Chinese Journal of Aeronautics最新文献

{"title":"An interlaminar damage shell model for typical composite structures","authors":"Jie ZHOU ,&nbsp;Zhen WU ,&nbsp;Zhengliang LIU ,&nbsp;Xiaohui REN","doi":"10.1016/j.cja.2023.05.027","DOIUrl":"10.1016/j.cja.2023.05.027","url":null,"abstract":"<div><p>Using the plate/shell elements in commercial software, accurate analysis of interlaminar initial damage in typical composite structures is still a challenging issue. To propose an accurate and efficient model for analysis of interlaminar initial damage, the following work is carried out: (A) A higher-order theory is firstly proposed by introducing the local Legendre polynomials, and then a novel shell element containing initial damage prediction is developed, which can directly predict transverse shear stresses without any postprocessing methods. Unknown variables at each node are independent of number of layers, so the proposed model is more efficient than the 3D-FEM. (B) Compression experiment is carried out to verify the capability of the proposed model. The results obtained from the proposed model are in good agreement with experimental data. (C) Several examples have been analyzed to further assess the capability of the proposed model by comparing to the 3D-FEM results. Moreover, accuracy and efficiency have been evaluated in different damage criterion by comparing with the selected models. The numerical results show that the proposed model can well predict the initial interlaminar damage as well as other damage. Finally, the model is implemented with UEL subroutine, so that the present approach can be readily utilized to analyze the initial damage in typical composite structures.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 1","pages":"Pages 118-137"},"PeriodicalIF":5.7,"publicationDate":"2024-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S100093612300184X/pdfft?md5=06ae8c2e29293e7bcb8bae017623b0d5&pid=1-s2.0-S100093612300184X-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42303465","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"PPB structure elimination, DRX nucleation mechanisms and grain growth behavior of the 3rd-generation PM superalloy for manufacturing aviation components","authors":"Baoyun ZHANG ,&nbsp;Yongquan NING ,&nbsp;Zhaotian WANG ,&nbsp;Qiaomu LIU","doi":"10.1016/j.cja.2023.10.016","DOIUrl":"10.1016/j.cja.2023.10.016","url":null,"abstract":"<div><p>Previous Particle Boundary (PPB), as the detrimental structure in Powder Metallurgy (PM) components, should be eliminated by subsequent hot process to improve the mechanical properties. The objective is to investigate the Dynamic Recrystallization (DRX) nucleation mechanisms and grain growth behavior of the 3rd-generation PM superalloy with PPB structure. Microstructure observation reveals that PPB decorated with (Ti, Ta, Nb)C carbides belongs to the discontinuous chain-like structure. The elimination of PPB networks can be achieved effectively via hot deformation due to the occurrence of DRX. Four different DRX nucleation mechanisms were proposed and discussed in detail according to the special microstructure characteristics of the PM superalloy. Firstly, local lattice rotations can be detected in the vicinity of (Ti, Ta, Nb)C carbides during hot deformation and thus PPB structure serves as the preferential nucleation sites for DRX grains via Particle-Stimulated Nucleation (PSN). Then, Discontinuous-DRX (DDRX) characterized by grain boundary bulging dominates the microstructure refinement and Continuous-DRX (CDRX) operated by subgrain rotation can be regarded as an important assistant mechanism. At last, the initial Σ3 boundaries would lose their twin characteristics owing to the crystal rotation and then transform into the general High Angle Grain Boundaries (HAGBs). The distorted twins provide additional DRX nucleation sites, viz., twin-assisted nucleation. Particular attention was focused on the grain growth behavior of the PM superalloy in subsequent annealing process. The recrystallization temperature was determined to be about 1110 °C and 1140 °C can be considered as the critical temperature for grain growth. The findings would provide theoretical support for microstructure refinement of the 3rd-generation PM superalloy, which is of pivotal significance for improving the mechanical properties of aviation components.