Aerospace Science and Technology最新文献

{"title":"Flow field analysis of a high agility type aircraft aeroelastic wind tunnel model","authors":"Julius Stegmüller,&nbsp;Andreas Molz,&nbsp;Paloma García-Guillén,&nbsp;Christian Breitsamter","doi":"10.1016/j.ast.2025.110177","DOIUrl":"10.1016/j.ast.2025.110177","url":null,"abstract":"<div><div>Modern high-agility aircraft are often affected by the consequences of tail buffeting effects at subsonic speeds and medium to high angles of attack. High pressure fluctuations with distinct frequency contents characterize the flow field downstream of vortex breakdown and are often responsible for the dynamic structural response, which can result in heavy structural damage and degraded handling qualities. For analyzing the flow field and the frequency content of the pressure fluctuations over a modular full-span wind tunnel model with either rigid or aeroelastically scaled double-delta wings and horizontal and vertical tailplanes, stereoscopic particle image velocimetry measurements and measurements with a fast-response aerodynamic pressure probe are performed. The aeroelastically scaled components are 3D-printed from polylactide whereas the rigid components are made of aluminum and serve as a reference case. When comparing the rigid and aeroelastically scaled configurations, significant differences in the axial vortex core velocities in some measurement planes can be detected, while the power spectral densities of the flow field pressure fluctuations show similar characteristics with slight differences in the amplitudes.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110177"},"PeriodicalIF":5.0,"publicationDate":"2025-03-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143747321","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":"Dynamic characteristics analysis under different flame modes in coaxial staged combustor","authors":"Yunjiao Shi ,&nbsp;Jinghe Lu ,&nbsp;Xiao Liu ,&nbsp;Guangpu Lv ,&nbsp;Enhui Liu ,&nbsp;Hongtao Zheng","doi":"10.1016/j.ast.2025.110181","DOIUrl":"10.1016/j.ast.2025.110181","url":null,"abstract":"<div><div>Gas turbines are extensively employed due to their high power output and rapid start-up capabilities. However, the growing demand for environmental protection has imposed increasingly stringent requirements on gas turbine performance. Among the technological advancements addressing these challenges, lean premixed combustion technology has gained widespread application for its ability to substantially reduce combustion temperatures, thereby mitigating harmful emissions. Specifically, in liquid-fueled combustors, the implementation of lean premixed prevaporization (LPP) technology offers a compact and lightweight design, making it particularly advantageous for use in aircraft engines. A low-emission, tower-type coaxial staged combustor incorporating a tower-type main combustion stage and utilizing LPP technology is simulated in this study. The flame structure, droplet distribution, temperature distribution, and flow field fluctuations under different loads are studied using large eddy simulation (LES) and the flamelet generated manifold (FGM) combustion model. Finally, the dynamic mode decomposition (DMD) method was used to analyze the spatial characteristics of the flame distribution. Results show that with the load changing, two flame modes: diffusion flame and partially premixed flame are observed within the combustor. The dynamic characteristics of the tower-staged coaxial combustor are significantly affected by the flame mode. As the combustor flame mode transitions from a diffusion flame to a partially premixed flame, the flame structure becomes more compact. This transition results in a decrease in CO emissions, while NO emissions increase significantly, with NO levels at the 0.35 load reaching nearly 20 times those observed at the 0.1 load. As the load increases, pressure fluctuations intensify, but overall they remain below 8‰ of the operating pressure, indicating relatively stable combustion. The amplitude distribution of different mode orders exhibits specific regional characteristics.