculiX. Effective homogenized material properties for Inconel 625 are precomputed using NASA’s Micromechanics Analysis Code with Generalized Method of Cells (MAC/GMC). The evolving porosity of the material is estimated with each pass of the laser beam during simulation runtime. A comparison with a homogenous model and the evolving model shows that the evolving porous model predicts larger distortions with greater residual stresses.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"72 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"84148093","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
T. Zwieten, Jacob Brodnick, S. Reese, M. Ruth, B. Marsell, R. Parks
Propellant tank slosh damping models for launch vehicle ascent analysis typically employ linear models for bare-wall damping, or assume a single, low-amplitude wave height for baffled configurations. A higher fidelity damping model would incorporate nonlinear effects to increase damping as slosh wave amplitude increases. This paper provides an overview of a technical assessment performed by the NASA Engineering and Safety Center (NESC) to evaluate lateral slosh damping as a function of lateral force (or wave) amplitude for multiple tank configurations. The increased fidelity of nonlinear slosh damping models, if leveraged, has the potential to reduce over-conservatism associated with the use of linear slosh damping models. This can provide design flexibility to enhance launch vehicle flight control performance, reduce baffle design requirements and/or increase robustness in targeted areas such as control-structure interaction during ascent. provide context for use of CFD full-scale propellant tank subscale tank test are
{"title":"Nonlinear Slosh Damping Testing and Analysis for Launch Vehicle Propellant Tanks","authors":"T. Zwieten, Jacob Brodnick, S. Reese, M. Ruth, B. Marsell, R. Parks","doi":"10.2514/6.2020-2050","DOIUrl":"https://doi.org/10.2514/6.2020-2050","url":null,"abstract":"Propellant tank slosh damping models for launch vehicle ascent analysis typically employ linear models for bare-wall damping, or assume a single, low-amplitude wave height for baffled configurations. A higher fidelity damping model would incorporate nonlinear effects to increase damping as slosh wave amplitude increases. This paper provides an overview of a technical assessment performed by the NASA Engineering and Safety Center (NESC) to evaluate lateral slosh damping as a function of lateral force (or wave) amplitude for multiple tank configurations. The increased fidelity of nonlinear slosh damping models, if leveraged, has the potential to reduce over-conservatism associated with the use of linear slosh damping models. This can provide design flexibility to enhance launch vehicle flight control performance, reduce baffle design requirements and/or increase robustness in targeted areas such as control-structure interaction during ascent. provide context for use of CFD full-scale propellant tank subscale tank test are","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"8 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81767566","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Troy A. Abraham, D. Hunsaker, Jonathan M. Weaver-Rosen, R. Malak
{"title":"Identifying Optimal Equivalent Area Changes to Reduce Sonic Boom Loudness","authors":"Troy A. Abraham, D. Hunsaker, Jonathan M. Weaver-Rosen, R. Malak","doi":"10.2514/6.2020-0790","DOIUrl":"https://doi.org/10.2514/6.2020-0790","url":null,"abstract":"","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"77 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"78650049","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Although receptivity plays a key role in the transition of hypersonic flows, most prior computational receptivity studies have neglected to study broadband frequency disturbance spectra. This work uses perfect gas linear stability theory (LST) and direct numerical simulation (DNS) to study the receptivity of flow over a 9.525 mm nose radius, 7 deg half-angle straight cone at Mach 10 using finite spherical and planar pulses to approximate disturbances with broadband frequency spectra. Freestream fast acoustic, slow acoustic, temperature, and vorticity pulses of both geometrieswere studied to investigate awide range of forcing conditions.UnsteadyDNSpredicts secondmodegrowth and agrees well with LST. DNS and LST data are used to extract second mode receptivity coefficients and phase spectra. For the finite pulses the strongest to weakest responses are for the fast acoustic, temperature, slow acoustic, and vorticity pulses, respectively. The planar disturbances show the strongest response for the slow acoustic, temperature, vorticity, and fast acoustic pulses in that order. Fast Fourier transform results show significant variation in the spectral disturbance response between disturbance types and geometries, and the planar fast acoustic pulse in particular is shown to much more readily excite modal disturbances other than the primary second mode.
