Chinese Journal of Aeronautics最新文献

{"title":"A novel adaptive coordinated tracking control scheme for a morphing aircraft with telescopic wings","authors":"Enmei WANG ,&nbsp;Hao LU ,&nbsp;Jianchun ZHANG ,&nbsp;Chenliang WANG ,&nbsp;Jianzhong QIAO","doi":"10.1016/j.cja.2023.10.026","DOIUrl":"10.1016/j.cja.2023.10.026","url":null,"abstract":"<div><p>Inspired by flight biology, morphing flight technology has great potential to improve the adaptability and maneuverability of aircraft. This paper is devoted to the flight control problem of morphing aircraft, and aimed at safe and fuel-saving flight through morphing actively. Specifically, the longitudinal dynamics of a morphing aircraft with telescopic wings is modelled as a strict-feedback nonlinear system. Through fitting the expression of aerodynamic parameters by the morphing ratio, the model uncertainties induced by morphing errors are embedded in the dynamics. To meet the safety and fuel-saving requirements, an Adaptive Coordinated Tracking Control Scheme (ACTCS) is then proposed, which consists of a morphing control module and a tracking control module. For the morphing control module, an on-line morphing decision model is given in an optimization process with respect to the morphing ratio, and a second-order tracking filter is introduced to smooth the decision output and ensure the physical realizability. For the tracking control module, the novel adaptive controllers for the velocity and altitude subsystems are proposed based on the dynamic surface control method, in which adaptive mechanisms are designed to compensate for the model uncertainties. Finally, the proposed ACTCS is simulated in nine different cases of the test flight mission, to verify its effectiveness, robustness and fuel-saving effect.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 148-162"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003758/pdfft?md5=fbd14749f7afab01e0e0fed3d8fcefc5&pid=1-s2.0-S1000936123003758-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136152713","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":"Seamless morphing trailing edge flaps for UAS-S45 using high-fidelity aerodynamic optimization","authors":"Mir Hossein NEGAHBAN,&nbsp;Musavir BASHIR,&nbsp;Victor TRAISNEL,&nbsp;Ruxandra Mihaela BOTEZ","doi":"10.1016/j.cja.2023.10.024","DOIUrl":"10.1016/j.cja.2023.10.024","url":null,"abstract":"<div><p>The seamless trailing edge morphing flap is investigated using a high-fidelity steady-state aerodynamic shape optimization to determine its optimum configuration for different flight conditions, including climb, cruise, and gliding descent. A comparative study is also conducted between a wing equipped with morphing flap and a wing with conventional hinged flap. The optimization is performed by specifying a certain objective function and the flight performance goal for each flight condition. Increasing the climb rate, extending the flight range and endurance in cruise, and decreasing the descend rate, are the flight performance goals covered in this study. Various optimum configurations were found for the morphing wing by determining the optimum morphing flap deflection for each flight condition, based on its objective function, each of which performed better than that of the baseline wing. It was shown that by using optimum configuration for the morphing wing in climb condition, the required power could be reduced by up to 3.8% and climb rate increases by 6.13%. The comparative study also revealed that the morphing wing enhances aerodynamic efficiency by up to 17.8% and extends the laminar flow. Finally, the optimum configuration for the gliding descent brought about a 43% reduction in the descent rate.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 12-29"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003734/pdfft?md5=608da58ac8eea8e17e520fb9ca4febe0&pid=1-s2.0-S1000936123003734-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136152674","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":"Semi-supervised remote sensing image scene classification with prototype-based consistency","authors":"Yang LI,&nbsp;Zhang LI,&nbsp;Zi WANG,&nbsp;Kun WANG,&nbsp;Qifeng YU","doi":"10.1016/j.cja.2023.12.012","DOIUrl":"10.1016/j.cja.2023.12.012","url":null,"abstract":"<div><p>Deep learning significantly improves the accuracy of remote sensing image scene classification, benefiting from the large-scale datasets. However, annotating the remote sensing images is time-consuming and even tough for experts. Deep neural networks trained using a few labeled samples usually generalize less to new unseen images. In this paper, we propose a semi-supervised approach for remote sensing image scene classification based on the prototype-based consistency, by exploring massive unlabeled images. To this end, we, first, propose a feature enhancement module to extract discriminative features. This is achieved by focusing the model on the foreground areas. Then, the prototype-based classifier is introduced to the framework, which is used to acquire consistent feature representations. We conduct a series of experiments on NWPU-RESISC45 and Aerial Image Dataset (AID). Our method improves the State-Of-The-Art (SOTA) method on NWPU-RESISC45 from 92.03% to 93.08% and on AID from 94.25% to 95.24% in terms of accuracy.