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110181"},"PeriodicalIF":5.0,"publicationDate":"2025-03-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143768784","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Numerical studies on steady interaction of low enthalpy hypersonic double wedge flows using different gas models","authors":"Qin Li ,&nbsp;Yonghai Wang ,&nbsp;Yihui Weng ,&nbsp;Zhenfeng Wang ,&nbsp;Yunchuan Wu ,&nbsp;Mengyu Wang ,&nbsp;Pan Yan ,&nbsp;Linsen Zhang ,&nbsp;Wei Su","doi":"10.1016/j.ast.2025.110171","DOIUrl":"10.1016/j.ast.2025.110171","url":null,"abstract":"&lt;div&gt;&lt;div&gt;Numerical investigations and analyses are carried out on the interactions of low enthalpy hypersonic 30–55° double wedge configuration, particularly focusing on steady cases at conditions similar to the experimental setup by Swantek &amp; Austin [AIAA 2012–284], with &lt;span&gt;&lt;math&gt;&lt;mrow&gt;&lt;mi&gt;M&lt;/mi&gt;&lt;mi&gt;a&lt;/mi&gt;&lt;mo&gt;=&lt;/mo&gt;&lt;mn&gt;7&lt;/mn&gt;&lt;/mrow&gt;&lt;/math&gt;&lt;/span&gt; and &lt;span&gt;&lt;math&gt;&lt;mrow&gt;&lt;msub&gt;&lt;mi&gt;h&lt;/mi&gt;&lt;mn&gt;0&lt;/mn&gt;&lt;/msub&gt;&lt;mo&gt;=&lt;/mo&gt;&lt;mn&gt;2.1&lt;/mn&gt;&lt;mi&gt;M&lt;/mi&gt;&lt;mi&gt;J&lt;/mi&gt;&lt;mo&gt;/&lt;/mo&gt;&lt;mi&gt;k&lt;/mi&gt;&lt;mi&gt;g&lt;/mi&gt;&lt;/mrow&gt;&lt;/math&gt;&lt;/span&gt;. To achieve a steady solution, Reynolds numbers (&lt;span&gt;&lt;math&gt;&lt;mrow&gt;&lt;mi&gt;R&lt;/mi&gt;&lt;mi&gt;e&lt;/mi&gt;&lt;/mrow&gt;&lt;/math&gt;&lt;/span&gt;) lower than those in the experiment are used. For increased accuracy, a third-order scheme &lt;span&gt;&lt;math&gt;&lt;msubsup&gt;&lt;mrow&gt;&lt;mtext&gt;WENO&lt;/mtext&gt;&lt;mn&gt;3&lt;/mn&gt;&lt;mo&gt;−&lt;/mo&gt;&lt;mtext&gt;PRM&lt;/mtext&gt;&lt;/mrow&gt;&lt;mrow&gt;&lt;mrow&gt;&lt;mn&gt;1&lt;/mn&gt;&lt;mo&gt;,&lt;/mo&gt;&lt;mn&gt;1&lt;/mn&gt;&lt;/mrow&gt;&lt;/mrow&gt;&lt;mn&gt;2&lt;/mn&gt;&lt;/msubsup&gt;&lt;/math&gt;&lt;/span&gt; [Li et al., J. Sci. Comput., 88(3) (2021) 75–130] with improved resolution is employed. Meanwhile, three gas models, i.e., the perfect, equilibrium, and non-equilibrium gas models, are used to analyze the difference potentials that arise from the physical model. After validating the methods, grid convergence studies are first conducted at &lt;span&gt;&lt;math&gt;&lt;mrow&gt;&lt;mi&gt;M&lt;/mi&gt;&lt;mi&gt;a&lt;/mi&gt;&lt;mo&gt;=&lt;/mo&gt;&lt;mn&gt;7&lt;/mn&gt;&lt;/mrow&gt;&lt;/math&gt;&lt;/span&gt; and &lt;span&gt;&lt;math&gt;&lt;mrow&gt;&lt;mi&gt;R&lt;/mi&gt;&lt;mi&gt;e&lt;/mi&gt;&lt;mo&gt;=&lt;/mo&gt;&lt;mn&gt;2.5&lt;/mn&gt;&lt;mo&gt;×&lt;/mo&gt;&lt;msup&gt;&lt;mrow&gt;&lt;mn&gt;10&lt;/mn&gt;&lt;/mrow&gt;&lt;mn&gt;5&lt;/mn&gt;&lt;/msup&gt;&lt;mo&gt;/&lt;/mo&gt;&lt;mi&gt;m&lt;/mi&gt;&lt;/mrow&gt;&lt;/math&gt;&lt;/span&gt;, to determine the appropriate grid resolution for the main computations. Subsequently, comprehensive numerical studies are carried out on the steady interactions and their evolution at &lt;span&gt;&lt;math&gt;&lt;mrow&gt;&lt;mi&gt;M&lt;/mi&gt;&lt;mi&gt;a&lt;/mi&gt;&lt;mo&gt;=&lt;/mo&gt;&lt;mn&gt;7&lt;/mn&gt;&lt;/mrow&gt;&lt;/math&gt;&lt;/span&gt; and &lt;span&gt;&lt;math&gt;&lt;mrow&gt;&lt;msub&gt;&lt;mi&gt;h&lt;/mi&gt;&lt;mn&gt;0&lt;/mn&gt;&lt;/msub&gt;&lt;mo&gt;=&lt;/mo&gt;&lt;mn&gt;2.1&lt;/mn&gt;&lt;mi&gt;M&lt;/mi&gt;&lt;mi&gt;J&lt;/mi&gt;&lt;mo&gt;/&lt;/mo&gt;&lt;mi&gt;k&lt;/mi&gt;&lt;mi&gt;g&lt;/mi&gt;&lt;/mrow&gt;&lt;/math&gt;&lt;/span&gt;. Specifically: (a) The upper limits of &lt;span&gt;&lt;math&gt;&lt;mrow&gt;&lt;mi&gt;R&lt;/mi&gt;&lt;mi&gt;e&lt;/mi&gt;&lt;/mrow&gt;&lt;/math&gt;&lt;/span&gt; are identified where the flows remain steady with the transmitted shock impinging on the aft wedge, and the corresponding interaction characteristics as well as differences in the three gas models are investigated qualitatively and quantitatively, e.g., the shock system, vortex structures, distributions such as pressure, Mach number, and specific heat ratio. Notably, a quasi-normal shock wave is observed within the slip line passage in the case of the perfect gas model. (b) The flow characteristics of the three models, including the interaction pattern, geometric features of triple points, impingements, and separation zone, are studied and compared for &lt;span&gt;&lt;math&gt;&lt;mrow&gt;&lt;mi&gt;R&lt;/mi&gt;&lt;mi&gt;e&lt;/mi&gt;&lt;mo&gt;=&lt;/mo&gt;&lt;mn&gt;4&lt;/mn&gt;&lt;mo&gt;,&lt;/mo&gt;&lt;mspace&gt;&lt;/mspace&gt;&lt;mn&gt;3&lt;/mn&gt;&lt;mo&gt;,&lt;/mo&gt;&lt;mrow&gt;&lt;mspace&gt;&lt;/mspace&gt;&lt;mtext&gt;and&lt;/mtext&gt;&lt;mspace&gt;&lt;/mspace&gt;&lt;/mrow&gt;&lt;mn&gt;2&lt;/mn&gt;&lt;mo&gt;×&lt;/mo&gt;&lt;msup&gt;&lt;mrow&gt;&lt;mn&gt;10&lt;/mn&gt;&lt;/mrow&gt;&lt;mn&gt;4&lt;/mn&gt;&lt;/msup&gt;&lt;mo&gt;/&lt;/mo&gt;&lt;mi&gt;m&lt;/mi&gt;&lt;/mrow&gt;&lt;/math&gt;&lt;/span&gt;. Differences primarily emerge between the results of the perfect gas model","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110171"},"PeriodicalIF":5.0,"publicationDate":"2025-03-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143792643","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Combustion