{"title":"Real-time power flow analysis and management for a long-endurance solar UAV during continuous flight","authors":"Nourddine Ghelem, Djamel Boudana, Ouahid Bouchhida","doi":"10.1007/s13272-023-00684-9","DOIUrl":"https://doi.org/10.1007/s13272-023-00684-9","url":null,"abstract":"","PeriodicalId":38083,"journal":{"name":"CEAS Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134975096","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}
Pub Date : 2023-10-05DOI: 10.1007/s13272-023-00683-w
Yassine Ghanjaoui, Mara Fuchs, Jörn Biedermann, Björn Nagel
Abstract The aviation industry is currently facing major challenges due to environmental and socio-economic trends toward sustainable and digitalized aviation. Revolutionary, more powerful and efficient technologies must be rapidly integrated into aircraft, while aircraft manufacturers must demonstrate the required safety. To support the implementation of new concepts, the DLR Institute of System Architectures in Aeronautics is researching methods for end-to-end digitalization from the preliminary design phase to assembly and production. In this context, Model-Based Systems Engineering (MBSE) and Multidisciplinary Design Optimization are important approaches for the development of complex systems. This paper presents a method for the end-to-end use of digital models for multidisciplinary optimization of system architectures. The Systems Modeling Language (SysML) is used to represent the system architecture. The focus is on the cabin and cabin systems, since they are highly coupled to other aircraft systems and have dynamic, customer-specific configuration requirements. The system architecture in SysML is instantiated and configured by the interface to the aircraft fuselage and cabin design parameter sets in the Common Parametric Configuration Schema. The subsequent coupling of the generated system architecture model with the cabin system design model developed in Matlab allows a multidisciplinary optimization of the system properties. A sensitivity analysis is performed using the Passenger Service Unit as an example. The effects of different cabin configurations on the system architecture are investigated and interdisciplinary synergies are identified and analyzed. The results of this analysis are discussed in this paper.
{"title":"Model-based design and multidisciplinary optimization of complex system architectures in the aircraft cabin","authors":"Yassine Ghanjaoui, Mara Fuchs, Jörn Biedermann, Björn Nagel","doi":"10.1007/s13272-023-00683-w","DOIUrl":"https://doi.org/10.1007/s13272-023-00683-w","url":null,"abstract":"Abstract The aviation industry is currently facing major challenges due to environmental and socio-economic trends toward sustainable and digitalized aviation. Revolutionary, more powerful and efficient technologies must be rapidly integrated into aircraft, while aircraft manufacturers must demonstrate the required safety. To support the implementation of new concepts, the DLR Institute of System Architectures in Aeronautics is researching methods for end-to-end digitalization from the preliminary design phase to assembly and production. In this context, Model-Based Systems Engineering (MBSE) and Multidisciplinary Design Optimization are important approaches for the development of complex systems. This paper presents a method for the end-to-end use of digital models for multidisciplinary optimization of system architectures. The Systems Modeling Language (SysML) is used to represent the system architecture. The focus is on the cabin and cabin systems, since they are highly coupled to other aircraft systems and have dynamic, customer-specific configuration requirements. The system architecture in SysML is instantiated and configured by the interface to the aircraft fuselage and cabin design parameter sets in the Common Parametric Configuration Schema. The subsequent coupling of the generated system architecture model with the cabin system design model developed in Matlab allows a multidisciplinary optimization of the system properties. A sensitivity analysis is performed using the Passenger Service Unit as an example. The effects of different cabin configurations on the system architecture are investigated and interdisciplinary synergies are identified and analyzed. The results of this analysis are discussed in this paper.","PeriodicalId":38083,"journal":{"name":"CEAS Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134975271","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}
Pub Date : 2023-10-01DOI: 10.1007/s13272-023-00697-4
Nicolai Neumann, Dieter Peitsch
{"title":"Holistic performance evaluation of a turbofan featuring pressure gain combustion for a short-range mission","authors":"Nicolai Neumann, Dieter Peitsch","doi":"10.1007/s13272-023-00697-4","DOIUrl":"https://doi.org/10.1007/s13272-023-00697-4","url":null,"abstract":"","PeriodicalId":38083,"journal":{"name":"CEAS Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139328304","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}
Pub Date : 2023-10-01DOI: 10.1007/s13272-023-00693-8
Maria Stolz, A. Papenfuss, Georgia Cesar de Albuquerque Richers, Anna Bahnmüller, Azeem Muhammad Syed, Andreas Gerndt, Martin Fischer, Jan Wegener, Teemu Joonas Lieb, Marcus Biella
