Volume 1: Advances in Aerospace Technology最新文献_第2页

Optimization of 3D Printed Elastomeric Nanocomposites for Flexible Strain Sensing Applications 用于柔性应变传感应用的3D打印弹性纳米复合材料的优化

Volume 1: Advances in Aerospace Technology Pub Date : 2019-11-11 DOI: 10.1115/imece2019-11467

M. Abshirini, Mohammad Charara, M. Saha, M. Altan, Yingtao Liu

{"title":"Optimization of 3D Printed Elastomeric Nanocomposites for Flexible Strain Sensing Applications","authors":"M. Abshirini, Mohammad Charara, M. Saha, M. Altan, Yingtao Liu","doi":"10.1115/imece2019-11467","DOIUrl":"https://doi.org/10.1115/imece2019-11467","url":null,"abstract":"\u0000 Flexible and sensitive strain sensors can be utilized as wearable sensors and electronic devices in a wide range of applications, such as personal health monitoring, sports performance, and electronic skin. This paper presents the fabrication of a highly flexible and sensitive strain sensor by 3D printing an electrically conductive polydimethylsiloxane (PDMS)/multi-wall carbon nanotube (MWNT) nanocomposite on a PDMS substrate. To maximize the sensor’s gauge factor, the effects of MWNT concentration on the strain sensing function in nanocomposites are evaluated. Critical 3D printing and curing parameters, such as 3D printing nozzle diameter and nanocomposites curing temperature, are explored to achieve the highest piezoresistive response, showing that utilizing a smaller deposition nozzle size and higher curing temperature can result in a higher gauge factor. The optimized 3D printed nanocomposite sensor’s sensitivity is characterized under cyclic tensile loads at different maximum strains and loading rates. A linear piezoresistive response is observed up to 70% strain with an average gauge factor of 12, pointing to the sensor’s potential as a flexible strain sensor. In addition, the sensing function is almost independent of the applied load rate. The fabricated sensors are attached to a glove and used as a wearable sensor by detecting human finger and wrist motion. The results indicate that this 3D printed functional nanocomposite shows promise in a broad range of applications, including wearable and skin mounted sensors.","PeriodicalId":119220,"journal":{"name":"Volume 1: Advances in Aerospace Technology","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-11-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126473903","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

Aeroelastic Modeling and Analysis of High Aspect Ratio Wings With Different Fidelity Structural Models 不同保真度结构模型大展弦比机翼气动弹性建模与分析

Volume 1: Advances in Aerospace Technology Pub Date : 2019-11-11 DOI: 10.1115/imece2019-11483

Gökçen Çiçek, A. Kayran

{"title":"Aeroelastic Modeling and Analysis of High Aspect Ratio Wings With Different Fidelity Structural Models","authors":"Gökçen Çiçek, A. Kayran","doi":"10.1115/imece2019-11483","DOIUrl":"https://doi.org/10.1115/imece2019-11483","url":null,"abstract":"\u0000 This paper is concerned with the aeroelastic modeling and analysis of high aspect ratio wings with large torsional deflections with different fidelity structural models.\u0000 The approach for structural modeling presented here is based on linear and nonlinear theories. The linear theories are based on the slender-straight wing and bending-torsion beam finite element formulations. The nonlinear theory is based on the nonlinear finite element model with only a torsional rotation degree of freedom to study the static aeroelastic behavior. The aerodynamic theory used for aeroelastic coupling is ESDU 95010 [1], which uses steady lifting-surface theory based on Multhopp-Richardson’s solution to provide the spanwise loading of lifting surfaces with camber and twist.\u0000 Analyses are performed with three different structural models coupled with ESDU for simple plate-like wing models.\u0000 The results of linear structural models are verified with MSC NASTRAN® and the nonlinear structural model results are verified with the work of Trahair [2]. Linear aeroelastic models are compared with the MSC NASTRAN® solution performed by SOL144. Significant differences in torsional deflection of tip location are observed between the linear and the nonlinear solution methodologies. The linear theory is found to be conservative for the aeroelastic analysis of high aspect ratio wings.","PeriodicalId":119220,"journal":{"name":"Volume 1: Advances in Aerospace Technology","volume":"123 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-11-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131696321","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: 0

A Semi-Empirical Approach to Determine Dynamic Stability of In-Flight Morphing Platforms 一种确定飞行变形平台动态稳定性的半经验方法

Volume 1: Advances in Aerospace Technology Pub Date : 2019-11-11 DOI: 10.1115/imece2019-10274

