Aerospace最新文献_第6页

Numerical Investigation of Model Support, Closed Engine Nacelle and Scale Effect on a Wind Tunnel Test Model 模型支撑、封闭式发动机短舱和风洞试验模型比例效应的数值研究

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-06-11 DOI: 10.3390/aerospace11060464

Ioan-Laurentiu Padureanu, D. Pepelea, Gilbert Stoican, Marco Marini, Nicole Viola, Matthew Clay

{"title":"Numerical Investigation of Model Support, Closed Engine Nacelle and Scale Effect on a Wind Tunnel Test Model","authors":"Ioan-Laurentiu Padureanu, D. Pepelea, Gilbert Stoican, Marco Marini, Nicole Viola, Matthew Clay","doi":"10.3390/aerospace11060464","DOIUrl":"https://doi.org/10.3390/aerospace11060464","url":null,"abstract":"In the frame of the H2020 MORE&LESS project co-funded by European Commission, a test campaign for a hypersonic vehicle demonstrator took place at the INCAS Trisonic Facility. CFD analysis was used to quantify the effects of the wind tunnel model support, the closed engine nacelle, and to perform the Reynolds number extrapolation. Three sets of simulations were used in order to generate the corrections. The wind tunnel configuration with sting, sting cavity, and closed nacelle was used as the baseline, with the aim of matching the experimental results as precisely as possible. A configuration with a flow-through nacelle and the shock cone in the appropriate position for each Mach number and no sting or cavity was used to determine the effect of the sting and the closed nacelle. For the Reynolds extrapolation, a 1:1 model was used, with the boundary conditions deriving from the theoretical trajectory of the vehicle. The CFD results for the wind tunnel configuration closely align with the experimental data. Significant differences between the three configurations can be observed just for the pitching moment, and those are caused by the presence of the sting and the open nacelle. The difference in Reynolds number does not seem to have a significant effect on the aerodynamic coefficients.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":null,"pages":null},"PeriodicalIF":2.6,"publicationDate":"2024-06-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141355866","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

An rVPM-Based Aerodynamic Hybrid Optimization Method for Coaxial Rotor with Differentiated Upper and Lower Blades in Both Hover and High-Speed Cruising States 基于 rVPM 的气动混合优化方法，适用于悬停和高速巡航状态下具有不同上下叶片的同轴转子

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-06-09 DOI: 10.3390/aerospace11060463

Zhiwei Ding, Dengyan Duan, Chaoqun Zhang, Jianbo Li

引用次数: 0

Structural Analysis and Testing of a Flexible Rudder Using a Cosine Honeycomb Structure 使用余弦蜂窝结构的柔性尾舵的结构分析与测试

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-06-08 DOI: 10.3390/aerospace11060462

Jinwei Huang, Weidong Liu, Yue Zhou, Dian Liu

{"title":"Structural Analysis and Testing of a Flexible Rudder Using a Cosine Honeycomb Structure","authors":"Jinwei Huang, Weidong Liu, Yue Zhou, Dian Liu","doi":"10.3390/aerospace11060462","DOIUrl":"https://doi.org/10.3390/aerospace11060462","url":null,"abstract":"This paper introduces a new type of flexible rudder surface based on the cosine-type zero Poisson’s ratio honeycomb to enhance the adaptive capabilities of aircraft and enable multi-condition, rudderless flight. The zero Poisson’s ratio honeycomb structure exhibits exceptional in-plane and out-of-plane deformation capacities, as well as a high load-bearing capability. To investigate the deformation characteristics of flexible rudder surfaces utilizing cosine honeycomb structures, this study undertakes a comprehensive investigation through finite element simulation and 3D printing experiments. Moreover, this study analyzed the impact of honeycomb parameters and layout on the deflection performance and weight. The flexible rudder surface, fabricated from nylon, achieves smooth and consistent chordwise bending deformation, as well as uniform spanwise deformation within a tolerance of ±25°, and the maximum equivalent stress observed was 31.99 MPa, which is within the material’s allowable stress limits (50 MPa). Finite element simulation results indicate that once the deflection angle of the rocker exceeds 15°, a discernible deviation arises between the actual deflection angle of the flexible control surface and that of the rocker. Furthermore, this deviation escalates with increasing rocker rotation angles, and this discrepancy can be mitigated by augmenting the number of cosine honeycomb cells within the flexible rudder surface. Finally, a prototype of the flexible rudder surface was successfully produced using 3D printing technology, and the experimental results confirmed the deformation behavior, aligning with simulation outcomes with a deviation of less than 20%. These findings confirm the effective deflection performance of the designed flexible rudder surface, highlighting its potential application in small unmanned aerial vehicles.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":null,"pages":null},"PeriodicalIF":2.6,"publicationDate":"2024-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141369424","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