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 459-470"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123004272/pdfft?md5=37b9840b8ccd056f068e7a94382e82a3&pid=1-s2.0-S1000936123004272-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139021144","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":"Design and validation of a variable camber wing structure","authors":"Xiasheng SUN ,&nbsp;Jingfeng XUE ,&nbsp;Jin ZHOU ,&nbsp;Zhigang WANG ,&nbsp;Wenjuan WANG ,&nbsp;Mengjie ZHANG","doi":"10.1016/j.cja.2023.09.004","DOIUrl":"10.1016/j.cja.2023.09.004","url":null,"abstract":"<div><p>Variable camber wing technology is one of the important development trends of green aviation at present. Through smooth, seamless, continuous and adaptive change of wing camber, the aerodynamic performance is improved in achieving increase in lift and reduction in resistance and noise. Based on the aerodynamic validation model CAE-AVM, Chinese Aeronautical Establishment (CAE) has carried out the design and validation of a variable camber wing, proposed an aerodynamic deformation matrix for the leading and trailing edges of aircraft wings in take-off, landing and cruise conditions. Various structures and driving schemes are compared, and several key technology problems of leading and trailing edge deformation are solved. A full-size leading edge wind tunnel test piece with a span of 2.7 m and a trailing edge ground function test piece are developed. The deformation and shape maintenance capabilities of the leading edge is verified under real wind load conditions, and the load bearing and deformation capabilities of the trailing edge is verified under simulated follow-on load. The results indicate that the leading and trailing edges of the variable camber wing can achieve the required deformation angle and have a certain load-bearing capacity. Our study can provide some insights into the application of variable camber wing technology for civil aircraft.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 1-11"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003084/pdfft?md5=89343e5ba641bd485a5e1dcec8bf64ef&pid=1-s2.0-S1000936123003084-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135249357","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":"Editorial Board - Inside Front Cover","authors":"","doi":"10.1016/S1000-9361(23)00450-8","DOIUrl":"https://doi.org/10.1016/S1000-9361(23)00450-8","url":null,"abstract":"","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Page IFC"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123004508/pdfft?md5=034e0215caeb015fbcd8e4fb9b083d52&pid=1-s2.0-S1000936123004508-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139549475","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":"Conventional and micro scale finite element modeling for metal cutting process: A review","authors":"Le WANG ,&nbsp;Caixu YUE ,&nbsp;Xianli LIU ,&nbsp;Ming LI ,&nbsp;Yongshi XU ,&nbsp;Steven Y. LIANG","doi":"10.1016/j.cja.2023.03.004","DOIUrl":"10.1016/j.cja.2023.03.004","url":null,"abstract":"<div><p>The metal cutting process is accompanied by complex stress field, strain field, temperature field. The comprehensive effects of process parameters on chip morphology, cutting force, tool wear and residual stress are complex and inter-connected. Finite element method (FEM) is considered as an effective method to predict process variables and reveal microscopic physical phenomena in the cutting process. Therefore, the finite element (FE) simulation is used to research the conventional and micro scale cutting process, and the differences in the establishment of process variable FE simulation models are distinguished, thereby improving the accuracy of FE simulation. The reliability and effectiveness of FE simulation model largely depend on the accuracy of the simulation method, constitutive model, friction model, damage model in describing mesh element, the dynamic mechanical behavior of materials, the tool-chip-workpiece contact process and the chip formation mechanism. In this paper, the FE models of conventional and micro process variables are comprehensively and up-to-date reviewed for different materials and machining methods. The purpose is to establish a FE model that is more in line with the real cutting conditions, and to provide the possibility for optimizing the cutting process variables. The development direction of FE simulation of metal cutting process is discussed, which provides guidance for future cutting process modeling.