{"title":"A mixed-method approach to investigate the public acceptance of drones","authors":"Maria Stolz, A. Papenfuss, Georgia Cesar de Albuquerque Richers, Anna Bahnmüller, Azeem Muhammad Syed, Andreas Gerndt, Martin Fischer, Jan Wegener, Teemu Joonas Lieb, Marcus Biella","doi":"10.1007/s13272-023-00693-8","DOIUrl":"https://doi.org/10.1007/s13272-023-00693-8","url":null,"abstract":"","PeriodicalId":38083,"journal":{"name":"CEAS Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-10-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139329298","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}
Pub Date : 2023-09-25DOI: 10.1007/s13272-023-00682-x
Robert Kowalski, Patrick Juchmann
Abstract Electro-mechanical flight control actuators have become a viable option as a replacement for conventional hydraulic actuators in future more electric aircraft. A rotor angle measurement is generally required for field-oriented control of the electrical machine and usually obtained from a safety-critical resolver. It contributes, however, to a rising local hardware complexity with a negative impact on space allocation, weight, motor inertia, reliability, and cost. This paper investigates sensorless control strategies that might substitute the resolver with an accurate estimate value. A hybrid observer is implemented that allows position control without an angle sensor at all speeds. In the high speed domain, the extended electromotive force of the permanent magnet synchronous machine is used for angle estimation. In the low speed domain, including standstill, anisotropy properties of the motor are exploited by applying the alternating injection method. The performance of the control algorithm is evaluated on an aileron actuator test rig for a large civil aircraft.
{"title":"Sensorless motor control for electro-mechanical flight control actuators","authors":"Robert Kowalski, Patrick Juchmann","doi":"10.1007/s13272-023-00682-x","DOIUrl":"https://doi.org/10.1007/s13272-023-00682-x","url":null,"abstract":"Abstract Electro-mechanical flight control actuators have become a viable option as a replacement for conventional hydraulic actuators in future more electric aircraft. A rotor angle measurement is generally required for field-oriented control of the electrical machine and usually obtained from a safety-critical resolver. It contributes, however, to a rising local hardware complexity with a negative impact on space allocation, weight, motor inertia, reliability, and cost. This paper investigates sensorless control strategies that might substitute the resolver with an accurate estimate value. A hybrid observer is implemented that allows position control without an angle sensor at all speeds. In the high speed domain, the extended electromotive force of the permanent magnet synchronous machine is used for angle estimation. In the low speed domain, including standstill, anisotropy properties of the motor are exploited by applying the alternating injection method. The performance of the control algorithm is evaluated on an aileron actuator test rig for a large civil aircraft.","PeriodicalId":38083,"journal":{"name":"CEAS Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-09-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135815414","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}
Pub Date : 2023-09-20DOI: 10.1007/s13272-023-00679-6
Sébastien Guérin, Damiano Tormen
Abstract The objective of this work is to better understand the acoustic interferences created by distributed propulsion engines based on an approach that combines RANS simulation results for the aerodynamic prediction and analytical models to calculate acoustics. A multi-propeller configuration without wing is considered for this investigation. The propeller geometry and the operating conditions are realistic for a regional transport airplane. In the first part of the paper, the results obtained by two different and independent prediction methods are compared. One method is well-established and serves as validation for the second, low-order method, which is better suited for design-to-noise applications since it requires less details as input and is computationally faster by several orders of magnitude. The good agreement between both methods, obtained for a single propeller as well as for the distributed propeller configuration, is exploited in the second part of the paper to investigate the role of acoustic interferences. Taking acoustic interferences into account drastically affects the directivity of the tonal emission. Compared to the results obtained by considering the propellers as if they were uncorrelated, the far-field sound pressure levels can be significantly lower at the radiation nodes or amplified up to the theoretical limit of 9 dB calculated for eight propellers. The directivity patterns depend on the relative initial angular positions of the propellers. When these positions are randomly varied according to the uniform probability density distribution model, the mean result (expectation) is the same as if the propellers were considered as uncorrelated. Finally, the results show that the probability that the acoustic level is lower than the mean value is higher than 50% because of the positive skewness of the probability distribution of the resulting pressure amplitude. Even though the propeller–propeller and propeller–wing interactions were not considered, the essence of the findings is expected to remain valid for more complex configurations because those interactions are rotor phase-locked.