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-06-07 DOI: 10.3390/aerospace11060461

Peiran Qiao, Minghua Hu, Jianan Yin, Jiaming Su, Yutong Chen, Mengxuan Yin

{"title":"An Adaptive Similar Scenario Matching Method for Predicting Aircraft Taxiing Time","authors":"Peiran Qiao, Minghua Hu, Jianan Yin, Jiaming Su, Yutong Chen, Mengxuan Yin","doi":"10.3390/aerospace11060461","DOIUrl":"https://doi.org/10.3390/aerospace11060461","url":null,"abstract":"Accurate prediction of taxiing time is important in ensuring efficient and safe operations on the airport surface. It helps improve ground operation efficiency, reduce fuel waste, and improve carbon emissions at the airport. In actual operations, taxiing time is influenced by various factors, including a large number of categorical features. However, few previous studies have focused on selecting such features. Additionally, traditional taxiing time prediction methods are often black-box models that only provide a single prediction result; they fail to provide effective practical references for controllers. Therefore, this paper analyses the features that affect taxiing time from different data types and forms a taxi feature set consisting of nine key features. We also propose a taxiing time prediction method based on adaptive scenario matching rules. This process classifies the scenarios into multiple typical historical scenario sets and adaptively matches the current target scenario to a typical scenario set based on quantified rules. Then, based on the matching results, a pre-trained model obtained from the corresponding scenario set is used to predict the taxiing time of an aircraft in the target scenario, aiming to mitigate the impact of data heterogeneity on prediction results. Experimental results show that compared to baseline methods, the mean absolute error and root mean square error of the proposed method decreased by 4.8% and 12.6%, respectively. This method significantly reduces the fluctuations in results caused by sample heterogeneity and enhances controllers’ acceptance of prediction results from the model. It can be used to further improve auxiliary decision making systems and enhance the precise control capabilities of airport surface operations.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":null,"pages":null},"PeriodicalIF":2.6,"publicationDate":"2024-06-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141371106","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

Optimal Impulsive Orbit Transfers from Gateway to Low Lunar Orbit 从网关到低月球轨道的最佳脉冲轨道转换

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-06-07 DOI: 10.3390/aerospace11060460

Dario Sanna, Edoardo Maria Leonardi, G. De Angelis, Mauro Pontani

引用次数: 0

An Information Integration Technology for Safety Assessment on Civil Airborne System 用于民用航空系统安全评估的信息集成技术

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-06-06 DOI: 10.3390/aerospace11060459

Xi Chen, Quan Zou, Jie Bai, Lei Dong

{"title":"An Information Integration Technology for Safety Assessment on Civil Airborne System","authors":"Xi Chen, Quan Zou, Jie Bai, Lei Dong","doi":"10.3390/aerospace11060459","DOIUrl":"https://doi.org/10.3390/aerospace11060459","url":null,"abstract":"With the significant expansion of civil aviation, particularly in the low-altitude economy, there is a significant gap between the escalating demand for airworthiness certification of novel aircraft designs, such as electric vertical take-off and landing (eVTOL) vehicles, and the inefficiency of the current safety assessment process. This gap is partially attributed to safety assessors’ limited exposure to these innovative aircraft models in the safety assessment process, necessitating extensive efforts in identifying precedents and their handling strategies. Complicating matters further, pertinent case studies are scattered across diverse, unstandardized digital formats, obliging assessors to navigate voluminous electronic records while concurrently establishing links among fragmented information scattered across multiple files. This study introduces an advanced information integration methodology, comprising a multi-level path-based architecture and a self-updating algorithm. The proposed method not only furnishes safety assessors with pertinent knowledge featuring explicative interconnectedness automatically, but also dynamically enriches this knowledge corpus through operational usage. Additionally, we devise a suite of evaluative criteria to validate the capacity of our method in processing and consolidating relevant safety datasets. Experimental analyses affirm the efficacy of our proposed approach in streamlining and refreshing safety assessment data. The automation of the retrieval of analogous cases, which relieves the reliance on expert knowledge, enhances the efficiency of the overall safety appraisal procedure. Consequently, this research contributes a solution to enhancing the velocity and accuracy of aircraft certification processes.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":null,"pages":null},"PeriodicalIF":2.6,"publicationDate":"2024-06-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141380131","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

