Chinese Journal of Aeronautics最新文献

{"title":"Geometric error measuring, modeling, and compensation for CNC machine tools: A review","authors":"Zhao ZHANG ,&nbsp;Feng JIANG ,&nbsp;Ming LUO ,&nbsp;Baohai WU ,&nbsp;Dinghua ZHANG ,&nbsp;Kai TANG","doi":"10.1016/j.cja.2023.02.035","DOIUrl":"10.1016/j.cja.2023.02.035","url":null,"abstract":"<div><p>Geometric error, mainly due to imperfect geometry and dimensions of machine components, is one of the major error sources of machine tools. Considering that geometric error has significant effects on the machining quality of manufactured parts, it has been a popular topic for academic and industrial research for many years. A great deal of research work has been carried out since the 1970 s for solving the problem and improving the machining accuracy. Researchers have studied how to measure, detect, model, identify, reduce, and compensate the geometric errors. This paper presents a thorough review of the latest research activities and gives an overview of the state of the art in understanding changes in machine tool performance due to geometric errors. Recent advances in measuring the geometrical errors of machine tools are summarized, and different kinds of error identification methods of translational axes and rotation axes are illustrated respectively. Besides, volumetric geometric error modeling, tracing, and compensation techniques for five-axis machine tools are emphatically introduced. Finally, research challenges in order to improve the volumetric accuracy of machine tools are also highlighted.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 163-198"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123000560/pdfft?md5=87f82ae0849a3d6e9972e5887612c0f5&pid=1-s2.0-S1000936123000560-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43535551","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":"Enhancing adhesive bond strength of CFRP/titanium joints through NaOH anodising and resin pre-coating treatments with optimised anodising conditions","authors":"Yunsen HU ,&nbsp;Jingheng ZHANG ,&nbsp;Lin WANG ,&nbsp;Fei CHENG ,&nbsp;Xiaozhi HU","doi":"10.1016/j.cja.2023.11.007","DOIUrl":"10.1016/j.cja.2023.11.007","url":null,"abstract":"<div><p>Adhesively Bonded Carbon Fibre Reinforced Plastic (CFRP) and titanium alloy have been extensively used as a hybrid structure in modern aircrafts due to their excellent combination of mechanical properties and chemical stabilities. This study utilised NaOH anodising method to create micro-rough titanium surfaces for enhancing adhesive bonding between titanium alloy and CFRP laminates. A special and simple technique named Resin Pre-Coating (RPC) was also employed to improve the surface wetting of anodised titanium and grinded CFRP substrates. The influences of anodising temperature and duration on the surface morphology, wettability and adhesive bond strength were investigated. The single lap shear test results showed that the bond strength of specimens anodised at 20 °C for 15 min improved by 135.9% and 95.4%, respectively, in comparison with that of acid pickled and grinded specimens (without RPC treatment). Although increasing the anodising temperature and duration produced rougher titanium surfaces, the adhesively bonded joints were not strong enough due to relatively friable titanium oxide layers.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 511-523"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003916/pdfft?md5=95759223b1c524c2e871ff94bff57423&pid=1-s2.0-S1000936123003916-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135715353","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":"Model of fractured medium and nondestructive control of composite materials","authors":"Vasily GOLUBEV ,&nbsp;Ilia NIKITIN ,&nbsp;Katerina BEKLEMYSHEVA","doi":"10.1016/j.cja.2023.11.023","DOIUrl":"10.1016/j.cja.2023.11.023","url":null,"abstract":"<div><p>Non-destructive testing of composites is an important issue in the modern aircraft industry. Composites are susceptible to the barely visible impact damage which can affect the residual strength of the material and occurs both during production and operation. The continuum model for describing the damaged zone is presented. The slip theory relations used for a continuous distribution of slip planes are applied. At the initial stage, the isotropic background model is used. This model allows the material slippage along the fractures based on the Coulomb friction law with the small viscous addition. In this regime, the govern system of equations becomes rigid. To overcome this difficulty, the explicit–implicit grid-characteristic scheme is proposed. The standard ultrasound diagnostic procedure of damaged composite materials is successfully simulated. Compared with the trivial free-surface fracture model, different reactions on the compression and stretch waves are registered. This approach provided an effective way for the simulation of complex dynamic behavior of damage zones.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 93-99"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123004077/pdfft?md5=553b1ef9105418244f53636043f93eec&pid=1-s2.0-S1000936123004077-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138616479","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":"Microstructure evolution and mechanical properties of brazing joint for ultra-thin-walled Inconel 718 considering grain size effect and brazing temperature","authors":"Rui ZHAO ,&nbsp;Yueshuai SONG ,&nbsp;Hui KANG ,&nbsp;Min WAN","doi":"10.1016/j.cja.2023.12.002","DOIUrl":"https://doi.org/10.1016/j.cja.2023.12.002","url":null,"abstract":"<div><p>The systematic investigation of the mechanical properties and microstructure evolution process of ultra-thin-walled Inconel 718 capillary brazing joints is of great significance because of the exceptionally high demands on its application. To achieve this objective, this study investigates the impact of three distinct brazing temperatures and five typical grain sizes on the brazed joints’mechanical properties