{"title":"A contribution to the investigation of acoustic interferences in aircraft distributed propulsion","authors":"Sébastien Guérin, Damiano Tormen","doi":"10.1007/s13272-023-00679-6","DOIUrl":"https://doi.org/10.1007/s13272-023-00679-6","url":null,"abstract":"Abstract The objective of this work is to better understand the acoustic interferences created by distributed propulsion engines based on an approach that combines RANS simulation results for the aerodynamic prediction and analytical models to calculate acoustics. A multi-propeller configuration without wing is considered for this investigation. The propeller geometry and the operating conditions are realistic for a regional transport airplane. In the first part of the paper, the results obtained by two different and independent prediction methods are compared. One method is well-established and serves as validation for the second, low-order method, which is better suited for design-to-noise applications since it requires less details as input and is computationally faster by several orders of magnitude. The good agreement between both methods, obtained for a single propeller as well as for the distributed propeller configuration, is exploited in the second part of the paper to investigate the role of acoustic interferences. Taking acoustic interferences into account drastically affects the directivity of the tonal emission. Compared to the results obtained by considering the propellers as if they were uncorrelated, the far-field sound pressure levels can be significantly lower at the radiation nodes or amplified up to the theoretical limit of 9 dB calculated for eight propellers. The directivity patterns depend on the relative initial angular positions of the propellers. When these positions are randomly varied according to the uniform probability density distribution model, the mean result (expectation) is the same as if the propellers were considered as uncorrelated. Finally, the results show that the probability that the acoustic level is lower than the mean value is higher than 50% because of the positive skewness of the probability distribution of the resulting pressure amplitude. Even though the propeller–propeller and propeller–wing interactions were not considered, the essence of the findings is expected to remain valid for more complex configurations because those interactions are rotor phase-locked.","PeriodicalId":38083,"journal":{"name":"CEAS Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-09-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136313592","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}
Pub Date : 2023-09-19DOI: 10.1007/s13272-023-00680-z
Anna A. Kostek, Felix Lößle, Robin Wickersheim, Manuel Keßler, Ronan Boisard, Gabriel Reboul, Antonio Visingardi, Mattia Barbarino, Anthony D. Gardner
Abstract The study provided a base of comparison of known computational techniques with different fidelity levels for performance and noise prediction of a single, fixed-pitch UAV rotor operating with varying flight parameters. The range of aerodynamic tools included blade element theory, potential flow methods (UPM, RAMSYS), lifting-line method (PUMA) and Navier–Stokes solver (FLOWer). Obtained loading distributions served as input for aeroacoustic codes delivering noise estimation for the blade passing frequency on a plane below the rotor. The resulting forces and noise levels showed satisfactory agreement with experimental data; however, differences in accuracy could be noticed depending on the computational method applied. The wake influence on the results was estimated based on vortex trajectories from simulations and those visible in background-oriented schlieren (BOS) pictures. The analysis of scattering effects showed that influence of ground and rotor platform on aeroacoustic results was observable even for low frequencies.