chamber length prediction for scramjet based on a quasi-one-dimensional model","authors":"Xiang Zhao ,&nbsp;Ruyan Zhao ,&nbsp;Gaochun Li ,&nbsp;Kehai Dong ,&nbsp;Zhixun Xia ,&nbsp;Likun Ma","doi":"10.1016/j.ast.2025.110182","DOIUrl":"10.1016/j.ast.2025.110182","url":null,"abstract":"<div><div>At present, there have been a lot of studies on combustion chamber configurations of scramjet, and the prevailing method is to employ cavities or struts to create regional recirculation zones to achieve complete combustion. Few attentions are paid to the combustion chamber length. This paper, from the perspective of chemical kinetics, aims to study the factors affecting the combustion chamber length required for complete combustion, and the effect of chamber length on engine performance. To achieve this purpose, a one-dimensional model with finite-rate chemistry has been established. The chamber length is computed from the occurrence of the peak in species’ concentration. The results show that dynamic pressure and elevation have impacts on the required chamber length. The fuel itself also plays an important role. Hydrogen, compared to other fuels, has a quite short ignition delay time and, therefore, the chamber length for complete combustion is quite short. Restricted chamber length inevitably worsens engine performance because of incomplete combustion.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110182"},"PeriodicalIF":5.0,"publicationDate":"2025-03-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143808430","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Prediction of subsonic cascade flow fields by physics-informed graph neural networks with unbalanced data","authors":"Yunyang Feng ,&nbsp;Wei Yuan ,&nbsp;Xizhen Song ,&nbsp;Zhaoqi Yan ,&nbsp;Tianyu Pan","doi":"10.1016/j.ast.2025.110173","DOIUrl":"10.1016/j.ast.2025.110173","url":null,"abstract":"<div><div>Accurate and fast prediction of flow field is a significant task for compressor design and optimization which leads to a faster iteration of design cycle. Deep learning method shows ability to solve diverse types of problem and has enormous potential in flow field reconstruction. Graph neural networks (GNN) is one of verified structures of deep learning model and is well-suited for the flow field prediction task. Data of compressor is usually insufficient or unbalanced since the high cost of experiment or high-fidelity simulation and leads to the deterioration of deep learning model. To improve the deep learning model performance with unbalanced training data, a physic-informed graph neural networks (PIGNN) model is suggested with the residual of governing equations introduced into the loss function to constraint the prediction of flow field. As a typical case, the cascade flow field is selected to be the research object in this study. The residual of governing equations is fast calculated in batch by numerical differential. With the guidance of physics-informed learning, PIGNN outperforms GNN in flow field prediction while its mean error decreases 13.4 % with balanced data and up to 38.6 % with different unbalanced data. The model performances at different inlet conditions and the predictions of key characteristics are explored simultaneously. The mean prediction error of key characteristics is reduced over 10 % in most situations by physics-informed learning.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110173"},"PeriodicalIF":5.0,"publicationDate":"2025-03-29","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143768782","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Influence of the fuel jet injection angle on the combustion process of a gel scramjet","authors":"Zhitan Zhou,&nbsp;Taiyu Cao,&nbsp;Ranhui Liang,&nbsp;Yueheng Mi","doi":"10.1016/j.ast.2025.110180","DOIUrl":"10.1016/j.ast.2025.110180","url":null,"abstract":"<div><div>Boron-containing gel propellants have high-energy densities and controllable injection characteristics, can significantly improve ramjet performance, and present a new direction for hypersonic vehicle development. To address the performance optimization problem of boron-containing gel scramjet engines, this study combines supersonic turbulence combustion interaction equations and the multiphase flow equations to make use of a combustion flow simulation method for the internal flow fields of boron particle gel ramjet engines at a multi-grid scale. Numerical simulations of the internal flow field of