and microstructure evolution process. Microstructural evolution analysis was conducted based on Electron Back Scatter Diffraction (EBSD), Scanning Electron Microscopy (SEM), X-Ray Diffraction (XRD), High-Resolution Transmission Electron Microscopy (HRTEM), and Focused Ion Beam (FIB). Besides, the mechanical properties and fracture behavior were studied based on the uniaxial tension tests and <em>in-situ</em> tension tests. The findings reveal that the brazing joint’s strength is higher for the fine-grain capillary than the coarse-grain one, primarily due to the formation of a dense branch structure composed of G-phase in the brazing seam. The effects of grain size, such as pinning and splitting, are amplified at higher brazing temperatures. Additionally, micro-cracks initiate around brittle intermetallic compounds and propagate through the eutectic zone, leading to a cleavage fracture mode. The fracture stress of fine-grain specimens is higher than that of coarse-grain due to the complex micro-crack path. Therefore, this study contributes significantly to the literature by highlighting the crucial impact of grain size on the brazing properties of ultra-thin-walled Inconel 718 structures.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 541-556"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S100093612300417X/pdfft?md5=6e37a2721b7ac6790c2c2b323b1660fa&pid=1-s2.0-S100093612300417X-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139548876","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":"Mismatch loss analysis of solar array output power on stratospheric airship during flight","authors":"Siyu LIU ,&nbsp;Kangwen SUN ,&nbsp;Haoquan LIANG ,&nbsp;Xinzhe JI ,&nbsp;Tong ZOU ,&nbsp;Chuan SHAN","doi":"10.1016/j.cja.2023.10.014","DOIUrl":"10.1016/j.cja.2023.10.014","url":null,"abstract":"<div><p>Stratospheric airships are long-endurance aerostats and have broad applications. All of the energy required for their operation is obtained from solar radiation, which makes accurate calculation of the energy output from the solar array crucial to the design and flight planning of the airships. However, the status of each photovoltaic module in the solar array may differ due to the airship curvature, resulting in mismatch losses and lowered output power, which has not been widely studied. In this paper, an irradiation model and a thermal model are established based on the actual arrangement of the modules. The output power model is established considering the non-uniform radiation in the array. The mismatch losses of the array are analyzed under different flight conditions. The output power of the solar array is decreased by up to 31.6% compared to the ideal state. Moreover, the proportion of mismatch losses increases with latitude, but the maximum mismatch loss power occurs at mid-latitudes. Then, an array reconfiguration method is proposed based on the irradiance dispersion index and position dispersion index. The reconfigured array increases output power by 11.5% and can maintain energy balance in continuous flight. The results can be used to correct the overestimation of the output power during the airship design or to guide the configuration of the solar array.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 371-384"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003631/pdfft?md5=093f4594507163097b2a0b96d8625f75&pid=1-s2.0-S1000936123003631-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136059878","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)00451-X","DOIUrl":"https://doi.org/10.1016/S1000-9361(23)00451-X","url":null,"abstract":"","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages i-ii"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S100093612300451X/pdfft?md5=d4159f2a6e8edc01a0b98dd8f2cf6664&pid=1-s2.0-S100093612300451X-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139549476","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":"Impact characterization on thin structures using machine learning approaches","authors":"Flavio DIPIETRANGELO,&nbsp;Francesco NICASSIO,&nbsp;Gennaro SCARSELLI","doi":"10.1016/j.cja.2023.11.022","DOIUrl":"10.1016/j.cja.2023.11.022","url":null,"abstract":"<div><p>Machine learning algorithms are trained and compared to identify and to characterise the impact on typical aerospace panels of different geometry. Experimental activities are conducted to build a proper impacts’ dataset. Polynomial regression algorithm and artificial neural network are applied and optimised to panels without stringer to test their capability to identify the impacts. Subsequently, the algorithms are applied to panels reinforced with stringers that represent a significant increase of complexity in terms of dynamic features of the system to test: the focus is not only on the impact position’s detection but also on the event’s severity. After the identification of the best algorithm, the corresponding machine learning model is deployed on an ARM processor mini-computer, implementing an impact detection system, able to be installed on board an aerial vehicle, making it a smart aircraft equipped with an artificial intelligence decision-making system.