2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE)最新文献_第5页

CFD Based Stochastic Optimization of Pelton Turbine Bucket in Stationery Condition 基于CFD的水轮机筒体静止状态随机优化

2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2018-07-01 DOI: 10.1109/ICMAE.2018.8467607

Suyesh Bhattarai, K. Dahal, P. Vichare, B. Mishra

引用次数: 7

Modal Analysis as a Tool of Problem Identification of Gear Mechanism 作为齿轮机构问题识别工具的模态分析

2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2018-07-01 DOI: 10.1109/ICMAE.2018.8467632

K. Monkova, P. Monka, M. Ungureanu, N. Ungureanu

{"title":"Modal Analysis as a Tool of Problem Identification of Gear Mechanism","authors":"K. Monkova, P. Monka, M. Ungureanu, N. Ungureanu","doi":"10.1109/ICMAE.2018.8467632","DOIUrl":"https://doi.org/10.1109/ICMAE.2018.8467632","url":null,"abstract":"The paper deals with modal analysis as a tool of problem identification of gear mechanism. The gear mechanism has been newly designed based on new principle, at which the motion and power are transferred from one input shaft to two output shafts in one direction. The noise emission measurements showed a problem with resonance at specific input shaft speeds that was necessary to solve. At the first step, the excitation frequencies have been computed to be possible to compare them with natural frequencies determined by modal analysis. I has been found out that the problem part was a toothed flange that is a part of gear-box. The paper aimed to create experimental and computational model of the toothed flange with subsequent verification of selected theories, to compare results obtained by numerical and experimental modal analysis and to assess the dynamic characteristics of the component with respect to its operating conditions. There are described conditions of both numerical and experimental modal analysis in the paper. The measurements have shown that the values of natural frequencies along with the natural shapes are adequate and comparable within the both investigation methods. Moreover, based on results, the shape of flange has been modified so to be the noise emission appropriate and the gear works properly.","PeriodicalId":118501,"journal":{"name":"2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"105 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124049319","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}

引用次数: 1

Uncertainty Quantification of k-ω Turbulence Model for Hypersonic Flow 高超声速k-ω湍流模型的不确定性量化

2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2018-07-01 DOI: 10.1109/ICMAE.2018.8467619

Yatian Zhao, Hongkang Liu, Chao Yan

引用次数: 1

Reconfiguring NASA Generic Transport Model for Normal Flight Envelope Simulation and Analysis 重新配置NASA通用运输模型用于正常飞行包线模拟和分析

2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2018-07-01 DOI: 10.1109/ICMAE.2018.8467651

R. Norouzi

{"title":"Reconfiguring NASA Generic Transport Model for Normal Flight Envelope Simulation and Analysis","authors":"R. Norouzi","doi":"10.1109/ICMAE.2018.8467651","DOIUrl":"https://doi.org/10.1109/ICMAE.2018.8467651","url":null,"abstract":"NASA Generic Transport Model (GTM) is a subscale airplane developed within the NASA Aviation Safety Program’s Integrated Resilient Aircraft Control Project with the aim of studying critical flight conditions outside the normal flight envelope without taking the risks of full-scale manned aircraft flight tests. Extensive wind tunnel tests were carried out on the model at the NASA Langley center to create extended flight envelope dataset. As part of the NASA project, a nonlinear high fidelity simulated model of GTM was developed in MATLAB® and Simulink® environment which utilizes the extensive wind tunnel test data in tabular form as the required aerodynamic database. The Simulink model is very useful in studies which require a valid high fidelity nonlinear model; however there are asymmetries in the model configuration and aerodynamic database which result in considerable amount of error if the model is used for normal flight envelope simulation and analysis. In this paper, the sources of the model asymmetry are explained and the model is reconfigured such that it can be correctly used for normal flight envelope studies. A number of simulations are provided which verify the model reconfiguration.","PeriodicalId":118501,"journal":{"name":"2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129389373","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}

引用次数: 2

Turbo Engine Starting Control Law Design and Process Simulation 涡轮发动机起动控制规律设计与过程仿真

2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2018-07-01 DOI: 10.1109/ICMAE.2018.8467712

Tian Tan, Yu-chun Chen, Xin-yue Ma, Chao Zhou

引用次数: 3

RF Source Localization using Unmanned Aerial Vehicle with Particle Filter 基于粒子滤波的无人机射频源定位

2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2018-07-01 DOI: 10.1109/ICMAE.2018.8467555

M. Hasanzade, Ömer Herekoğlu, R. Yeniceri, E. Koyuncu, G. Inalhan

引用次数: 10

Research on Reverse Design of Turboshaft Engine Based on the Balance of Difficulty Factor 基于难度系数平衡的涡轮轴发动机反设计研究

2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2018-07-01 DOI: 10.1109/ICMAE.2018.8467673

Zhang Shao-feng, Cheng Yu-chun

引用次数: 0

Transition Flight Control and Test of a New Kind Tilt Prop Box-Wing VTOL UAV 一种新型倾斜支撑箱翼垂直起降无人机的过渡飞行控制与试验

2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2018-07-01 DOI: 10.1109/ICMAE.2018.8467657

Deng Yangping, Gao Honggang

引用次数: 2

Research on Aeroheating of Complicated Hypersonic Reentry Vehicles 复杂高超声速再入飞行器气动加热研究

2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2018-07-01 DOI: 10.1109/ICMAE.2018.8467602

Qin Xuguo, Shui Yongtao, Wang Yonghai, Wang Fei, Li Qiang

引用次数: 1

A Practical Method for Redesigning Statistical Tolerances Using Monte Carlo Simulation 用蒙特卡罗模拟重新设计统计公差的实用方法

2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE) Pub Date : 2018-07-01 DOI: 10.1109/ICMAE.2018.8467654

Heping Peng, Zhuoqun Peng

{"title":"A Practical Method for Redesigning Statistical Tolerances Using Monte Carlo Simulation","authors":"Heping Peng, Zhuoqun Peng","doi":"10.1109/ICMAE.2018.8467654","DOIUrl":"https://doi.org/10.1109/ICMAE.2018.8467654","url":null,"abstract":"This paper presents a practical method for redesigning statistical tolerances by combining the unified Jacobian-Torsor model and Monte Carlo simulation. After having identified the assembly functional requirement (FR) and determined the functional elements (FEs) encountered in tolerance chain, the specific expression of Jacobian-Torsor model can be obtained. Monte Carlo simulation is employed to repeatedly evaluate the model using sets of random values as inputs to make this deterministic model become a statistical model. Once the real multiplication operations have been performed on this model, we can get large amount of simulated data, from which we can obtain the statistical limits of the assembly FR in the desired direction. The percentage contribution of each FE to the total FR can help the designer redesign the tolerances of the critical FEs to respect the specified FR. This redesign process may need to be repeated several times until the calculated FR is consistent with the specified FR, so the tolerance values that need to be determined are obtained, and the redesign of statistical tolerances is achieved. The effectiveness of the proposed method is illustrated by taking the crank-connecting rod mechanism of piston aeroengine assembly as an example.","PeriodicalId":118501,"journal":{"name":"2018 9th International Conference on Mechanical and Aerospace Engineering (ICMAE)","volume":"61 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2018-07-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124401784","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}

引用次数: 1