a combustion chamber at different fuel injection angles were conducted. The results indicated that as the fuel injection angle increased, the fuel jet penetration effect was enhanced, and the obstruction effect on the supersonic airflow became more pronounced. When the injection angle exceeds 35°, the supersonic airflow flows along the lower wall at a particular deflection angle. As the angle increases, the main combustion region of the fuel moves from the end of the combustion chamber to the downstream cavity. When the fuel injection angle reaches 80°, the temperature increase efficiency reaches its optimal value of 71 %. The research findings provide an optimized design solution for boron-containing gel propellant scramjet engines.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110180"},"PeriodicalIF":5.0,"publicationDate":"2025-03-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143760238","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Research on the combustion and internal ballistic characteristics of paraffin-enhanced grains with dual-layer skeleton in hybrid rocket motors","authors":"Guobiao Cai ,&nbsp;Yuchen Zhang ,&nbsp;Yuanjun Zhang ,&nbsp;Jiaqi Tian ,&nbsp;Hao Zhu ,&nbsp;Hui Tian","doi":"10.1016/j.ast.2025.110179","DOIUrl":"10.1016/j.ast.2025.110179","url":null,"abstract":"<div><div>Hybrid rocket motors have seen increasing applications in launch vehicles, upper stages, suborbital spacecrafts, and sounding rockets. 3D printing technology has been utilized to manufacture skeletons with complex geometries that support paraffin-based fuel, enhancing the regression rate. However, few studies have investigated the evolution of the burning surface at the interface of the two fuels, and considered layered skeleton technology for thrust adjustment. This study introduced a novel paraffin-enhanced grain with a dual-layer skeleton that combined the benefits of both paraffin and acrylonitrile-butadiene-styrene. Using a combination of simulation and experimental methods, the changing law of the burning surface, dual-stage performance, and advantages of the dual-layer skeleton grain were investigated. The results showed that the dual-layer skeleton forms sharp angles in the 1st stage and burning surface expansion angles in the 2nd stage, with the angle variations being determined by the regression rates of skeleton and paraffin. This grain achieved dual-stage combustion and internal ballistic performance through distinct skeleton structures in the inner and outer layers, providing high thrust in the 1st stage and progressively increasing lower thrust in the 2nd stage. At a constant oxidizer mass flow rate of 30 g/s, the dual-layer skeleton grain achieved a packing fraction of 88 %, a burn duration of 31.6 s, an initial thrust of 68.7 N, and a thrust adjustment ratio of 1.92, demonstrating enhanced performance compared to conventional grains. Our findings improved the performance of grains in hybrid rocket motors to benefit the aerospace industry.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110179"},"PeriodicalIF":5.0,"publicationDate":"2025-03-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143792746","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Large-Eddy Simulations of kerosene spray combustion in a supersonic jet flow","authors":"Florian Kissel,&nbsp;Guillaume Ribert,&nbsp;Pascale Domingo","doi":"10.1016/j.ast.2025.110164","DOIUrl":"10.1016/j.ast.2025.110164","url":null,"abstract":"<div><div>High-speed reactive two-phase flows, relevant for the development of future scramjet engines, are studied by Large-Eddy Simulations. The present configuration is inspired by the supersonic Cheng's burner replacing hydrogen with kerosene in the gaseous or liquid phase. The sonic kerosene injection is surrounded by a supersonic co-flow of hot vitiated air, ensuring a jet flame's stabilization. The global equivalence of the burner is set to 0.5. A 5-species global mechanism and a more detailed mechanism from the literature involving 19 species and 54 reactions are compared with a new optimized chemistry involving 18 species and 29 reactions. The impact of ignition delay and droplet size on flame stabilization dynamics and combustion modes is discussed. The necessity of a sub-grid closure for the source terms is assessed. Whatever the kerosene phase, the flame structure is dominated by the non-premixed combustion regime, even if a non-negligible contribution of the rich premixed regime is detected.