Fatigue of Aircraft Structures最新文献_第5页

Breaking the Testing Pyramid with Virtual Testing and Hybrid Simulation 用虚拟测试和混合仿真打破测试金字塔

Fatigue of Aircraft Structures Pub Date : 2019-12-01 DOI: 10.2478/fas-2019-0001

S. You, X. Shawn Gao, A. Nelson

{"title":"Breaking the Testing Pyramid with Virtual Testing and Hybrid Simulation","authors":"S. You, X. Shawn Gao, A. Nelson","doi":"10.2478/fas-2019-0001","DOIUrl":"https://doi.org/10.2478/fas-2019-0001","url":null,"abstract":"Abstract Virtual testing and hybrid simulation have become an important trend in airplane design and validation. The traditional Testing Pyramid (or Building Block) approaches that emphasis on uniaxial coupon test and full structure certification test are being challenged. Researchers are trying to use advanced testing and simulation methods to replace the Testing Pyramid approach. Before physical testing, virtual testing can be conducted to simulate the physical test. Virtual model of the full testing system including controller, actuators, and fixtures can be constructed and validated. In this work, an example has been developed and validated to show the potentials of the virtual testing process. Hybrid simulation is an approach of analyzing an analysis model and physical structure integrated system under realistic loading conditions. Hybrid simulation combines the lab testing with numerical analysis to explore the benefits of both methodologies. In this study, a hybrid simulation for a simplified airplane wing was conducted to demonstrate the process. Virtual testing and hybrid simulation are alternative methods of Testing Pyramid approach. Full scale tests are still required for certification but the more that is known about the test article, the greater chances of success in the full-scale certification testing.","PeriodicalId":37629,"journal":{"name":"Fatigue of Aircraft Structures","volume":"2019 1","pages":"1 - 10"},"PeriodicalIF":0.0,"publicationDate":"2019-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49354673","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: 4

Comparative Study on Fatigue Life of CFRP Composites with Damages CFRP复合材料损伤后疲劳寿命的比较研究

Fatigue of Aircraft Structures Pub Date : 2019-12-01 DOI: 10.2478/fas-2019-0004

Marta Baran, P. Synaszko, J. Lisiecki, S. Kłysz

{"title":"Comparative Study on Fatigue Life of CFRP Composites with Damages","authors":"Marta Baran, P. Synaszko, J. Lisiecki, S. Kłysz","doi":"10.2478/fas-2019-0004","DOIUrl":"https://doi.org/10.2478/fas-2019-0004","url":null,"abstract":"Abstract In this work, the compressive residual strength tests results, Compression After Impact (CAI), are presented. The specimens were made of carbon-epoxy prepreg E722-02 UHS 130-14. Two variants of specimens were tested: samples undamaged and samples with damage that was centrally introduced by a drop-weight impact, as per the ASTM D7136/7136M standard. An impactor with potential energy equal to 15J and the type of support required by the standard were used. The size of impacted damages, defined as an area of damage on a plane perpendicular to the impact direction, and the equivalent diameter were specified using the flash thermography method. The tests were performed using the fixtures manufactured according to the ASTM D7137/7137M standard. The specimens were compressed to determine the residual strength. This value was afterwards used to specify the force levels for the fatigue tests. The fatigue tests were carried out under force control – with a sinusoidal shape, stress ratio R equal to 0.1 and frequency f 1Hz. Maximum force in a loading cycle Pmax was being increased after each thousand of cycles N until its value was close to the residual strength determined in the previously mentioned tests. In this work, the following relationships were presented: force-displacement P-δ for both static and fatigue tests and displacement-loading cycles δ-N for fatigue tests. A method of conducting the fatigue tests of CFRP composite was proposed, in which both the CAI specimens and CAI fixture were used. This allowed researchers to accelerate making initial comparisons between the two groups of specimens with damages – grouped relative to the way of conditioning.","PeriodicalId":37629,"journal":{"name":"Fatigue of Aircraft Structures","volume":"2019 1","pages":"28 - 38"},"PeriodicalIF":0.0,"publicationDate":"2019-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48841209","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

