Journal of Aircraft最新文献_第3页

Study on the Anti-Icing of Conical Rotating Spinners with Different Cone Angles 不同锥角锥形旋转纺纱机的防结冰研究

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-28 DOI: 10.2514/1.c037904

Ningli Chen, Xian Yi, Jinghao Ren, Qiang Wang, Ke Li

引用次数: 0

Low-Order Modeling of Stacked Rotor Performance in Hover 堆叠式转子悬停性能的低阶建模

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-28 DOI: 10.2514/1.c037555

Chloe Johnson, Jayant Sirohi

引用次数: 0

Scale Effects in Wind Tunnel Testing: Extrapolation of the Drag Coefficient 风洞试验中的规模效应：阻力系数外推法

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-28 DOI: 10.2514/1.c037907

Lance W. Traub

引用次数: 0

Quantifying Impacts of Uncertainties on Certification-Driven Design 量化不确定性对认证驱动设计的影响

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-17 DOI: 10.2514/1.c037615

Jiacheng Xie, Evan D. Harrison, Dimitri N. Mavris

{"title":"Quantifying Impacts of Uncertainties on Certification-Driven Design","authors":"Jiacheng Xie, Evan D. Harrison, Dimitri N. Mavris","doi":"10.2514/1.c037615","DOIUrl":"https://doi.org/10.2514/1.c037615","url":null,"abstract":"Airworthiness certification is challenging for novel aircraft concepts. To avoid the significant cost associated with the redesign for certification compliance, incorporating certification requirements into early aircraft design is desired for unconventional aircraft. However, epistemic uncertainties arising from modeling assumptions, and aleatory uncertainties stemming from uncontrollable noise factors may have impacts on the certification analysis and certification-constrained design process. This paper presents an uncertainty quantification study based on a certification-constrained design and optimization study previously conducted for NASA’s Parallel Electric–Gas Architecture with Synergistic Utilization Scheme (PEGASUS) concept. The epistemic uncertainties are modeled through a set of multiplicative factors applied to intermediate disciplinary variables. The sensitivity analysis between design metrics and multiplicative factors reveals that uncertainties in stability and control derivatives can significantly affect certification constraint predictions, and uncertainties in drag approximations have considerable impacts on the vehicle sizing process. The aleatory uncertainties added to flight dynamics simulations include wind velocities and variations of weight and center of gravity. Four representative design candidates are evaluated for their robustness against aleatory uncertainties based on the Monte Carlo simulation performed on noise factors. The results show that aleatory uncertainties can affect the aircraft dynamic responses in flight test simulations, thus compromising certification compliance.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":null,"pages":null},"PeriodicalIF":2.2,"publicationDate":"2024-05-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140963603","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Aerodynamic Modeling of a Missile Combining Transfer Learning and Dendritic Net 结合迁移学习和树枝状网的导弹空气动力学建模

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-14 DOI: 10.2514/1.c037865

Zijian Ni, Shiwei Chen, Zejun Zhu, Wei Wang

引用次数: 0

Actuator Surface Modeling of Rotors at the Ship–Helicopter Dynamic Interface 船舶-直升机动态界面上的旋翼致动器表面建模

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-13 DOI: 10.2514/1.c037034

Daniel Linton, Ben Thornber

引用次数: 0

Performance Improvement of Winged Compound Helicopter Due to Differential Flap Deflections 差异襟翼挠度改善翼型复合直升机的性能

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-08 DOI: 10.2514/1.c037307

Hideaki Sugawara, Yasutada Tanabe, Masaharu Kameda

引用次数: 0

Machine Learning Models for Multirotor Performance Prediction 用于多旋翼飞行器性能预测的机器学习模型