{"title":"Experimental investigation of UAV rotor aeroacoustics and aerodynamics with computational cross-validation","authors":"Anna A. Kostek, Felix Lößle, Robin Wickersheim, Manuel Keßler, Ronan Boisard, Gabriel Reboul, Antonio Visingardi, Mattia Barbarino, Anthony D. Gardner","doi":"10.1007/s13272-023-00680-z","DOIUrl":"https://doi.org/10.1007/s13272-023-00680-z","url":null,"abstract":"Abstract The study provided a base of comparison of known computational techniques with different fidelity levels for performance and noise prediction of a single, fixed-pitch UAV rotor operating with varying flight parameters. The range of aerodynamic tools included blade element theory, potential flow methods (UPM, RAMSYS), lifting-line method (PUMA) and Navier–Stokes solver (FLOWer). Obtained loading distributions served as input for aeroacoustic codes delivering noise estimation for the blade passing frequency on a plane below the rotor. The resulting forces and noise levels showed satisfactory agreement with experimental data; however, differences in accuracy could be noticed depending on the computational method applied. The wake influence on the results was estimated based on vortex trajectories from simulations and those visible in background-oriented schlieren (BOS) pictures. The analysis of scattering effects showed that influence of ground and rotor platform on aeroacoustic results was observable even for low frequencies.","PeriodicalId":38083,"journal":{"name":"CEAS Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-09-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135014533","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}
Pub Date : 2023-09-14DOI: 10.1007/s13272-023-00681-y
Massimo Brunetti, Andrea Nesci, Nicola Bianchi
{"title":"Conceptual design of a distributed electric anti-torque system for enhanced helicopter safety and performance","authors":"Massimo Brunetti, Andrea Nesci, Nicola Bianchi","doi":"10.1007/s13272-023-00681-y","DOIUrl":"https://doi.org/10.1007/s13272-023-00681-y","url":null,"abstract":"","PeriodicalId":38083,"journal":{"name":"CEAS Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-09-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134912827","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}
Pub Date : 2023-09-05DOI: 10.1007/s13272-023-00677-8
Nils Schwagerus, M. Stößel, Michael Krummenauer, D. Kožulović, Reinhard Niehuis
{"title":"Numerical investigation of a Coandă-based fluidic thrust vectoring system for subsonic nozzles","authors":"Nils Schwagerus, M. Stößel, Michael Krummenauer, D. Kožulović, Reinhard Niehuis","doi":"10.1007/s13272-023-00677-8","DOIUrl":"https://doi.org/10.1007/s13272-023-00677-8","url":null,"abstract":"","PeriodicalId":38083,"journal":{"name":"CEAS Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-09-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45367650","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}
Pub Date : 2023-08-26DOI: 10.1007/s13272-023-00678-7
M. Werner, M. Rein, K. Richter, S. Weiss
Abstract The flow field around a generic multi-swept delta wing configuration is investigated under transonic flow conditions, both experimentally and numerically. A special focus is on the analysis of vortex/vortex and vortex/shock interactions at moderate angles of attack. In the present study, the Mach number is varied between $$textrm{Ma} = {0.50}$$ Ma=0.50 and $$textrm{Ma} = {1.41}$$ Ma=1.41 and the angle of attack is varied between $$alpha = 8^circ$$ α=8∘ and $$alpha = 28^circ$$ α=28∘ . Numerical results are validated using experimental surface pressure data from pressure taps, as well as forces and moments based on strain gauge measurements. For selected cases, velocity field data from particle image velocimetry (PIV) measurements are available as well. Over a broad range of angle of attack and Mach number, strong vortex/vortex interactions, including vortex braiding and vortex merging, occur. The location of vortex merging is moving downstream with increasing angle of attack and increasing Mach number. Additionally, at $$textrm{Ma} = {0.85}$$ Ma=0.85 , vortex/shock interaction occurs above the wing. For moderate angles of attack, shock-induced vortex breakdown is observed.
