Kirankumar Purohit, Abhishek Sharma, Aravind Vaidyanathan, T. John Tharakan
Journal of Propulsion and Power, Ahead of Print.
推进与动力杂志》，印刷版前。
{"title":"Multi-Element Gaseous Methane–Oxygen Rocket Combustor Optimization for Modern Space-Flight Technology","authors":"Kirankumar Purohit, Abhishek Sharma, Aravind Vaidyanathan, T. John Tharakan","doi":"10.2514/1.b39248","DOIUrl":"https://doi.org/10.2514/1.b39248","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":"2023-12-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139057529","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}
Dakun Sun, Ruize Xu, Xu Dong, Jia Li, Xiaofeng Sun
Journal of Propulsion and Power, Ahead of Print.
推进与动力杂志》，印刷版前。
{"title":"Aeroengine Stall Warning by Multicorrelation Analysis","authors":"Dakun Sun, Ruize Xu, Xu Dong, Jia Li, Xiaofeng Sun","doi":"10.2514/1.b39230","DOIUrl":"https://doi.org/10.2514/1.b39230","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":"2023-12-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138562220","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}
Wei Sun, Yuntao Guo, Zhiwen Wu, Zening Du, Ningfei Wang, Zhenning Sun
Journal of Propulsion and Power, Ahead of Print.
推进与动力杂志，印刷前。
{"title":"Design and Performance of an Electrowetting Ionic Liquid Electrospray Thruster Prototype","authors":"Wei Sun, Yuntao Guo, Zhiwen Wu, Zening Du, Ningfei Wang, Zhenning Sun","doi":"10.2514/1.b39201","DOIUrl":"https://doi.org/10.2514/1.b39201","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":"2023-11-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138504331","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}
{"title":"Acoustic Waves Generated in Hypergolic Drop Tests of Low- and High-Volatility Fuels","authors":"Hongjae Kang, Chungman Kim, Jongkwang Lee","doi":"10.2514/1.b39290","DOIUrl":"https://doi.org/10.2514/1.b39290","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":"2023-11-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138504312","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}
{"title":"Overview of Selected Serpentine Duct Simulations Using Computational Fluid Dynamics","authors":"Neal D. Domel","doi":"10.2514/1.b39351","DOIUrl":"https://doi.org/10.2514/1.b39351","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":"2023-11-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138504311","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}
{"title":"Benefits of Spin Polarization for Inertial and Magneto-Inertial Fusion Propulsion","authors":"Gerrit Bruhaug, Ayden Kish","doi":"10.2514/1.b39138","DOIUrl":"https://doi.org/10.2514/1.b39138","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":"2023-11-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138504310","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}
Real-time monitoring of combustion behavior is a crucial step toward actively controlled rotating detonation engine (RDE) operation in laboratory and industrial environments. Various machine learning methods have been developed to advance diagnostic efficiencies from conventional postprocessing efforts to real-time methods. This work evaluates and compares conventional techniques alongside convolutional neural network (CNN) architectures trained in previous studies, including image classification, object detection, and time series classification, according to metrics affecting diagnostic feasibility, external applicability, and performance. Real-time, capable diagnostics are deployed and evaluated using an altered experimental setup. Image-based CNNs are applied to externally provided images to approximate dataset restrictions. Image classification using high-speed chemiluminescence images and time series classification using high-speed flame ionization and pressure measurements achieve classification speeds enabling real-time diagnostic capabilities, averaging laboratory-deployed diagnostic feedback rates of 4–5 Hz. Object detection achieves the most refined resolution of [Formula: see text] in postprocessing. Image and time series classification require the additional correlation of sensor data, extending their time-step resolutions to 80 ms. Comparisons show that no single diagnostic approach outperforms its competitors across all metrics. This finding justifies the need for a machine learning portfolio containing a host of networks to address specific needs throughout the RDE research community.
