Journal of Propulsion and Power最新文献_第6页

Acoustic Waves Generated in Hypergolic Drop Tests of Low- and High-Volatility Fuels 低挥发性和高挥发性燃料自燃跌落试验中产生的声波

IF 1.9 4区工程技术

Journal of Propulsion and Power Pub Date : 2023-11-20 DOI: 10.2514/1.b39290

Hongjae Kang, Chungman Kim, Jongkwang Lee

引用次数: 0

Overview of Selected Serpentine Duct Simulations Using Computational Fluid Dynamics 概览选定的蛇形管道模拟使用计算流体动力学

IF 1.9 4区工程技术

Journal of Propulsion and Power Pub Date : 2023-11-15 DOI: 10.2514/1.b39351

Neal D. Domel

引用次数: 0

Benefits of Spin Polarization for Inertial and Magneto-Inertial Fusion Propulsion 自旋极化对惯性和磁-惯性聚变推进的好处

IF 1.9 4区工程技术

Journal of Propulsion and Power Pub Date : 2023-11-15 DOI: 10.2514/1.b39138

Gerrit Bruhaug, Ayden Kish

引用次数: 0

Machine-Learning-Based Rotating Detonation Engine Diagnostics: Evaluation for Application in Experimental Facilities 基于机器学习的旋转爆震发动机诊断:在实验设施中的应用评估

4区工程技术

Journal of Propulsion and Power Pub Date : 2023-11-07 DOI: 10.2514/1.b39287

Kristyn B. Johnson, Don Ferguson, Andrew Nix

{"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":"85 12","pages":"0"},"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}

引用次数: 0

Fuel Injector Requirements to Achieve Supercritical Flow at the Exit 喷油器在出口达到超临界流动的要求

4区工程技术

Journal of Propulsion and Power Pub Date : 2023-11-02 DOI: 10.2514/1.b39265

Zachary B. Harris, Joshua A. Bittle, Ajay K. Agrawal

{"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":"14 6","pages":"0"},"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}

引用次数: 0

Numerical Simulations of Fuel Shape Change in Paraffin–Oxygen Hybrid Rocket Engines 石蜡-氧混合火箭发动机燃料形态变化的数值模拟

4区工程技术

Journal of Propulsion and Power Pub Date : 2023-11-01 DOI: 10.2514/1.b39086

Mario Tindaro Migliorino, Giorgio Gubernari, Daniele Bianchi, Francesco Nasuti, Daniele Cardillo, Francesco Battista

引用次数: 3

Rheological, Ballistic, and Mechanical Properties of 3D Printed, Photocured Composite Propellants 3D打印、光固化复合推进剂的流变、弹道和机械性能

4区工程技术

Journal of Propulsion and Power Pub Date : 2023-11-01 DOI: 10.2514/1.b39113

Justin Lajoie, Jacob Blocker, Travis Sippel

{"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":"256 ","pages":"0"},"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}

引用次数: 1

Solid-Fuel Ramjet Regression Rate Measurements Using X-Ray Radiography and Ultrasonic Transducers 固体燃料冲压发动机的回归率测量使用x射线摄影和超声波换能器

4区工程技术

Journal of Propulsion and Power Pub Date : 2023-11-01 DOI: 10.2514/1.b39210

Jay V. Evans, Brandon T. Reid, Rohan M. Gejji, Carson D. Slabaugh

{"title":"Solid-Fuel Ramjet Regression Rate Measurements Using X-Ray Radiography and Ultrasonic Transducers","authors":"Jay V. Evans, Brandon T. Reid, Rohan M. Gejji, Carson D. Slabaugh","doi":"10.2514/1.b39210","DOIUrl":"https://doi.org/10.2514/1.b39210","url":null,"abstract":"The instantaneous fuel regression rate within a solid-fuel ramjet combustor was characterized using X-ray radiography and ultrasonic transducer measurements. Experiments were performed with cylindrical center-perforated hydroxyl-terminated polybutadiene fuel grains at three mass fluxes ([Formula: see text]) with consistent inlet total temperatures and chamber pressures. Ultrasonic transducer measurements demonstrated changes of web thickness ranging from 7.50 to 9.85 mm and regression rate measurements ranging from 1.35 to [Formula: see text]. The local maxima of change in the web thickness due to flow reattachment and erosive burning were consistently measured with the ultrasonic transducers. Changes in the port radius on the order of 8–9 mm and regression rates of approximately [Formula: see text] were deduced from the X-ray radiography images. The structure of the flow reattachment region was evident in measurements from the X-ray radiography images captured near the combustor entrance, whereas images captured at the midlength of the combustor exhibited more uniform fuel regression profiles. Ultrasonic measurements of change in the web thickness were consistently greater in magnitude relative to X-ray radiography measurements. X-ray radiography imaging allowed for the more accurate measurement of fuel regression with the greatest axial spatial resolution, whereas ultrasonic transducer measurements yielded the greatest radial spatial resolution. The change in web thickness calculated with weight-based techniques yielded smaller-magnitude measurements of change in the web thickness relative to X-ray radiography. The regression rate was largely invariant with the mass flux within the investigated operating regime.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":"65 4","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-11-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134996582","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}

引用次数: 1

Combined Cycle Nuclear System Architecture for Crewed Mars Spacecraft Propulsion and Power 载人火星航天器推进与动力联合循环核系统结构

4区工程技术

Journal of Propulsion and Power Pub Date : 2023-10-24 DOI: 10.2514/1.b39149

Jack V. Maydan, James A. Nabity

{"title":"Combined Cycle Nuclear System Architecture for Crewed Mars Spacecraft Propulsion and Power","authors":"Jack V. Maydan, James A. Nabity","doi":"10.2514/1.b39149","DOIUrl":"https://doi.org/10.2514/1.b39149","url":null,"abstract":"Nuclear thermal propulsion can potentially reduce the time of flight and spacecraft system mass needed for human spaceflight beyond cislunar space. This nuclear propulsion system has comparable thrust capability to chemically impulsive systems, which at about twice the specific impulse, can double the delta-velocity ([Formula: see text]) for the same propellant mass. However, the canonical problem for nuclear propulsion has always been that its benefits are shadowed by low technology readiness of a complex system. This paper describes a combined cycle nuclear thermal rocket (CCNTR) system architecture for propulsion and electrical power that comprises a 42-MWt-capable nuclear reactor core to provide 9.4 kN thrust on demand at a specific impulse of 940 s. The liquid hydrogen propellant flow through the rocket chamber cools the reactor during burns, thereby producing thrust while concurrently rejecting waste heat to space. The reactor also produces up to 100 kWe power for the spacecraft, eliminating the need for solar power generation and averting challenges associated with restarting a cold reactor for propulsive burns. Radiators reject the waste heat from electrical power production. Earth-to-Mars orbital transfers less than 100 days appear feasible assuming 680,000 kg of liquid hydrogen propellant and a vehicle dry mass of 83,000 kg that includes the 13,000 kg CCNTR system. Together, these results suggest that a CCNTR could be most promising to enable crewed missions to Mars.","PeriodicalId":16903,"journal":{"name":"Journal of Propulsion and Power","volume":"8 4","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135316516","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}

引用次数: 0

Extinguishing and Combustion Characteristics of Electrically Controllable Solid Propellants Under Elevated Pressures 高压下电控固体推进剂的灭火和燃烧特性

4区工程技术

Journal of Propulsion and Power Pub Date : 2023-10-24 DOI: 10.2514/1.b39189

Bradley Gobin, Paul Reiter, Sean Whalen, Gregory Young

引用次数: 0