T. Marchelli, N. Sarigul-Klijn

引用次数: 0

Large-Deformation Analysis of Elastomeric Structures by Carrera Unified Formulation 基于Carrera统一公式的弹性结构大变形分析

Volume 1: Advances in Aerospace Technology Pub Date : 2019-11-11 DOI: 10.1115/imece2019-11364

E. Carrera, A. Pagani, Bin Wu, M. Filippi

{"title":"Large-Deformation Analysis of Elastomeric Structures by Carrera Unified Formulation","authors":"E. Carrera, A. Pagani, Bin Wu, M. Filippi","doi":"10.1115/imece2019-11364","DOIUrl":"https://doi.org/10.1115/imece2019-11364","url":null,"abstract":"Based on the well-known nonlinear hyperelasticity theory and by using the Carrera Unified Formulation (CUF) as well as a total Lagrangian approach, the unified theory of slightly compressible elastomeric structures including geometrical and physical nonlinearities is developed in this work. By exploiting CUF, the principle of virtual work and a finite element approximation, nonlinear governing equations corresponding to the slightly compressible elastomeric structures are straightforwardly formulated in terms of the fundamental nuclei, which are independent of the theory approximation order. Accordingly, the explicit forms of the secant and tangent stiffness matrices of the unified 1D beam and 2D plate elements are derived by using the three-dimensional Cauchy-Green deformation tensor and the nonlinear constitutive equation for slightly incompressible hyperelastic materials. Several numerical assessments are conducted, including uniaxial tension nonlinear response of rectangular elastomeric beams. Our numerical findings demonstrate the capabilities of the CUF model to calculate the large-deformation equilibrium curves as well as the stress distributions with high accuracy.","PeriodicalId":119220,"journal":{"name":"Volume 1: Advances in Aerospace Technology","volume":"63 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-11-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122308950","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

Comparative Structural Optimization Study of Composite and Aluminum Horizontal Tail Plane of a Helicopter 直升机复合材料与铝制水平尾翼结构优化对比研究

Volume 1: Advances in Aerospace Technology Pub Date : 2019-11-11 DOI: 10.1115/imece2019-11153

Bertan Arpacioglu, A. Kayran

{"title":"Comparative Structural Optimization Study of Composite and Aluminum Horizontal Tail Plane of a Helicopter","authors":"Bertan Arpacioglu, A. Kayran","doi":"10.1115/imece2019-11153","DOIUrl":"https://doi.org/10.1115/imece2019-11153","url":null,"abstract":"\u0000 This work presents structural optimization studies of aluminum and composite material horizontal tail plane of a helicopter by using MSC. NASTRAN SOL200 optimization capabilities. Structural design process starts from conceptual design phase, and structural layout design is performed by using CATIA. In the preliminary design phase, study focuses on the minimum weight optimization with multiple design variables and similar constraints for both materials. Aerodynamic load calculation is performed using ANSYS and the finite element model of the horizontal tail plane is created by using MSC.PATRAN. According to the characteristics of materials, design variables are chosen. For the aluminum horizontal tail, thickness and flange areas are used as the design variables; and for composite horizontal tail, attention is mainly focused on the ply numbers and ply orientation angles of the laminated composite panels. By considering the manufacturability issues, discrete design variables are used. For three different mesh densities, different initial values of the design variables, and similar design constraints, optimizations are repeated and the results of optimizations are examined and compared with each other. In the optimizations performed, constraints are taken as strength and local buckling constraints. It is shown that the optimization methodology used in this study gives confident results for optimizing structures in the preliminary design phase.","PeriodicalId":119220,"journal":{"name":"Volume 1: Advances in Aerospace Technology","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-11-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125898038","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: 0

An Inertial / Altimetric / Infrared / Geomagnetic Integrated Navigation Method for Unmanned Aerial Vehicles 无人机惯性/高程/红外/地磁组合导航方法

Volume 1: Advances in Aerospace Technology Pub Date : 2019-11-11 DOI: 10.1115/imece2019-10948