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 1","pages":"Pages 325-344"},"PeriodicalIF":5.7,"publicationDate":"2024-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003655/pdfft?md5=e6a7cec7247bd671d8bf38913a7484d6&pid=1-s2.0-S1000936123003655-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136059875","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"A novel seal-flow multi-vortex friction stir lap welding of metal to polymer matrix composites","authors":"Shuaiqiang NIAN ,&nbsp;Mingshen LI ,&nbsp;Shude JI ,&nbsp;Wei HU ,&nbsp;Zhiqing ZHANG ,&nbsp;Zelin SUN","doi":"10.1016/j.cja.2023.04.009","DOIUrl":"10.1016/j.cja.2023.04.009","url":null,"abstract":"<div><p>The friction stir lap welding (FSLW) of metal to polymer is a challenging work due to the unavoidable polymer overflowing. Facing this problem, a novel seal-flow multi-vortex friction stir lap welding (SM-FSLW) technology based on the subversively-designed multi-step pin was put forward. Choosing 7075 aluminum alloy and short glass fiber-reinforced polyether ether ketone (PEEK) as research subjects, the welding temperature, material flow, formation and tensile shear strength of dissimilar materials lap joint under the SM-FSLW were studied and compared with those under traditional FSLW based on the conical pin. The multi-step pin rather than the conical pin effectively hindered the polymer overflowing due to the formation of vortexes by the step, thereby attaining a joint with a smooth surface. Compared with traditional FSLW, the SM-FSLW obtained the higher welding temperature, the more violent material flow and the larger area with high flow velocity, thereby producing the macro-mechanical and micro-mechanical interlockings and then heightening the joint loading capacity. The tensile shear strength of lap joint under SM-FSLW was 27.8% higher than that under traditional FSLW. The SM-FSLW technology using the multi-step pin provides an effective way on obtaining a heterogeneous lap joint of metal to polymer with the excellent formation and high strength.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 1","pages":"Pages 451-462"},"PeriodicalIF":5.7,"publicationDate":"2024-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123001243/pdfft?md5=ff30d540ebaf0a69d7e2b3641f52223b&pid=1-s2.0-S1000936123001243-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47601213","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Laser-assisted grinding of RB-SiC composites: Laser ablation behavior and mechanism","authors":"Zhigang DONG,&nbsp;Wenchao SUN,&nbsp;Xintong CAI,&nbsp;Feng YANG,&nbsp;Yan BAO,&nbsp;Renke KANG,&nbsp;Dongjiang WU,&nbsp;Guangyi MA,&nbsp;Fangyong NIU","doi":"10.1016/j.cja.2023.10.018","DOIUrl":"10.1016/j.cja.2023.10.018","url":null,"abstract":"<div><p>Laser ablation is an important process during Laser-Assisted Grinding (LAG) of hard and brittle materials. To realize controllable material removal during laser ablation of RB-SiC composites, ablation experiments under different Laser Energy Density (LAED) and LAG experiments are conducted. Evolution rules and mechanism of physical phase, ablation morphology and crack characteristics caused by laser irradiation are investigated. The forces of LAG and Conventional Grinding (CG) are compared. The results show that ablation surface changes from slight oxidation to obvious material removal with LAED increasing, and ablation depth increases gradually. The ablation products change from submicron SiO₂ particles to nanoscale particles and floccule. High LAED promotes SiC decomposition and sublimation, which leads to the increase of C element. The SiC phase forms corrugated shape in recast layer and columnar shape in Heat Affected Zone (HAZ) at 56 J/mm². The cold and heat cycle leads to formation of fishbone crack. For ablation specimen under 30 J/mm², the grinding force can be reduced by a maximum of 39% and brittle damage region is reduced. The material removal and microcrack generated will significantly reduce the hardness and improve machinability, which can promote grinding efficiency.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 1","pages":"Pages 362-376"},"PeriodicalIF":5.7,"publicationDate":"2024-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003679/pdfft?md5=a29f9d09a6b4260397453129e97eff39&pid=1-s2.0-S1000936123003679-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136159587","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Improvement of titanium alloy TA19 fatigue life by submerged abrasive waterjet peening: Correlation of its process parameters with surface integrity and fatigue performance","authors":"Gongyu WANG ,&nbsp;Shulei YAO ,&nbsp;Yuxin CHI ,&nbsp;Chengcheng ZHANG ,&nbsp;Ning WANG ,&nbsp;Yalong CHEN ,&nbsp;Rongsheng LU ,&nbsp;Zhuang LI ,&nbsp;Xiancheng ZHANG","doi":"10.1016/j.cja.2023.03.033","DOIUrl":"10.1016/j.cja.2023.03.033","url":null,"abstract":"<div><p>Submerged abrasive waterjet peening (SAWJP) is an effective anti-fatigue manufacturing technology that is widely used to strengthen aeroengine components. This study investigated the correlation of SAWJP process parameters on surface integrity and fatigue life of titanium alloy TA19. SAWJP with different water pressures and standoff distances (SoDs) was conducted on the TA19 specimens. The surface integrity of the specimens before and after SAWJP with different process parameters was experimentally studied, including microstructure, surface roughness, microhardness, and compressive residual stress (CRS). Finally, fatigue tests of the specimens before and after SAWJP treatment with different process parameters were carried out at room temperature. The results highlighted that the fatigue life of the TA19 specimen can be increased by 5.46, 5.98, and 6.28 times under relatively optimal process parameters, which is mainly due to the improved surface integrity of the specimen after SAWJP treatment. However, the fatigue life of specimens treated with improper process parameters is decreased by 0.55 to 0.69 times owing to the terrible surface roughness caused by the material erosion. This work verifies that SAWJP can effectively improve the surface integrity and fatigue life of workpieces, and reveals the relationship between process parameters, surface integrity, and fatigue life, which provides support for the promotion of SAWJP in the manufacturing fields.