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-06 DOI: 10.2514/1.c037460

Jason Cornelius, Sven Schmitz

引用次数: 0

Propeller Ceiling Effect in Forward Flight 正向飞行中的螺旋桨升限效应

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-02 DOI: 10.2514/1.c037779

Jielong Cai, Sidaard Gunasekaran

{"title":"Propeller Ceiling Effect in Forward Flight","authors":"Jielong Cai, Sidaard Gunasekaran","doi":"10.2514/1.c037779","DOIUrl":"https://doi.org/10.2514/1.c037779","url":null,"abstract":"The study extends the investigation of the fixed-pitch small-scale propeller in the ceiling effect to forward flight conditions at different propeller incidence angles. Force-based experiments, phase-locked particle image velocimetry (PIV), and surface oil flow visualization were conducted on two APC propellers at the University of Dayton Low Speed Wind Tunnel. For propellers in edgewise flight, the power required at constant thrust decreases at small advance ratios for each <math altimg=\"eq-00001.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mi>h</mi><mo>/</mo><mi>D</mi></mrow></math> and then increases with a further increase in the advance ratio. Tilting the propeller forward reduces the ceiling effect benefits in both thrust and power, particularly at higher advance ratios. Performance similarity in the propeller ceiling effect at different <math altimg=\"eq-00002.gif\" display=\"inline\" overflow=\"scroll\"><mrow><mi>h</mi><mo>/</mo><mi>D</mi></mrow></math> is observed, and a performance prediction method is proposed. Phase-locked PIV showed an increase in the propeller inflow angle in the ceiling effect at small advance ratios, resulting in higher thrust generation. This effect reduces with an increase in the advance ratio due to minimized interactions with the ceiling plate. Hence, the measured propeller in-ceiling-effect (ICE) propeller performance cannot represent the propeller ICE performance at a higher forward flight speed. Additionally, PIV and surface flow visualization indicated the presence of a stagnation point on the ceiling plate near the trailing side of the propeller disk at higher advance ratios, leading to a reduction in propeller thrust generation.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":null,"pages":null},"PeriodicalIF":2.2,"publicationDate":"2024-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140841618","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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

Design Exploration of a Distributed Electric Propulsion Aircraft Using Explainable Surrogate Models 利用可解释代用模型探索分布式电力推进飞机的设计思路

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2024-05-02 DOI: 10.2514/1.c037848

Pramudita Satria Palar, Eric Nguyen Van, Nathalie Bartoli, Joseph Morlier

{"title":"Design Exploration of a Distributed Electric Propulsion Aircraft Using Explainable Surrogate Models","authors":"Pramudita Satria Palar, Eric Nguyen Van, Nathalie Bartoli, Joseph Morlier","doi":"10.2514/1.c037848","DOIUrl":"https://doi.org/10.2514/1.c037848","url":null,"abstract":"Distributed electric propulsion in aircraft design is a concept that involves placing multiple electric motors across the aircraft’s airframe. Such a system has the potential to contribute to sustainable aviation by significantly reducing greenhouse gas emissions, minimizing noise pollution, improving fuel efficiency, and encouraging the use of cleaner energy sources. This paper investigates the impact and relationship of turbo-electric propulsion component characteristics with three performance quantities of interest: lift-to-drag ratio, operating empty weight, and fuel burn. Using the small- and medium-range “DRAGON” aircraft concept, we performed design exploration enabled through the explainable surrogate model strategy. This work uses Shapley additive explanations to illuminate the dependencies of these critical performance metrics on specific turbo-electric propulsion component characteristics, offering valuable insights to inform future advancements in electric propulsion technology. Through global sensitivity analysis, the study reveals a significant impact of electrical power unit (EPU) power density on lift-to-drag ratio, alongside notable roles played by EPU-specific power and applied voltage. For operating empty weight, EPU-specific power and voltage are highlighted as critical factors, while turboshaft power-specific fuel consumption notably influences fuel burn. The analysis concludes by exploring the implications of the insights for the future development of turbo-electric propulsion technology.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":null,"pages":null},"PeriodicalIF":2.2,"publicationDate":"2024-05-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"140841171","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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