{"title":"Machine-Learning-Based Rotating Detonation Engine Diagnostics: Evaluation for Application in Experimental Facilities","authors":"Kristyn B. Johnson, Don Ferguson, Andrew Nix","doi":"10.2514/1.b39287","DOIUrl":"https://doi.org/10.2514/1.b39287","url":null,"abstract":"Real-time monitoring of combustion behavior is a crucial step toward actively controlled rotating detonation engine (RDE) operation in laboratory and industrial environments. Various machine learning methods have been developed to advance diagnostic efficiencies from conventional postprocessing efforts to real-time methods. This work evaluates and compares conventional techniques alongside convolutional neural network (CNN) architectures trained in previous studies, including image classification, object detection, and time series classification, according to metrics affecting diagnostic feasibility, external applicability, and performance. Real-time, capable diagnostics are deployed and evaluated using an altered experimental setup. Image-based CNNs are applied to externally provided images to approximate dataset restrictions. Image classification using high-speed chemiluminescence images and time series classification using high-speed flame ionization and pressure measurements achieve classification speeds enabling real-time diagnostic capabilities, averaging laboratory-deployed diagnostic feedback rates of 4–5 Hz. Object detection achieves the most refined resolution of [Formula: see text] in postprocessing. Image and time series classification require the additional correlation of sensor data, extending their time-step resolutions to 80 ms. Comparisons show that no single diagnostic approach outperforms its competitors across all metrics. This finding justifies the need for a machine learning portfolio containing a host of networks to address specific needs throughout the RDE research community.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135540419","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}
Zachary B. Harris, Joshua A. Bittle, Ajay K. Agrawal
Advanced engine designs and alternative fuels introduce the possibility of supercritical fuel injection in aviation gas turbines and diesel engines, as is already the case for many rocket engines. Previous studies have focused mainly on fuel–air mixing in the supercritical regime after injection. However, injector requirements to achieve supercritical flow at the exit have not been investigated systematically. In this study, supercritical flow in an injector is analyzed using computational fluid dynamics with a real gas model and fluid properties derived from Helmholtz equations of state. Three operational challenges are illustrated depending upon the fuel: 1) large decreases in pressure and temperature within the injector, 2) injector choking, and 3) supersonic expansion of the supercritical jet. These challenges are addressed by developing and validating a one-dimensional, nonisentropic model of supercritical flow in the injector. This reduced-order model can guide injector designs for different fuels and applications and help decouple the injector supercritical flow from that in the downstream chamber to significantly reduce the computational effort for fuel–air mixing simulations. Results show that larger-diameter injectors are generally required to achieve supercritical injection with a fuel energy injection rate per unit area matching that of a typical diesel injector.
{"title":"Fuel Injector Requirements to Achieve Supercritical Flow at the Exit","authors":"Zachary B. Harris, Joshua A. Bittle, Ajay K. Agrawal","doi":"10.2514/1.b39265","DOIUrl":"https://doi.org/10.2514/1.b39265","url":null,"abstract":"Advanced engine designs and alternative fuels introduce the possibility of supercritical fuel injection in aviation gas turbines and diesel engines, as is already the case for many rocket engines. Previous studies have focused mainly on fuel–air mixing in the supercritical regime after injection. However, injector requirements to achieve supercritical flow at the exit have not been investigated systematically. In this study, supercritical flow in an injector is analyzed using computational fluid dynamics with a real gas model and fluid properties derived from Helmholtz equations of state. Three operational challenges are illustrated depending upon the fuel: 1) large decreases in pressure and temperature within the injector, 2) injector choking, and 3) supersonic expansion of the supercritical jet. These challenges are addressed by developing and validating a one-dimensional, nonisentropic model of supercritical flow in the injector. This reduced-order model can guide injector designs for different fuels and applications and help decouple the injector supercritical flow from that in the downstream chamber to significantly reduce the computational effort for fuel–air mixing simulations. Results show that larger-diameter injectors are generally required to achieve supercritical injection with a fuel energy injection rate per unit area matching that of a typical diesel injector.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135974696","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}
Mario Tindaro Migliorino, Giorgio Gubernari, Daniele Bianchi, Francesco Nasuti, Daniele Cardillo, Francesco Battista
Reynolds-averaged Navier–Stokes simulations with submodels of turbulence, chemistry, fluid–surface interaction, and radiation are performed in this work to rebuild the internal ballistics of an experimentally tested hybrid rocket engine with paraffin and gaseous oxygen as propellants. Firstly, the effects of the prechamber and postchamber cavities at the initial, average, and final diameter of a reference burn are assessed to be negligible. Then, numerical simulations modeling the fuel shape change in space and time are compared to simulations performed at uniform port radius. The latter provide reasonable regression rate, pressure, and final grain profile predictions with reduced computational cost. On the other hand, the more computationally expensive fuel shape change simulations improve the model prediction capabilities providing a more accurate comparison with experimental data. The fuel shape change approach is finally applied with success to simulations of a throttled burn.
