Eunsung Kwak , Keekeun Kim , Chungryeol Lee , Jinhyung Kim , Yongha Kim
{"title":"Optimization based on artificial intelligence for thermal barrier coating with shadow effects using electron beam physical vapor deposition","authors":"Eunsung Kwak , Keekeun Kim , Chungryeol Lee , Jinhyung Kim , Yongha Kim","doi":"10.1016/j.ast.2025.110991","DOIUrl":"10.1016/j.ast.2025.110991","url":null,"abstract":"<div><div>Thermal barrier coatings for gas turbine engine cooling blades require precise thickness control during electron beam physical vapor deposition (EB-PVD), and achieving uniform coating distribution is critical for aerospace applications. However, shadow effects during EB-PVD create significant thickness variations that compromise coating quality and performance reliability. Therefore, this study presents a comprehensive computational formulation that integrates three key models: thermal behavior of the ingot within the EB-PVD machine, coating deposition modeling of the vapor plume, and substrate-manipulator kinematics. Virtual ingots were employed to specifically account for shadow effects, while specimen tests provided experimental coefficients that were incorporated into the formulation. The approach utilizes coating deposition characteristics related to manipulator input profiles to train a computationally efficient multi-layer perceptron (MLP). Using the trained MLP, optimization was performed to minimize thermal barrier coating thickness variation on cooling blades. The results demonstrate that this integrated formulation successfully addresses shadow-induced thickness variations, contributing to a comprehensive database of coating deposition characteristics for thermal barrier coating applications in gas turbine engines. Consequently, the proposed formulation offers a straightforward and computationally efficient solution for optimizing EB-PVD processes, enabling improved coating uniformity and reliability for aerospace thermal barrier coating applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110991"},"PeriodicalIF":5.8,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145158249","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}
Zhezhe Su , Yanbing Zheng , Jianfeng Zhu , Yancheng You
{"title":"Surrogate model-based design method for auxiliary intake door of tilt electric ducted fans","authors":"Zhezhe Su , Yanbing Zheng , Jianfeng Zhu , Yancheng You","doi":"10.1016/j.ast.2025.110990","DOIUrl":"10.1016/j.ast.2025.110990","url":null,"abstract":"<div><div>Targeting the lip flow separation phenomenon during tilting processes of electric-driven ducted fans, a flow separation suppression method employing auxiliary intake door has been proposed. A Kriging surrogate model correlating intake door parameters with the overall performance metrics of ducted fans has been constructed. Multi-objective genetic optimization algorithms were applied to select optimal intake door parameters, with the effects of auxiliary intake door on ducted fan performance during tilting, takeoff, and cruise processes being analyzed. Results show that during the 90° to 24° tilting phase, the Pareto-frontier-optimized intake door configuration for thrust-per-unit-power effectively suppresses lip flow separation under high-intensity crosswind inflow conditions. During this process, the loss between three-dimensional CFD simulations and one-dimensional ideal thrust-per-unit-power can be reduced from a range of 31.7 % to -0.6 % down to 13.5 %-2.1 %. During takeoff conditions, the implementation of auxiliary intake door increases lip suction area; this intake door configuration enables a 1.8 % improvement in thrust-per-unit-power under takeoff conditions. During cruise conditions, no flow occurs within the intake door, and the incorporation of intake door demonstrates negligible impact on cruise performance.