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 1","pages":"Pages 377-390"},"PeriodicalIF":5.7,"publicationDate":"2024-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123000948/pdfft?md5=53da120a1fcf5aa27b372c624de15821&pid=1-s2.0-S1000936123000948-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"49653310","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"A multi-scale framework for life reduction assessment of turbine blade caused by microstructural degradation","authors":"Xiaoguang YANG ,&nbsp;Menglei WANG ,&nbsp;Duoqi SHI ,&nbsp;Zhenlei LI ,&nbsp;Yongsheng FAN","doi":"10.1016/j.cja.2023.07.021","DOIUrl":"10.1016/j.cja.2023.07.021","url":null,"abstract":"<div><p>The prolonged thermal exposure with centrifugal load results in microstructural degradation, which ultimately leads to a reduction in the fatigue and creep resistance of the turbine blades. The present work proposes a multi-scale framework to estimate the life reduction of turbine blades, which combines a microstructural degradation model, a two-phase constitutive model, and a microstructure-dependent fatigue and creep life reduction model. The framework with multi-scale models is validated by a Single Crystal (SC) Ni-based superalloy at the microstructural length-scale and is then applied to calculate the microstructural degradation and the fatigue and creep life reduction of turbine blades under two specific service conditions. The simulation results and quantitative analysis show that the microstructural degradation and fatigue and creep life reduction of the turbine blade are heavily influenced by the variations in the proportion of the intermediate state, namely, the maximum rotor speed status, in the two specific service conditions. The intermediate state accelerates the microstructural degradation and leads to a reduction of the life, especially the effective fatigue life reserve due to the higher temperature and rotational speed than that of the 93% maximum rotor speed status marked as the reference state. The proposed multi-scale framework provides a capable approach to analyze the reduction of the fatigue and creep life for turbine blade induced by microstructural degradation, which can assist to determine a reasonable Time Between Overhaul (TBO) of the engine.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 1","pages":"Pages 186-200"},"PeriodicalIF":5.7,"publicationDate":"2024-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123002510/pdfft?md5=aa40dcfd58bc5065fc1a3f8044bfffee&pid=1-s2.0-S1000936123002510-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42838395","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Efficient machining of a complex blisk channel using a disc cutter","authors":"Xiangyu LI ,&nbsp;Zhaoyu LI ,&nbsp;Dong HE ,&nbsp;Junxue REN ,&nbsp;Qian FENG ,&nbsp;Kai TANG","doi":"10.1016/j.cja.2023.04.017","DOIUrl":"10.1016/j.cja.2023.04.017","url":null,"abstract":"<div><p>For rough machining of a complex narrow cavity, e.g., a complex blisk channel on an aero-engine, the typically used cutting tools are the slender cylindrical cutter and conical cutter. Nevertheless, as neither of the two is particularly suited for rough machining, wherein the main purpose is to remove a large volume as quickly as possible, the machining efficiency is low, especially when the part materials are of hard-to-cut types (e.g., Titanium-alloy) for which it often takes days to rough machine a blisk. Fortunately, disc machining provides a new and efficient roughing solution, since a disc cutter with a large radius enables a much larger cutting speed and thus a larger material removal rate. However, due to the large radius of the disc cutter, its potential collision with narrow and twisted channels becomes a serious concern. In this paper, we propose a novel two-phase approach for efficiently machining a complex narrow cavity workpiece using a disc-shaped cutter, i.e., 3 + 2-axis disc-slotting of the channel by multiple layers (rough machining) + five-axis disc-milling of the freeform channel side surfaces (semi-finish machining). Both simulation and physical cutting experiments are conducted to assess the effectiveness and advantages of the proposed method. The experimental results show that, with respect to a same cusp-height threshold on the channel side surfaces, the total machining time of the tested part by the proposed method is about only 36% of that by the conventional approach of plunging-milling (for roughing) plus milling by a slender cylindrical cutter (for semi-finishing).