摘要采用实验和数值方法研究了跨声速流动条件下通用多掠三角翼结构的流场。特别关注的是在中等迎角下涡/涡和涡/激波相互作用的分析。在本研究中，马赫数在$$textrm{Ma} = {0.50}$$ Ma = 0.50和$$textrm{Ma} = {1.41}$$ Ma = 1.41之间变化，攻角在$$alpha = 8^circ$$ α = 8°和$$alpha = 28^circ$$ α = 28°之间变化。数值结果使用来自压力水龙头的实验表面压力数据以及基于应变计测量的力和力矩进行验证。对于选定的情况，粒子图像测速(PIV)测量的速度场数据也是可用的。在较大的迎角和马赫数范围内，会发生强涡/涡相互作用，包括涡编织和涡合并。随着迎角的增大和马赫数的增大，涡合并的位置向下游移动。此外，在$$textrm{Ma} = {0.85}$$ Ma = 0.85时，机翼上方出现了涡/激波相互作用。对于中等迎角，可以观察到激波引起的涡流击穿。
{"title":"Experimental and numerical analysis of the aerodynamics and vortex interactions on multi-swept delta wings","authors":"M. Werner, M. Rein, K. Richter, S. Weiss","doi":"10.1007/s13272-023-00678-7","DOIUrl":"https://doi.org/10.1007/s13272-023-00678-7","url":null,"abstract":"Abstract The flow field around a generic multi-swept delta wing configuration is investigated under transonic flow conditions, both experimentally and numerically. A special focus is on the analysis of vortex/vortex and vortex/shock interactions at moderate angles of attack. In the present study, the Mach number is varied between $$textrm{Ma} = {0.50}$$ <mml:math xmlns:mml=\"http://www.w3.org/1998/Math/MathML\"> <mml:mrow> <mml:mtext>Ma</mml:mtext> <mml:mo>=</mml:mo> <mml:mrow> <mml:mn>0.50</mml:mn> </mml:mrow> </mml:mrow> </mml:math> and $$textrm{Ma} = {1.41}$$ <mml:math xmlns:mml=\"http://www.w3.org/1998/Math/MathML\"> <mml:mrow> <mml:mtext>Ma</mml:mtext> <mml:mo>=</mml:mo> <mml:mrow> <mml:mn>1.41</mml:mn> </mml:mrow> </mml:mrow> </mml:math> and the angle of attack is varied between $$alpha = 8^circ$$ <mml:math xmlns:mml=\"http://www.w3.org/1998/Math/MathML\"> <mml:mrow> <mml:mi>α</mml:mi> <mml:mo>=</mml:mo> <mml:msup> <mml:mn>8</mml:mn> <mml:mo>∘</mml:mo> </mml:msup> </mml:mrow> </mml:math> and $$alpha = 28^circ$$ <mml:math xmlns:mml=\"http://www.w3.org/1998/Math/MathML\"> <mml:mrow> <mml:mi>α</mml:mi> <mml:mo>=</mml:mo> <mml:msup> <mml:mn>28</mml:mn> <mml:mo>∘</mml:mo> </mml:msup> </mml:mrow> </mml:math> . Numerical results are validated using experimental surface pressure data from pressure taps, as well as forces and moments based on strain gauge measurements. For selected cases, velocity field data from particle image velocimetry (PIV) measurements are available as well. Over a broad range of angle of attack and Mach number, strong vortex/vortex interactions, including vortex braiding and vortex merging, occur. The location of vortex merging is moving downstream with increasing angle of attack and increasing Mach number. Additionally, at $$textrm{Ma} = {0.85}$$ <mml:math xmlns:mml=\"http://www.w3.org/1998/Math/MathML\"> <mml:mrow> <mml:mtext>Ma</mml:mtext> <mml:mo>=</mml:mo> <mml:mrow> <mml:mn>0.85</mml:mn> </mml:mrow> </mml:mrow> </mml:math> , vortex/shock interaction occurs above the wing. For moderate angles of attack, shock-induced vortex breakdown is observed.","PeriodicalId":38083,"journal":{"name":"CEAS Aeronautical Journal","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-08-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135181507","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}
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