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110990"},"PeriodicalIF":5.8,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145219729","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 investigation of circumferentially-inclined film cooling for rotating detonation combustor","authors":"Jingtian Yu , Songbai Yao , Yeqi Zhou , Wenwu Zhang","doi":"10.1016/j.ast.2025.110986","DOIUrl":"10.1016/j.ast.2025.110986","url":null,"abstract":"<div><div>The stable operation of rotating detonation engines (RDEs) faces significant thermal protection challenges. Unlike most conventional combustors with purely axial flow, the rotating detonation combustor (RDC) is characterized by a circumferential primary flow induced by the rotating detonation wave (RDW). Therefore, this study proposes a film cooling configuration with combined axial and circumferential injection angles. Numerical simulations are conducted to examine the evolution of the secondary cooling flow and the variation of the film cooling performance under different injection pressures and circumferential angles. Distinct jet behaviors are observed depending on whether the secondary flow is oriented with (co-flow) or against (counter-flow) the RDW propagation. The counter-flow inclination case is found to form an inclined jet that enhances cooling, particularly in the vacuum region between film holes, with performance improving as the inclination angle increases. In contrast, the co-flow inclination case promotes vortex-induced stagnation and wall detachment, reducing both the protected area and temperature drop as the inclination angle increases. The associated increase in coolant mass flow rate is also analyzed for cost efficiency when the secondary flow injection pressure is adjusted to enhance the temperature drop.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110986"},"PeriodicalIF":5.8,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265915","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}
Zhiyuan Cao , Zhipeng Li , Jing Yang , Qinpeng Gu , Xi Gao , Na Yang , Bo Liu
{"title":"Influence of circumferential casing treatment groove on leakage vortex breakdown and unsteady flow characteristics in a transonic compressor rotor","authors":"Zhiyuan Cao , Zhipeng Li , Jing Yang , Qinpeng Gu , Xi Gao , Na Yang , Bo Liu","doi":"10.1016/j.ast.2025.110992","DOIUrl":"10.1016/j.ast.2025.110992","url":null,"abstract":"<div><div>The study reveals that leakage vortex breakdown is the primary cause of unsteady flow phenomena in the tip region of a transonic compressor rotor. Under near-stall conditions, significant unsteady flow characteristics are observed in the multi-channel configuration, with the tip unsteadiness closely linked to variations in tip loading. Under shock wave interaction, the tip leakage vortex undergoes expansion and generates reverse flow, leading to vortex breakdown. The leakage flow outside the vortex core circumvents the large-scale reverse flow region, accompanied by secondary leakage phenomena. Due to blockage in the tip flow field, leading-edge spillage occurs, forming a self-sustained unsteady cycle. After implementing circumferential casing treatment, leakage vortex breakdown is suppressed even under stall conditions, and the unsteady phenomena in the tip region are significantly mitigated. The scheme of groove parameters (CT-Z1, h6, W2) improve stall margin by 29 %. Regarding the stall mechanism: For the solid casing, the leading-edge spillage induced by leakage vortex breakdown serves as the precursor to rotor stall. As the outlet pressure increases, substantial leakage flow spills over the blade leading edge, thereby increasing the incidence angle of the mainstream and further destabilizing the flow in adjacent blade passages. When multiple channels experience large-scale blockage clusters, the rotor enters stall, accompanied by a rapid drop in mass flow. Unsteady RANS simulations reveal that leakage vortex breakdown is the primary cause of unsteady flow in the transonic compressor rotor tip region under near-stall conditions, and circumferential casing treatment can suppress such breakdown to mitigate unsteady phenomena. Although casing treatment grooves can eliminate leakage vortex breakdown and enhance compressor stability margin, the stall mechanism remains governed by leading-edge spillage of leakage flow. Consequently, casing treatment delays stall onset but does not fundamentally alter the underlying stall mechanism.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110992"},"PeriodicalIF":5.8,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145158252","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}
Bu-Kyeng Sung , Jae-Eun Kim , Eun-Sung Lee , Seung-Min Jeong , Jeong-Yeol Choi