Aircraft Corrosion – Review of Corrosion Processes and its Effects in Selected Cases 飞机腐蚀——腐蚀过程及其在选定情况下的影响综述

Fatigue of Aircraft Structures Pub Date : 2018-12-01 DOI: 10.2478/fas-2018-0001

Magdalena Czaban

引用次数: 23

Verification of the Computed Tomography Results of Aluminum Alloy Welded Joint 铝合金焊接接头计算机断层扫描结果的验证

Fatigue of Aircraft Structures Pub Date : 2018-12-01 DOI: 10.2478/fas-2018-0004

Maciej Malicki, K. Sobczak

引用次数: 2

Accumulation of Fatigue Microdefects– Entropy Interpretation 疲劳微缺陷的累积-熵解释

Fatigue of Aircraft Structures Pub Date : 2018-12-01 DOI: 10.2478/fas-2018-0010

K. Szafran, N. Delas

引用次数: 2

Fatigue Degradation of the Structure of Parachute Systems 降落伞系统结构的疲劳退化

Fatigue of Aircraft Structures Pub Date : 2018-12-01 DOI: 10.2478/fas-2018-0009

K. Szafran, Ireneusz Kramarski

引用次数: 5

Evaluation of Impact Damage in Composite Structures Using Ultrasonic Testing 复合材料结构冲击损伤的超声检测评价

Fatigue of Aircraft Structures Pub Date : 2018-12-01 DOI: 10.2478/fas-2018-0008

Angelika Wronkowicz-Katunin, K. Dragan

引用次数: 2

Influence of the Fatigue Load Level and the Hole Diameter on the Laminate Structure’s Fatigue Performance 疲劳载荷水平和孔直径对层压结构疲劳性能的影响

Fatigue of Aircraft Structures Pub Date : 2018-12-01 DOI: 10.2478/fas-2018-0002

M. Zalewska

{"title":"Influence of the Fatigue Load Level and the Hole Diameter on the Laminate Structure’s Fatigue Performance","authors":"M. Zalewska","doi":"10.2478/fas-2018-0002","DOIUrl":"https://doi.org/10.2478/fas-2018-0002","url":null,"abstract":"Abstract Damage tolerance of composite aircraft structure is one of the main areas of research, important when a new product is being developed. There are a number of variables, such as damage characteristics (dent depth, delamination area) and loading parameters (load type, amplitude of cyclic loading, load sequence) that need to be investigated experimentally [1]. These tests of composite materials are usually performed at an element level and are carried out in order to validate the analytical model, developed to predict the full-scale component’s behaviour. The paper presents the results of compression testing of the [36/55/9] carbon fibre/epoxy laminate, manufactured with the Automated Fibre Placement technology (AFP) and subjected to static and fatigue loads. The laminate compression loading mode was achieved through sandwich 4-point flexure. At the stage of fatigue testing, two parameters were investigated: the damage size, simulated by the hole diameter and the fatigue load level. Based on the test results, the laminate fatigue load limit equal to 75% of the OHC failure load was evaluated. By collating the static and fatigue tests results, the damage tolerance characteristic of the considered laminate was created.","PeriodicalId":37629,"journal":{"name":"Fatigue of Aircraft Structures","volume":"2018 1","pages":"21 - 30"},"PeriodicalIF":0.0,"publicationDate":"2018-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44271538","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 Brief Review on NDT&E Methods For Structural Aircraft Components 飞机结构件无损检测与测试方法综述

Fatigue of Aircraft Structures Pub Date : 2018-12-01 DOI: 10.2478/fas-2018-0007

Angelika Wronkowicz-Katunin

引用次数: 9

The Hardening in Alloys and Composites and Its Examination with a Diffraction and Self-Consistent Model 合金和复合材料的硬化及其衍射和自洽模型检验

Fatigue of Aircraft Structures Pub Date : 2018-12-01 DOI: 10.2478/fas-2018-0003

Elżbieta Gadalińska, A. Baczmaňski, S. Wronski, M. Wróbel, Christian Scheffzük

引用次数: 0