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 199-232"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123000602/pdfft?md5=32f692df1b9143ad0c47058ee74cf60e&pid=1-s2.0-S1000936123000602-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41623228","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":"Performance evaluation for multi-target tracking with temporal dimension specifics","authors":"Zhenzhen SU ,&nbsp;Hongbing JI ,&nbsp;Cong TIAN ,&nbsp;Yongquan ZHANG","doi":"10.1016/j.cja.2023.08.024","DOIUrl":"10.1016/j.cja.2023.08.024","url":null,"abstract":"<div><p>With the great development of Multi-Target Tracking (MTT) technologies, many MTT algorithms have been proposed with their own advantages and disadvantages. Due to the fact that requirements to MTT algorithms vary from the application scenarios, performance evaluation is significant to select an appropriate MTT algorithm for the specific application scenario. In this paper, we propose a performance evaluation method on the sets of trajectories with temporal dimension specifics to compare the estimated trajectories with the true trajectories. The proposed method evaluates the estimate results of an MTT algorithm in terms of tracking accuracy, continuity and clarity. Furthermore, its computation is based on a multi-dimensional assignment problem, which is formulated as a computable form using linear programming. To enhance the influence of recent estimated states of the trajectories in the evaluation, an attention function is used to reweight the trajectory errors at different time steps. Finally, simulation results show that the proposed performance evaluation method is able to evaluate many aspects of the MTT algorithms. These evaluations are worthy for selecting suitable MTT algorithms in different application scenarios.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 446-458"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003047/pdfft?md5=f6f1c0edf6c6d318169eba981768502d&pid=1-s2.0-S1000936123003047-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135299073","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 semi-analytical multi-harmonic balance method on full-3D contact model for dynamic analysis of dry friction systems","authors":"He SUN ,&nbsp;Dayi ZHANG ,&nbsp;Yaguang WU ,&nbsp;Qingyang SHEN ,&nbsp;Dianyin HU","doi":"10.1016/j.cja.2023.11.026","DOIUrl":"10.1016/j.cja.2023.11.026","url":null,"abstract":"<div><p>Dry friction damping structures are widely-used in aero-engines to mitigate vibration. The nonlinear nature of friction and the two-dimensional in-plane motion on the contact interface bring challenges to accurately and efficiently predict the forced response of frictionally damped structures. The state-of-the-art Multi-Harmonic Balance Method (MHBM) on quasi-3D contact model in engineering cannot precisely capture the kinematics on the friction interface although the efficiency is high. The full-3D contact model can describe the constitutive relationship of the interface in a more accurate manner; however, the efficiency and convergence are not guaranteed for large-scale models. In this paper, a semi-analytical MHBM on full-3D contact model is proposed. The original Trajectory Tracking Method (TTM) for evaluating the contact force is reformulated to make the calculation more concise and the derivation of the Analytical Jacobian Matrix (AJM) feasible. Based on the chain rule of derivation, the AJM which is the core to upgrade the performance is deduced. Through a shrouded blade finite element model, the accuracy and efficiency of the proposed method are compared with both the MHBM on full-3D contact model with numerical Jacobian matrix and the MHBM on quasi-3D contact model with AJM. The results show that the AJM improves significantly the efficiency of the MHBM on full-3D contact model. The time cost of the proposed method is in the same order of magnitude as that of the MHBM on quasi-3D contact model. We also confirm that the full-3D contact model is necessary for the dynamic analyses of shrouded blades. If one uses the quasi-3D model, the estimation relative error of damping can even reach 31.8% in some cases. In addition, the AJM also brings benefits for stability analysis. It is highly recommended that engineers use the MHBM on full-3D contact model for the dynamic analysis and design of shrouded blades.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 309-329"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123004156/pdfft?md5=fb97ee7deaea6811cf4e24b0d582e3a6&pid=1-s2.0-S1000936123004156-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138622772","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":"Design of a large-scale model for wind tunnel test of a multiadaptive flap concept","authors":"Mürüvvet Sinem SICIM DEMIRCI ,&nbsp;Rosario PECORA ,&nbsp;Metin Orhan KAYA","doi":"10.1016/j.cja.2023.11.008","DOIUrl":"10.1016/j.cja.2023.11.008","url":null,"abstract":"<div><p>The design and application of morphing systems are ongoing issues compelling the aviation industry. The Clean Sky - program represents the most significant aeronautical research ever launched in Europe on advanced