</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 1","pages":"Pages 414-437"},"PeriodicalIF":5.7,"publicationDate":"2024-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123001322/pdfft?md5=d9dfdae7ea484f37253dda461d003d01&pid=1-s2.0-S1000936123001322-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48973244","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Thermodynamic property of sandwich cylindrical shell structure with metallic wire mesh: Numerical modeling and experimental analysis","authors":"Xin XUE ,&nbsp;Guojian SHEN ,&nbsp;Juan LIAO","doi":"10.1016/j.cja.2023.06.038","DOIUrl":"10.1016/j.cja.2023.06.038","url":null,"abstract":"<div><p>As a new addition to lightweight composite structures, the sandwich cylindrical shell with a metallic wire mesh core has emerged as a promising solution for thermodynamic performance analysis at elevated temperatures. The intricate interwoven cellular formations within the metallic wire mesh pose difficulties for thermo-mechanical modeling and property evaluation. First, the constitutive models employed to characterize hysteresis phenomena were presented, comprising isotropic elasticity, Bergstrom-Boyce model, Ogden hyper-elasticity, and parameter identification through mechanical examinations at varying temperatures. Second, the finite element modeling of cylindrical shell structures was determined for modal and steady-state dynamic analyses. Third, the experimental procedures were carried out, including the preparation of the sandwich cylindrical shell and the dynamic testing platform. The first-order natural frequency of the cylindrical shell structure is close to the resonance frequency of the dynamic test results, with a maximum error of 6.5%, demonstrating the accuracy of the simulation model. When compared to the solid-core cylindrical shell, the average insertion loss of the sandwich cylindrical shell structure within the frequency range of 10–1000 Hz at room temperature is up to 11.09 dB. Furthermore, at elevated temperatures, the average insertion loss of the sandwich cylindrical shell decreases but fluctuates as the temperature changes.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 1","pages":"Pages 138-152"},"PeriodicalIF":5.7,"publicationDate":"2024-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123002303/pdfft?md5=6cca265c491c3ae8eaa458be14a34020&pid=1-s2.0-S1000936123002303-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45768498","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Table of Content","authors":"","doi":"10.1016/S1000-9361(23)00412-0","DOIUrl":"https://doi.org/10.1016/S1000-9361(23)00412-0","url":null,"abstract":"","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 1","pages":"Pages i-ii"},"PeriodicalIF":5.7,"publicationDate":"2024-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123004120/pdfft?md5=a7d95c547285c91c082485b51052a13c&pid=1-s2.0-S1000936123004120-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139100920","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Deployment analysis of composite thin-walled lenticular tubes with effect of storage time and temperature","authors":"Jinfeng DENG ,&nbsp;Ning AN ,&nbsp;Qilong JIA ,&nbsp;Xiaofei MA","doi":"10.1016/j.cja.2023.05.011","DOIUrl":"10.1016/j.cja.2023.05.011","url":null,"abstract":"<div><p>Composite Thin-walled Lenticular Tube (CTLT) is increasingly utilized in small satellites missions as a lightweight, foldable, and rollable structural material that facilitates the construction of large deployable systems. The CTLT is initially flattened and coiled around a central hub for storage before launch, during which elastic energy is stored as deformation energy, allowing it to be self-deployed on demand for use in orbit. This work presents a comprehensive investigation into the coiling, storage and deployment behaviors of CTLT that wraps around a central hub. A nonlinear explicit dynamic finite element model was developed with both deformable CTLT and rigid-bodies mechanisms including the central hub and guide rollers, as well as the complex interactions among them. The coiling mechanics characteristics such as stored strain energy and rotational moment were presented and validated against experimental data in the literature. Then, the dynamic deployment behaviors were analyzed in terms of two different deployment methods, namely, controlled deployment and free deployment. The effect of material property change during storage was also discussed through numerical experiments.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 1","pages":"Pages 162-172"},"PeriodicalIF":5.7,"publicationDate":"2024-01-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123001632/pdfft?md5=559a124f51b20a06876ddd006755a19a&pid=1-s2.0-S1000936123001632-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43032109","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}