{"title":"Flame structure and performance evaluation of rocket-type vitiated air heater with film cooling","authors":"Bu-Kyeng Sung , Jae-Eun Kim , Eun-Sung Lee , Seung-Min Jeong , Jeong-Yeol Choi","doi":"10.1016/j.ast.2025.111001","DOIUrl":"10.1016/j.ast.2025.111001","url":null,"abstract":"<div><div>This study presents a novel design approach for a Vitiated Air Heater (VAH) integrated into a direct-connect scramjet combustor (DCSC) by incorporating coolant-air injection into a rocket combustor. The suitability of hydrogen as a fuel for VAH operation was evaluated through thermodynamic analysis. Using Large Eddy Simulation (LES) with the ‘reactingFoam’ solver in OpenFOAM, the flame structure within the VAH combustor was analyzed. The VAH is designed to operate at a stagnation temperature of 1578 K and a pressure of 17.3 bar, corresponding to flight conditions at Mach numbers between 4.0 and 5.0. Key design features include a gaseous hydrogen/oxygen coaxial shear injector for heat addition and 24 peripheral air injectors for air supply and film cooling. The integration of coolant injection generated a recirculation zone that enhanced turbulence and facilitated the formation of a unique dual flame structure. This configuration enabled complete combustion within the first third of the combustor, achieving a uniform temperature distribution close to the target adiabatic flame temperature. The proposed VAH design offers significant potential to provide an efficient and precise testing environment for high-speed propulsion systems.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 111001"},"PeriodicalIF":5.8,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145265735","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":"Neural Networks for high accuracy short term ship motion predictions with applications to autonomous UAVs","authors":"Kameron P.C. Palmer, Rishad A. Irani","doi":"10.1016/j.ast.2025.110964","DOIUrl":"10.1016/j.ast.2025.110964","url":null,"abstract":"<div><div>An Autonomous Uncrewed Aerial Vehicle (UAV) attempting to perform a vertical landing on a moving ship’s deck must be capable of predicting the ship’s motion in order determine the most opportune landing time. If the UAV is acting independent of the ship additional constraints are introduced; computation resources are limited to what can be mounted on the drone and the UAV must predict motion from noisy UAV-mounted sensors. The work presented proposes a Gated Recurrent Unit based Autoencoder (GRU-A) Neural Network (NN) model for predicting future ship motion with the aforementioned constraints. The GRU-A model is compared to a more typical Multi-Layered Perceptron, Nonlinear Auto-Regressive (MLP-NAR) NN model. Both NN models are tested for their ability to minimize error over a 5 s prediction horizon composed of 50 separate time-steps, their ability to predict through noisy inputs and mitigate the introduced error, and their computation costs. Furthermore, a large dataset made from a high fidelity simulation is transformed to reflect data that would be encountered in-situ, improving the applicability of the work. It was found that the proposed GRU-A model has superior signal prediction capabilities, achieving approximately 30 times lower error than the MLP-NAR model when predicting over a 5 s period, suitable of a vertical landing time horizon. In addition, the proposed GRU-A model was more resilient to input noise and, when trained with noise it outperformed the MLP-NAR. It was also found that the memory required to compute predictions with both models is approximately equal and that the computation time of the GRU-A model is similar to the MLP-NAR model with both models being capable of making predictions within 100 ms so long as they are not chosen to be too large. Overall, the proposed GRU-A model is demonstrated as a superior alternative to the more typical MLP-NAR model when predicting full signals in all cases for use with a small UAV.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110964"},"PeriodicalIF":5.8,"publicationDate":"2025-09-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145219711","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}
Han Dong , Jinglei Xu , Shuai Huang , Jingqing Chen , Bingsong Lan , Ruifeng Pan , Yuqi Zhang