technologies for greening next-generation aircraft. The primary purpose of the program is to develop new concepts aimed at decreasing the effects of aviation on the environment, increasing reliability, and promoting eco-friendly mobility. These ambitions are pursued through research on enabling technologies fostering noise and gas emissions reduction, mainly by improving aircraft aerodynamic performances. Within the Clean Sky framework, a multimodal morphing flap device was designed based on tight industrial requirements and tailored for large civil aircraft applications. The flap is deployed in one unique setting, and its cross section is morphed differently in take-off and landing to get the necessary extra lift for the specific flight phase. Moreover, during the cruise, the tip of the flap is deflected for load control and induced drag reduction. Before manufacturing the first flap prototype, a high-speed (<em>Ma</em> = 0.3), large-scale test campaign (geometric scale factor 1:3) was deemed necessary to validate the performance improvements brought by this novel system at the aircraft level. On the other hand, the geometrical scaling of the flap prototype was considered impracticable due to the unscalability of the embedded mechanisms and actuators for shape transition. Therefore, a new architecture was conceived for the flap model to comply with the scaled dimensions requirements, withstand the relevant loads expected during the wind tunnel tests and emulate the shape transition capabilities of the true-scale flap. Simplified strategies were developed to effectively morph the model during wind tunnel tests while ensuring the robustness of each morphed configuration and maintaining adequate stiffness levels to prevent undesirable deviations from the intended aerodynamic shapes. Additionally, a simplified design was conceived for the flap-wing interface, allowing for quick adjustments of the flap setting and enabling load transmission paths like those arising between the full-scale flap and the wing. The design process followed for the definition of this challenging wind tunnel model has been addressed in this work, covering the definition of the conceptual layout, the numerical evaluation of the most severe loads expected during the test, and the verification of the structural layout by means of advanced finite element analyses.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 58-80"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003928/pdfft?md5=8a72076fe3eb5625d14b1d9fbf47d21f&pid=1-s2.0-S1000936123003928-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135764283","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 whole-net cooperative positioning method based on CDGNSS and inter-vehicle ranging","authors":"Shan HU,&nbsp;Hongbo ZHAO,&nbsp;Chen ZHUANG","doi":"10.1016/j.cja.2023.09.017","DOIUrl":"10.1016/j.cja.2023.09.017","url":null,"abstract":"<div><p>Relative positioning is recognized as an important issue for vehicles in urban environments. Multi-vehicle Cooperative Positioning (CP) techniques which fuse the Global Navigation Satellite System (GNSS) and inter-vehicle ranging have attracted attention in improving the performance of baseline estimation between vehicles. However, current CP methods estimate the baselines separately and ignore the interactions among the positioning information of different baselines. These interactions are called ‘information coupling’. In this work, we propose a new multi-vehicle precise CP framework using the coupled information in the network based on the Carrier Differential GNSS (CDGNSS) and inter-vehicle ranging. We demonstrate the benefit of the coupled information by deriving the Cramer-Rao Lower Bound (CRLB) of the float estimation in CP. To fully use this coupled information, we propose a Whole-Net CP (WN-CP) method which consists of the Whole-Net Extended Kalman Filter (WN-EKF) as the float estimation filter, and the Partial Baseline Fixing (PBF) as the ambiguity resolution part. The WN-EKF fuses the measurements of all baselines simultaneously to improve the performance of float estimation, and the PBF strategy fixes the ambiguities of the one baseline to be estimated, instead of full ambiguity resolution, to reduce the computation load of ambiguity resolution. Field tests involving four vehicles were conducted in urban environments. The results show that the proposed WN-CP method can achieve better performance and meanwhile maintain a low computation load compared to the existing methods.</p></div>","PeriodicalId":55631,"journal":{"name":"Chinese Journal of Aeronautics","volume":"37 2","pages":"Pages 401-416"},"PeriodicalIF":5.7,"publicationDate":"2024-02-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"https://www.sciencedirect.com/science/article/pii/S1000936123003205/pdfft?md5=215e72ca749e3ab071eaac9c1d2f3abc&pid=1-s2.0-S1000936123003205-main.pdf","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135429716","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}