{"title":"Hypersonic Boundary Layer Receptivity over a Blunt Cone to Freestream Pulse Disturbances","authors":"Simon He, X. Zhong","doi":"10.2514/6.2020-2057","DOIUrl":"https://doi.org/10.2514/6.2020-2057","url":null,"abstract":"Although receptivity plays a key role in the transition of hypersonic flows, most prior computational receptivity studies have neglected to study broadband frequency disturbance spectra. This work uses perfect gas linear stability theory (LST) and direct numerical simulation (DNS) to study the receptivity of flow over a 9.525 mm nose radius, 7 deg half-angle straight cone at Mach 10 using finite spherical and planar pulses to approximate disturbances with broadband frequency spectra. Freestream fast acoustic, slow acoustic, temperature, and vorticity pulses of both geometrieswere studied to investigate awide range of forcing conditions.UnsteadyDNSpredicts secondmodegrowth and agrees well with LST. DNS and LST data are used to extract second mode receptivity coefficients and phase spectra. For the finite pulses the strongest to weakest responses are for the fast acoustic, temperature, slow acoustic, and vorticity pulses, respectively. The planar disturbances show the strongest response for the slow acoustic, temperature, vorticity, and fast acoustic pulses in that order. Fast Fourier transform results show significant variation in the spectral disturbance response between disturbance types and geometries, and the planar fast acoustic pulse in particular is shown to much more readily excite modal disturbances other than the primary second mode.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"2015 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"87817623","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Marit E. Knapp, Christina M. Ivler, J. Horn, Eric N. Johnson, D. Bridges, Mark J. S. Lopez, M. Tischler, Joseph Wagster, Kenny Cheung
A piloted simulation study was conducted to evaluate damage tolerant control (DTC) law concepts. The simulated aircraft is a fly-by-wire compound utility helicopter based on the X-49A. The aircraft features auxiliary thrust through a vectored thrust ducted propeller and auxiliary lift through a wing. The configuration includes a number of redundant control surfaces, including flaperons and elevators that help enable DTC. This paper covers the design of the baseline inner-loop control laws, which were optimized to meet Level 1 requirements for a comprehensive set of stability, handling qualities and performance specifications. Methodology and development of the control allocation methods for DTC is presented. The fixed-base piloted simulation experiment qualitatively and quantitatively evaluated the baseline control laws with various control allocation methods. Handling qualities ratings were collected using a series of maneuvers, including pitch and roll capture and tracking tasks. Survivability ratings, quantitative performance metrics, and pilot comments were collected for multiple damage scenarios in which the pilot attempted to safely land the aircraft following damage that severely limited control in one or more axes. Handling qualities ratings were also collected for the tracking tasks in the presence of damage. The paper is concluded with an overall evaluation and comparison of the damage tolerant methods.
{"title":"Development and Simulation of Damage Tolerant Control Laws for a Compound Helicopter","authors":"Marit E. Knapp, Christina M. Ivler, J. Horn, Eric N. Johnson, D. Bridges, Mark J. S. Lopez, M. Tischler, Joseph Wagster, Kenny Cheung","doi":"10.2514/6.2020-1831","DOIUrl":"https://doi.org/10.2514/6.2020-1831","url":null,"abstract":"A piloted simulation study was conducted to evaluate damage tolerant control (DTC) law concepts. The simulated aircraft is a fly-by-wire compound utility helicopter based on the X-49A. The aircraft features auxiliary thrust through a vectored thrust ducted propeller and auxiliary lift through a wing. The configuration includes a number of redundant control surfaces, including flaperons and elevators that help enable DTC. This paper covers the design of the baseline inner-loop control laws, which were optimized to meet Level 1 requirements for a comprehensive set of stability, handling qualities and performance specifications. Methodology and development of the control allocation methods for DTC is presented. The fixed-base piloted simulation experiment qualitatively and quantitatively evaluated the baseline control laws with various control allocation methods. Handling qualities ratings were collected using a series of maneuvers, including pitch and roll capture and tracking tasks. Survivability ratings, quantitative performance metrics, and pilot comments were collected for multiple damage scenarios in which the pilot attempted to safely land the aircraft following damage that severely limited control in one or more axes. Handling qualities ratings were also collected for the tracking tasks in the presence of damage. The paper is concluded with an overall evaluation and comparison of the damage tolerant methods.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"51 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88421464","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
K. Lynch, B. Lance, G. Lee, J. Naughton, N. Miller, M. Barone, S. Beresh, R. Spillers, M. Soehnel
{"title":"A CFD Validation Challenge for Transonic, Shock-Induced Separated Flow: Experimental Characterization","authors":"K. Lynch, B. Lance, G. Lee, J. Naughton, N. Miller, M. Barone, S. Beresh, R. Spillers, M. Soehnel","doi":"10.2514/6.2020-1309","DOIUrl":"https://doi.org/10.2514/6.2020-1309","url":null,"abstract":"","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"299 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86272331","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
M. Haw, J. B. Meurisse, S. Visser, Sergio Fraile Izquierdo, J. Schulz, N. Mansour
This paper covers the design and first measurements of non-perturbative, external inductive magnetic diagnostics for arcjet constrictors which can measure the motion of the arc current-channel. These measurements of arc motion are motivated by previous simulations using the ARC Heater Simulator (ARCHeS), which predicted unsteady arc motion due to the magnetic kink instability. Measurements of the kink instability are relevant to characterizing motion of the enthalpy profile of the arcjet, the arcjet operational stability, and electrode damage due to associated arc detachment events. These first measurements indicate ± 4 mm oscillations at 0.5-2 kHz of the current profile.
{"title":"Preliminary Measurements of the Motion of Arcjet Current Channel Using Inductive Magnetic Probes","authors":"M. Haw, J. B. Meurisse, S. Visser, Sergio Fraile Izquierdo, J. Schulz, N. Mansour","doi":"10.2514/6.2020-0919","DOIUrl":"https://doi.org/10.2514/6.2020-0919","url":null,"abstract":"This paper covers the design and first measurements of non-perturbative, external inductive magnetic diagnostics for arcjet constrictors which can measure the motion of the arc current-channel. These measurements of arc motion are motivated by previous simulations using the ARC Heater Simulator (ARCHeS), which predicted unsteady arc motion due to the magnetic kink instability. Measurements of the kink instability are relevant to characterizing motion of the enthalpy profile of the arcjet, the arcjet operational stability, and electrode damage due to associated arc detachment events. These first measurements indicate ± 4 mm oscillations at 0.5-2 kHz of the current profile.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"6 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86111346","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)
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