{"title":"Numerical Simulations of Fuel Shape Change in Paraffin–Oxygen Hybrid Rocket Engines","authors":"Mario Tindaro Migliorino, Giorgio Gubernari, Daniele Bianchi, Francesco Nasuti, Daniele Cardillo, Francesco Battista","doi":"10.2514/1.b39086","DOIUrl":"https://doi.org/10.2514/1.b39086","url":null,"abstract":"Reynolds-averaged Navier–Stokes simulations with submodels of turbulence, chemistry, fluid–surface interaction, and radiation are performed in this work to rebuild the internal ballistics of an experimentally tested hybrid rocket engine with paraffin and gaseous oxygen as propellants. Firstly, the effects of the prechamber and postchamber cavities at the initial, average, and final diameter of a reference burn are assessed to be negligible. Then, numerical simulations modeling the fuel shape change in space and time are compared to simulations performed at uniform port radius. The latter provide reasonable regression rate, pressure, and final grain profile predictions with reduced computational cost. On the other hand, the more computationally expensive fuel shape change simulations improve the model prediction capabilities providing a more accurate comparison with experimental data. The fuel shape change approach is finally applied with success to simulations of a throttled burn.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136018602","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}
This study explores the rheological, mechanical, and ballistic properties of printed ammonium perchlorate composite propellant at 82.5% solids loading with binders curable with ultraviolet light of wavelength from 215 to 400 nm (UV). A polybutadiene urethane acrylate and two polyester urethane acrylate propellants are printed by an in-house-fabricated fused deposition molding printer. Propellants are all shear-thinning and have significantly lower viscosity than similar hydroxyl-terminated polybutadiene (HTPB) propellants. Uniaxial stress–strain measurements indicate that ultimate tensile strength and ultimate tensile strain of all photocurable propellants are found to be greater than HTPB propellant. In particular, the ultimate tensile strain of polyester urethane acrylate propellant is six times that of HTPB propellant, demonstrating high compliance. Ballistic properties are measured from combustion of printed propellant articles in a windowed Crawford combustion bomb at inert gas pressures of up to 12.1 MPa. The burning characteristics were found to be relatively planar, though strong burning rate anisotropy, expected as a result of print layer inhomogeneities, was observed in two of the three formulations. Overall, pressure exponents of the propellants were mild and ranged from 0.17 to 0.33. These results are compared and contrasted to those of other printed propellants. These results provide valuable insight into the selection of a safe binder system for printing of photocurable composite propellants.
{"title":"Rheological, Ballistic, and Mechanical Properties of 3D Printed, Photocured Composite Propellants","authors":"Justin Lajoie, Jacob Blocker, Travis Sippel","doi":"10.2514/1.b39113","DOIUrl":"https://doi.org/10.2514/1.b39113","url":null,"abstract":"This study explores the rheological, mechanical, and ballistic properties of printed ammonium perchlorate composite propellant at 82.5% solids loading with binders curable with ultraviolet light of wavelength from 215 to 400 nm (UV). A polybutadiene urethane acrylate and two polyester urethane acrylate propellants are printed by an in-house-fabricated fused deposition molding printer. Propellants are all shear-thinning and have significantly lower viscosity than similar hydroxyl-terminated polybutadiene (HTPB) propellants. Uniaxial stress–strain measurements indicate that ultimate tensile strength and ultimate tensile strain of all photocurable propellants are found to be greater than HTPB propellant. In particular, the ultimate tensile strain of polyester urethane acrylate propellant is six times that of HTPB propellant, demonstrating high compliance. Ballistic properties are measured from combustion of printed propellant articles in a windowed Crawford combustion bomb at inert gas pressures of up to 12.1 MPa. The burning characteristics were found to be relatively planar, though strong burning rate anisotropy, expected as a result of print layer inhomogeneities, was observed in two of the three formulations. Overall, pressure exponents of the propellants were mild and ranged from 0.17 to 0.33. These results are compared and contrasted to those of other printed propellants. These results provide valuable insight into the selection of a safe binder system for printing of photocurable composite propellants.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136103225","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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