Zilu He, X. Bu, Yihan Cao, Miaomiao Xu

{"title":"An Inertial / Altimetric / Infrared / Geomagnetic Integrated Navigation Method for Unmanned Aerial Vehicles","authors":"Zilu He, X. Bu, Yihan Cao, Miaomiao Xu","doi":"10.1115/imece2019-10948","DOIUrl":"https://doi.org/10.1115/imece2019-10948","url":null,"abstract":"\u0000 Unmanned aerial vehicle (UAV), is an unmanned aircraft operated by radio remote control equipment and self-contained program control device. When Unmanned Aerial Vehicle is on mission, its location information needs to be acquired to navigate it. Based on the research background of Unmanned Aerial Vehicle navigation information measurement, a passive integrated navigation mode of Inertial / Altimeter / Infrared / Geomagnetism Navigation method is designed in this paper. Firstly, several methods for Unmanned Aerial Vehicle navigation, including geomagnetic navigation, infrared navigation, inertial navigation and altimeter measurement, are introduced, and the advantages and disadvantages of various navigation methods are presented. Secondly, aiming at the problem that the output of barometric altimeter is affected by temperature and pressure, a temperature and pressure compensation model of barometric altimeter is established. Then, the attitude angle, velocity and position measurement models of inertial, infrared and geomagnetic navigation are established respectively. Finally, the data information of inertial / altimeter / infrared / geomagnetism measurement model is fused by extended Kalman filter and Unscented Kalman filter, and the signals processed by the two filters are compared. The reliability of the integrated navigation method is verified by simulation. This method has remarkable effect on improving the navigation accuracy of UAV and can make UAV suitable for many applications. It is simple and effective, and has wide application prospects.","PeriodicalId":119220,"journal":{"name":"Volume 1: Advances in Aerospace Technology","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-11-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127971194","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: 0

On the Role of Segmentation in the Analysis of Micro-CT Data of Impact Damage in the CFRP Composites 分割在CFRP复合材料冲击损伤微ct数据分析中的作用

Volume 1: Advances in Aerospace Technology Pub Date : 2019-11-11 DOI: 10.1115/imece2019-11037

O. Zhupanska

引用次数: 0

Cure Monitoring of Adhesive for Composite/Metal Bonded Structure Based on Highly Nonlinear Solitary Waves 基于高度非线性孤立波的复合材料/金属粘结结构胶粘剂固化监测

Volume 1: Advances in Aerospace Technology Pub Date : 2019-11-11 DOI: 10.1115/imece2019-10717

Wu Bin, Li Mingzhi, Liu Xiucheng, Wang Heying, He Cunfu, Liu Zongfa

{"title":"Cure Monitoring of Adhesive for Composite/Metal Bonded Structure Based on Highly Nonlinear Solitary Waves","authors":"Wu Bin, Li Mingzhi, Liu Xiucheng, Wang Heying, He Cunfu, Liu Zongfa","doi":"10.1115/imece2019-10717","DOIUrl":"https://doi.org/10.1115/imece2019-10717","url":null,"abstract":"\u0000 In this paper, a nondestructive evaluation technique based on highly nonlinear solitary waves (HNSWs) is proposed to monitor the curing process of adhesive for composite/metal bonded structure. HNSWs are mechanical waves with high energy intensity and non-distortive nature which can form and propagate in a nonlinear system, such as a one-dimensional granular chain. In the present study, a finite element model of the one-dimensional granular chain is established with the commercial software Abaqus, to study the reflection behavior of HNSWs at the interface between the particle at the end of chain and the sample. The simulation results show that the time of flight (TOF) of the primary reflected solitary wave decreases with the stiffness of the sample increases, and the amplitude ratio (AR) between the primary reflected solitary wave and the incident solitary wave increases. An HNSWs transducer based on the one-dimensional granular chain is designed and fabricated. The relationship between the characteristic parameters of the primary reflected solitary wave (TOF and AR) and the curing time of adhesive for a composite/metal bonded structure is experimentally investigated. The experiment results suggest that the TOF decreases and the AR increases as the epoxy cures. The experimental results are in good agreement with the simulation results. This study provides a new characterization method for monitoring the curing process of adhesive for composite/metal bonded structure.","PeriodicalId":119220,"journal":{"name":"Volume 1: Advances in Aerospace Technology","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2019-11-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131102406","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: 0

Influence of Fuel on a Valveless Pulsejet Engine Performance and Pollutant Emissions 燃油对无气门脉冲喷气发动机性能及污染物排放的影响

Volume 1: Advances in Aerospace Technology Pub Date : 2019-11-11 DOI: 10.1115/imece2019-11229

A. Melo, F. Brójo

引用次数: 0

Low-Cost Particulate Detection in Bleed Air 低成本的引气颗粒物检测

Volume 1: Advances in Aerospace Technology Pub Date : 2019-11-11 DOI: 10.1115/imece2019-10460

Mir Seliman Waez, S. Eckels, C. Sorensen

引用次数: 0