{"title":"Experimental and numerical investigation of thrust characteristics in a bypass dual throat nozzle with dagger-shaped deflection component","authors":"Han Dong , Jinglei Xu , Shuai Huang , Jingqing Chen , Bingsong Lan , Ruifeng Pan , Yuqi Zhang","doi":"10.1016/j.ast.2025.110961","DOIUrl":"10.1016/j.ast.2025.110961","url":null,"abstract":"<div><div>A novel BDTN-SVTOL with dagger-shaped deflection component, featuring simplified structural design for efficient cruise and short/vertical takeoff and landing (SVTOL) thrust vectoring (TV) with a single nozzle system, is developed, numerically simulated, and experimentally evaluated to investigate the thrust characteristics. The dagger-shaped deflection component serves as the critical flow-control element for BDTN-SVTOL, enabling mainstream large deflection exceeding 90° A parametric optimization framework was established for the deflection surface of dagger-shaped deflection component, quantifying the relationship between critical geometric parameters and thrust characteristics while maximizing angular coverage. A decoupled methodology for profile optimization is proposed guided by the distinct near-wall flow characteristics, and the optimized configuration achieves a TV angle greater than 95° while maintaining a vertical thrust coefficient (<em>c<sub>f</sub></em><sub>y</sub>) above 0.90 across all operating conditions, matching the SVTOL performance of Three-Bearing Swivel Nozzle (3BSN) while integrating multi-directional deflection capability and simpler mechanical architecture. The experimental model demonstrates dual-mode operational capabilities in wind tunnel tests, capturing nozzle internal flow field schlieren morphology while validating CFD simulation accuracy. In normal flight mode, the nozzle achieves a thrust vector angle exceeding 15° which can enhance high maneuverability. In SVTOL mode, compared to the conventional BDTN with crescent-shaped deflectors exhibiting TV angles of 60°and <em>c<sub>f</sub></em><sub>y</sub> of 0.7, the nozzle with dagger-shaped deflector demonstrates enhanced performance through more stable single-channel design, achieving TV angles exceeding 90° and thrust coefficients over 0.90, thereby overcoming limitations in angular deflection efficiency and the energy dissipation.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110961"},"PeriodicalIF":5.8,"publicationDate":"2025-09-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145219744","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}
Mingwei Chen , Chu Zhang , Jianwu He , Chao Yang , Pengcheng Wang , Yonghe Zhang , Li Duan , Qi Kang
{"title":"Emulating scaled drag-free control dynamics on a ground simulator testbed","authors":"Mingwei Chen , Chu Zhang , Jianwu He , Chao Yang , Pengcheng Wang , Yonghe Zhang , Li Duan , Qi Kang","doi":"10.1016/j.ast.2025.110937","DOIUrl":"10.1016/j.ast.2025.110937","url":null,"abstract":"<div><div>As a key technique for gravitational wave detection, drag-free control presents significant challenges for ground experimental validation. This work addresses the problem of experimentally emulating the scaled drag-free control on a ground simulator composed of an air-bearing testbed and two inverted pendulums. In this paper, the dynamics models are deduced and simplified. The dynamics similarity conditions are determined through the use of the Pi theorem. And the concepts of the equivalent stiffness and equivalent mass of the inverted pendulum are proposed to establish the similar dynamics equations. Subsequently, scaling laws are derived to design the simulator testbed. Basic scaling laws are introduced to evaluate the scaled control index. Besides, an underactuated closed-loop control strategy employing redundant adjustable thrusters is devised for the ground experiment. Finally, the precise tracking control of the air-bearing testbed relative to two pendulums is realized on the ground drag-free simulator, emulating the scaled displacement control mode with two test masses. And the scaled control indexes corresponding to space mission are validated in the resulting drag-free simulation system. The effectiveness of the proposed approach is confirmed by the scaling equivalence experiments of drag-free control with two test masses.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110937"},"PeriodicalIF":5.8,"publicationDate":"2025-09-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145105241","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}
Langjian Yang , Jilin Lei , Dongfang Wang , Xiwen Deng , Dewen Jia , Kang Liu , Liang Sun