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 30-44"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123004065/pdfft?md5=83cf95fde869ce7c3114a9fc21f18831&pid=1-s2.0-S1000936123004065-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139304415","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":"Aircraft parameter estimation using a stacked long short-term memory network and Levenberg-Marquardt method","authors":"Zhe HUI ,&nbsp;Yinan KONG ,&nbsp;Weigang YAO ,&nbsp;Gang CHEN","doi":"10.1016/j.cja.2023.09.002","DOIUrl":"10.1016/j.cja.2023.09.002","url":null,"abstract":"<div><p>To effectively estimate the unknown aerodynamic parameters from the aircraft’s flight data, this paper proposes a novel aerodynamic parameter estimation method incorporating a stacked Long Short-Term Memory (LSTM) network model and the Levenberg-Marquardt (LM) method. The stacked LSTM network model was designed to realize the aircraft dynamics modeling by utilizing a frame of nonlinear functional mapping based entirely on the measured input–output data of the aircraft system without requiring explicit postulation of the dynamics. The LM method combines the already-trained LSTM network model to optimize the unknown aerodynamic parameters. The proposed method is applied by using the real flight data, generated by ATTAS aircraft and a bio-inspired morphing Unmanned Aerial Vehicle (UAV). The investigation reveals that for the two different flight data, the designed stacked LSTM network structure can maintain the efficacy of the network prediction capability only by appropriately adjusting the dropout rates of its hidden layers without changing other network parameters (i.e., the initial weights, initial biases, number of hidden cells, time-steps, learning rate, and number of training iterations). Besides, the proposed method’s effectiveness and potential are demonstrated by comparing the estimated results of the ATTAS aircraft or the bio-inspired morphing UAV with the corresponding reference values or wind-tunnel results.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 123-136"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003060/pdfft?md5=96547d9fa061a6eceb623cf1e2b65b22&pid=1-s2.0-S1000936123003060-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135248588","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":"Aerodynamic optimization of an adaptive flap for next-generation green aircraft","authors":"Tianlong LIN ,&nbsp;Rosario PECORA ,&nbsp;Danilo CILIBERTI ,&nbsp;Wei XIA ,&nbsp;Shuling HU","doi":"10.1016/j.cja.2023.10.010","DOIUrl":"10.1016/j.cja.2023.10.010","url":null,"abstract":"<div><p>Adaptive, morphing flaps are taking ever-increasing attention in civil aviation thanks to the expected benefits this technology can bring at the aircraft level in terms of high-lift performance improvement and related fuel burnt reduction per flight. Relying upon morphing capabilities, it is possible to fix a unique setting for the flap and adapt the flap shape to match the aerodynamic requirements for take-off or landing. The proper morphed shapes can assure better high-lift performances than those achievable by referring to a conventional flap. Moreover, standing the unique flap setting for take-off and landing, a dramatic simplification of the flap deployment systems may be achieved. As a consequence of this simplification, the deployment system can be fully hosted in the wing, thus avoiding under-wing nacelles with significantly better aerodynamics and fuel consumption. The first step for a rational design of an adaptive flap consists in defining the target morphed shapes and the unique optimal flap setting in the take-off and landing phases. In this work, aerodynamic optimization analyses are carried out to determine the best flap setting and related morphed shapes in compliance with the take-off and landing requirements of a reference civil transport aircraft. Four different initial conditions are adopted to avoid the optimization falling into local optima, thus obtaining four groups of optimal candidate configurations. After comparing each candidate's performance through 2D and 3D simulations, the optimal configuration has been selected. 2D simulations show that the optimal configuration is characterized by a maximum lift increase of 31.92% in take-off and 9.04% in landing. According to 3D simulations, the rise in maximum lift equals 22.26% in take-off and 3.50% in landing. Numerical results are finally verified through wind tunnel tests, and the aerodynamic mechanism behind the obtained improvements is explained by carefully analyzing the flow field around the flap.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 100-122"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003540/pdfft?md5=aef7df18755bcb1dca7a56bb936dbc15&pid=1-s2.0-S1000936123003540-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135809362","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 and fair PPO-based integrated scheduling method for multiple tasks of SATech-01 satellite","authors":"Qi SHI ,&nbsp;Lu LI ,&nbsp;Ziruo FANG ,&nbsp;Xingzi BI ,&nbsp;Huaqiu LIU ,&nbsp;Xiaofeng ZHANG ,&nbsp;Wen CHEN ,&nbsp;Jinpei YU","doi":"10.1016/j.cja.2023.10.011","DOIUrl":"10.1016/j.cja.2023.10.011","url":null,"abstract":"<div><p>SATech-01 is an experimental satellite for space science exploration and on-orbit demonstration of advanced technologies. The satellite is equipped with 16 experimental payloads and supports multiple working modes to meet the observation requirements of various payloads. Due to the limitation of platform power supply and data storage systems, proposing reasonable mission planning schemes to improve scientific revenue of the payloads becomes a critical issue. In this article, we formulate the integrated task scheduling of SATech-01 as a multi-objective optimization problem and propose a novel Fair Integrated Scheduling with Proximal Policy Optimization (FIS-PPO) algorithm to solve it. We use multiple decision heads to generate decisions for each task and design the action mask to ensure the schedule meeting the platform constraints. Experimental results show that FIS-PPO could push the capability of the platform to the limit and improve the overall observation efficiency by 31.5% compared to rule-based plans currently used. Moreover, fairness is considered in the reward design and our method achieves much better performance in terms of equal task opportunities. Because of its low computational complexity, our task scheduling algorithm has the potential to be directly deployed on board for real-time task scheduling in future space projects.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 417-430"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003606/pdfft?md5=59d215b6f5551b4692c077f6c6d32727&pid=1-s2.0-S1000936123003606-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136009931","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}