RETRACTED: Eapen et al. A 6U CubeSat Platform for Low Earth Remote Sensing: DEWASAT-2 Mission Concept and Analysis. Aerospace 2023, 10, 815 RETRACTED：Eapen et al. A 6U CubeSat Platform for Low Earth Remote Sensing：DEWASAT-2 任务概念与分析。Aerospace 2023, 10, 815

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-06-05 DOI: 10.3390/aerospace11060454

Ann Mary Eapen, S. Bendoukha, Reem Al-Ali, Abdulrahman Sulaiman

引用次数: 0

Ice Object Exclusion Characteristics of Turboshaft Engine Inlet under Helicopter/Inlet Integration Conditions 直升机/进气口一体化条件下涡轮轴发动机进气口的冰物排除特性

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-06-05 DOI: 10.3390/aerospace11060458

Ge Zhou, Haoyu Zhou, Zhenlong Wu, Huijun Tan, Wanglong Qin

{"title":"Ice Object Exclusion Characteristics of Turboshaft Engine Inlet under Helicopter/Inlet Integration Conditions","authors":"Ge Zhou, Haoyu Zhou, Zhenlong Wu, Huijun Tan, Wanglong Qin","doi":"10.3390/aerospace11060458","DOIUrl":"https://doi.org/10.3390/aerospace11060458","url":null,"abstract":"In this study, the influence laws of different parameters on the exclusion characteristics of hailstone and ice flake, and on the aerodynamic performance of the inlet are studied by numerical method. The motion of the hailstone and ice flake is simulated using the 6-DOF method. Results show that the inhalation of hailstone in the inlet decreases total pressure distortion by about 20%, and the total pressure recovery coefficient is essentially unchanged. Icing of the upper lip decreases the total pressure distortion of the inlet by about 22%, and the total pressure recovery coefficient decreases by 0.6%. The ice flakes on the inner and outer lip, when shed and brake by collision with the center body, will cause damage to the engine duct. The shedding and breaking of ice flake at an angle of 150° to the lip can result in a large amount of ice flake debris entering the engine duct, threatening the performance and structure of the engine in the rear. The motion characteristics of hailstone and ice flake under helicopter fuselage/rotor/inlet integration conditions are revealed. It also provides a reference on the numerical methods for the numerical study of hailstone/ice flake exclusion characteristics of helicopter fuselage/rotor/inlet integration conditions.","PeriodicalId":48525,"journal":{"name":"Aerospace","volume":null,"pages":null},"PeriodicalIF":2.6,"publicationDate":"2024-06-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"141383488","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

Detection of Precursors of Thermoacoustic Instability in a Swirled Combustor Using Chaotic Analysis and Deep Learning Models 利用混沌分析和深度学习模型检测漩涡式燃烧器中的热声不稳定性前兆

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-06-05 DOI: 10.3390/aerospace11060455

Boqi Xu, Zhiyu Wang, Hongwu Zhou, Wei Cao, Zhan Zhong, Weidong Huang, Wansheng Nie

引用次数: 0

Robust Optimization Model of Airport Group Coordinated Timetable with Uncertain Flight Time 航班时刻不确定情况下机场群协调时刻表的稳健优化模型

IF 2.6 3区工程技术

Aerospace Pub Date : 2024-06-05 DOI: 10.3390/aerospace11060457

Jianzhong Yan, Minghua Hu

引用次数: 0