{"title":"Effects and grey relational analysis of electronic control parameters on mixture formation and combustion characteristics of an aviation piston engine during cold-start","authors":"Langjian Yang , Jilin Lei , Dongfang Wang , Xiwen Deng , Dewen Jia , Kang Liu , Liang Sun","doi":"10.1016/j.ast.2025.110988","DOIUrl":"10.1016/j.ast.2025.110988","url":null,"abstract":"<div><div>Deteriorated cold-start performance in plateau or extremely cold environments is a major challenge limiting the environmental adaptability of the aviation piston engines. A 3D combustion numerical model characterizing cold-start operation was developed and validated through overall engine tests and constant volume combustion chamber (CVCC) spray experiments. The effects of 6 electronic control parameters on spray, mixture formation, ignition, combustion characteristics, and parametric sensitivity were investigated. Results show that pilot injection (PiI) strategies helped form a larger equivalence ratio region (0.6∼1) that was more favorable for ignition and combustion around the periphery of the spray core after main injection (MI). PiI 2 timing had minimal influence on in-cylinder pressure, pressure rise rate (PRR) and heat release rate (HRR). Increasing PiI 2 and PiI 1 quantities enhanced combustion pressure, PRR and HRR during power stroke, though their phases of peaks first advanced and then retarded. The optimal MI timing in this study was identified as −15 °CA BTDC. As injection pressure increased from 40 to 160 MPa, LPL and VPL of spray gradually increased, while the Sauter mean diameter (SMD) gradually decreased. This facilitated to improvement of the spray atomization quality to form a larger near stoichiometric equivalence ratio region (0.8∼1.2) and accelerated the transition from low-temperature combustion (LTC) to high-temperature combustion (HTC), thus increasing the mean combustion temperature. OH was generated in the region of temperature above 2000 K, and the higher the temperature, the more OH was produced. Simultaneously, during power stroke, in-cylinder pressure, PRR, HRR and their peaks progressively increased. The order of sensitivity to the effects of maximum in-cylinder pressure and OH mass fraction peak was: pilot injection number > injection pressure > PiI 2 quantity > PiI 1 quantity > PiI 2 timing > MI timing. These findings support optimizing electronic control parameters for robust cold-start strategies.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110988"},"PeriodicalIF":5.8,"publicationDate":"2025-09-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145219714","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":"Traversal-flyby planning of walker-delta mega constellation using Hohmann maneuvers and phase sequencing","authors":"Qing Shi , Jin Zhang , Ke-Mao Wang , Bing Yan","doi":"10.1016/j.ast.2025.110982","DOIUrl":"10.1016/j.ast.2025.110982","url":null,"abstract":"<div><div>The planning of the traversal flyby of constellation satellites (TFCS) belongs to the time dependent travelling salesman problems (TDTSPs), and the solving methods only simply based on optimization methods are inefficient and unstable for mega constellations. A planning method based on the Hohmann maneuvers and phase sequencing (HMPS) is proposed for the TFCS, visiting all constellation satellites twice at close range by only one observation satellite (OS). The initial inclination and the right ascension of the ascending node (RAAN) of the OS are taken as variables and are searched by the differential evolution (DE) algorithm. The total cumulative adjusted phase of the Hohmann-maneuver phasing is used to represent the objective function of the total velocity increment. For the two-body problem, the sorting of the desired OS’s initial phases is used to determine the flyby sequence, and then the flyby times and impulses are calculated based on the Hohmann maneuvers. For the <em>J</em><sub>2</sub> perturbed problem, the multi-round phase sequencing is used. The proposed method is applied to solving the traversal flyby planning problems of small, medium and mega Walker-delta constellations. The results show that the HMPS method is efficient. Compared with the mixed-integer optimization using the DE algorithm, the proposed method can obviously improve the computational efficiency and reduce the fuel cost. For the mega constellation with 1584 satellites, the average velocity increment and mission duration per flyby are only 2.2 m/s and 1.3 h. Due to the regular distribution of the constellation satellites, the optimal flyby sequences for different Walker-delta constellations under the two-body dynamics show the obvious symmetry. The relation between the constellation configuration parameters and the situation that several flybys are completed by only one Hohmann transfer is revealed.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"168 ","pages":"Article 110982"},"PeriodicalIF":5.8,"publicationDate":"2025-09-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"145158253","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}