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110164"},"PeriodicalIF":5.0,"publicationDate":"2025-03-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143744742","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 data-driven vorticity-confinement approach for compressible aerodynamics prediction on very-coarse meshes","authors":"Tianhong Tu ,&nbsp;Zhiyu Zhang ,&nbsp;Huiyang Yu ,&nbsp;Chuangxin He ,&nbsp;Yingzheng Liu","doi":"10.1016/j.ast.2025.110176","DOIUrl":"10.1016/j.ast.2025.110176","url":null,"abstract":"<div><div>How to predict aerodynamics accurately and quickly is the focus of attention in this era, especially in the initial design stage of aircraft. In this study, we address the treatment of the shear layers in low-resolution mesh for compressible flow. The method is proposed to compensate for the inevitable increase in the thickness of the boundary layer and the reduction of the velocity gradient due to the coarse mesh by introducing a vorticity confinement term as the body source in the momentum equation. The confinement parameter determines the strength of the vorticity confinement term for the reduction of numerical dissipation. In order to extend this method to various flow conditions, a surrogate model is established using ordinary least squares (OLS) to link the confinement parameter to local flow features that reflect turbulence characteristics. Ultimately, the DVC approach is successfully applied to transonic boundary layer and free shear flow. The accurate prediction is achieved for the pressure coefficients on a transonic airfoil by capturing the λ structure of the buffet offset. The mean relative error of the pressure coefficients on the airfoil is reduced from 48.1 % (by inviscid Euler approach) and 26.7 % (by RANS) to 1.8 % (by DVC approach). Given that the current method is assimilated through a flat boundary layer, better results can be obtained by introducing flows that are related to the actual conditions for data assimilation. It thus serves as a novel data-driven approach for rapid prediction of specific flow structures and aerodynamic performances in aerospace engineering.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110176"},"PeriodicalIF":5.0,"publicationDate":"2025-03-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143792642","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Research on error compensation methods of wing deflection reconstruction based on FBG strain sensors","authors":"Yiheng Yuan,&nbsp;Wang Sun,&nbsp;Yingjie Zhang,&nbsp;Pinghui Wang,&nbsp;Song Han","doi":"10.1016/j.ast.2025.110167","DOIUrl":"10.1016/j.ast.2025.110167","url":null,"abstract":"<div><div>Fiber Bragg Grating (FBG) sensors have the characteristics of compact size, multiplexing capability, and high sensitivity, making them ideal for structural health monitoring of unmanned aerial vehicles (UAVs). However, FBG strain Sensors measure wing strain rather than wing deflection, necessitating the conversion of strain into deflection through a deflection reconstruction algorithm. The deflection reconstruction process is influenced by the number and placement of sensors, as well as the reconstruction algorithm, which may result in measurement errors.</div><div>To reduce reconstruction errors in wing deflection, this study proposes two approaches: the optimization of sensor placement and the application of an error compensation function.</div><div>Firstly, a method for optimizing the location and number of FBG sensors based on a genetic algorithm is proposed. By optimizing the sensor installation location and number to be more consistent with the actual strain distribution characteristics of the wing, the error of wing deflection measurement based on deflection reconstruction algorithm is reduced.</div><div>Additionally, a novel error compensation function based on Fourier Series Fitting is developed. Static loading test validated that this approach achieves high accuracy and robustness under varying load conditions, making it suitable for improving the precision of wing deflection reconstruction.</div><div>Finally, the wing deflection reconstruction system was implemented on a vertical take-off and landing (VTOL) UAV with a wingspan of 4 meters, achieving real-time measurement of wing deflection and twist angle during flight, verifying the effectiveness of both the reconstruction system and the error compensation function through flight testing.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110167"},"PeriodicalIF":5.0,"publicationDate":"2025-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143746875","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}