Aerospace Science and Technology最新文献

{"title":"An intelligent prediction method for supersonic flow field in scramjet isolator enhanced by feature details","authors":"Ye Tian ,&nbsp;Yitong Zhao ,&nbsp;Xue Deng ,&nbsp;Maotao Yang ,&nbsp;Erda Chen ,&nbsp;Mengqi Xu ,&nbsp;Hu Ren","doi":"10.1016/j.ast.2025.110116","DOIUrl":"10.1016/j.ast.2025.110116","url":null,"abstract":"<div><div>The accurate and fast prediction of hypersonic flow field can provide reliable data for the analysis of flow evolution process. The traditional unsteady numerical simulation method requires a large amount of time and economic cost to carry out flow prediction. The flow field prediction algorithm based on deep learning has been proved to be an effective modeling tool and approximator. In order to predict the complex flow process of scramjet isolation segment with high precision, an intelligent prediction model combining position coding and detail feature recovery is proposed. Positional encoding is used to capture the spatial distribution characteristics of pressure points, while multi-scale convolutions within the encoder-decoder framework extract multi-scale features from different receptive fields. This enhances the model's capability to capture detailed features of the Mach field. The method is validated with data from unsteady numerical simulations using various suction parameters. Experimental results show that this method effectively recovers characteristic parameters such as the position and area of the separation zone in the Mach field. Compared to the Neural Network model of Multipath Fusion (MBFCNN), the proposed method improves the Structural Similarity Index (SSIM) by 6.71% and the Peak Signal-to-Noise Ratio (PSNR) by 44.33% on the test dataset.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110116"},"PeriodicalIF":5.0,"publicationDate":"2025-03-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143548334","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":"The influence of different initial parameters on the operational characteristics of a Kerosene/air two-phase rotating detonation engine","authors":"Xiafei Li ,&nbsp;Jianzhong Li ,&nbsp;Wu Jin ,&nbsp;Qian Yao ,&nbsp;Qiongyao Qin ,&nbsp;Li Yuan","doi":"10.1016/j.ast.2025.110117","DOIUrl":"10.1016/j.ast.2025.110117","url":null,"abstract":"<div><div>An annular rotating detonation engine (RDE) with an integrated fuel atomization and mixing structure based on high-speed shear air flow rate and fuel injection was designed for air/kerosene reactants. Experimental studies were conducted on its detonation combustion characteristics. Under a low outlet contraction ratio, the RDE primarily operated in a \"Single Detonation Mode\"; as the outlet contraction ratio increased, the RDE exhibited a \"Complex Hybrid Detonation Mode.\" Based on detonation wave velocities and dynamic pressure characteristics, it was found that the \"Complex Hybrid Detonation Mode\" consists of \"Random Detonation Wave\" (0–1000 m/s), \"Single Detonation Wave\" (1000–2000 m/s), and \"Double Detonation Wave\" (2000–4000 m/s). Numerical simulations and high-frequency dynamic pressure test results indicate that the detonation energy is weakest and propagation stability poorest in the \"Random Detonation Wave\" mode, followed by the \"Double Detonation Wave\" mode, with the \"Single Detonation Wave\" mode demonstrating the best performance. Subsequently, relevant operational performance parameters of the rotating detonation wave for the \"Complex Hybrid Detonation Mode\" were proposed. The effects of varying total inlet air temperature, equivalence ratio, and air mass flow rate on the wave characteristics and operational performance of the two-phase kerosene/air RDE were further investigated. Results indicate that the contribution of different \"Detonation wave\" to the overall RDE detonation performance varies with different initial parameters, with the contribution of the \"Double Detonation Wave\" increasing with the rise in the three sets of initial parameters. Furthermore, optimal total inlet air temperature, equivalence ratio, and air flow rate parameters exist for which the RDE exhibits the best performance and stability. Under optimal conditions, the detonation wave velocity reached 1531.5 m/s, with a wave velocity standard deviation of 14.62 %.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110117"},"PeriodicalIF":5.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143548336","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":"Analysis of the dynamic characteristics of the forced start-up procedure of H2O2/ kerosene gas generator cycle rocket engine system","authors":"Yuqi Wei ,&nbsp;Baiyan Wang ,&nbsp;Xianggeng Wei ,&nbsp;Yuanbo He ,&nbsp;Xiao Zhao ,&nbsp;Xueren Wang ,&nbsp;Yuxin Yang","doi":"10.1016/j.ast.2025.110091","DOIUrl":"10.1016/j.ast.2025.110091","url":null,"abstract":"<div><div>The pump-fed H₂O₂ propulsion system is an important direction for future aerospace development, and the start-up process is an accident-prone stage in launch missions. However, the start-up characteristics of the pump-fed H₂O₂/ kerosene liquid rocket engines remain unclear. This paper built the basic components and overall system of a promising H₂O₂/ kerosene gas generator cycle engine system. The dynamic characteristics of the forced start-up procedure were analyzed, and a single factor sensitivity analysis with 9 factors and 9 levels and a multi factor sensitivity analysis with a <span><math><mrow><msub><mi>L</mi><mn>27</mn></msub><mrow><mo>(</mo><msup><mn>3</mn><mn>13</mn></msup><mo>)</mo></mrow></mrow></math></span> orthogonal experiment based on range method were conducted. The distribution, threshold, and reliability of the dynamic processes were also obtained through Monte Carlo method and Pearson <span><math><msup><mi>χ</mi><mn>2</mn></msup></math></span> test. The results show that the parameter settings during the forced start-up process are reasonable, and the coupling between the combustion components and the turbopump is good without overshoot. The pressure inside the main combustion chamber changes steadily and takes about 1 second to reach 95 % of the rated pressure. The maximum temperature in the cooling channel during the start-up process is about 358 K, which is within the safe range. The factors that have the greatest impact on the start-up process include the rotational inertia of the turbopump, the pressure, temperature and molar mass of the start-up gas. The dynamic response time of the start-up process follows a normal distribution, just like the machining error of the components. The point estimation of the reliability of <span><math><msub><mi>t</mi><mn>95</mn></msub></math></span>, which reaches 95 % of the rated thrust, is 0.95297, and the point estimation of the reliability of the valve OGV opening time <span><math><msub><mi>t</mi><mn>4</mn></msub></math></span> is 0.99322. The actual threshold of <span><math><msub><mi>t</mi><mn>95</mn></msub></math></span> is 92.508 %∼107.610 %, and the actual threshold of <span><math><msub><mi>t</mi><mn>4</mn></msub></math></span> is 99.656 %∼100.315 %. These findings will contribute to the design, manufacturing and hot test of H₂O₂/ kerosene gas generator cycle liquid rocket engines.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110091"},"PeriodicalIF":5.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143578495","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":"Efficient modal parameter identification using DMD-DBSCAN and rank stabilization diagrams","authors":"Chengyuan Wu ,&nbsp;Zhichun Yang ,&nbsp;Shun He","doi":"10.1016/j.ast.2025.110112","DOIUrl":"10.1016/j.ast.2025.110112","url":null,"abstract":"<div><div>Modal parameter identification of aerospace structures, particularly improving the efficient using time-domain vibration responses, is currently a topic of great interest in structural dynamics. Data-driven Dynamic Mode Decomposition (DMD) technique in fluid dynamics has shown good potential for identifying the flow mode. In this respect, there have been a few studies on the application of DMD technique in structural dynamics. This paper proposes an efficient structural modal parameter identification method that combines the DMD technique and Density-based Spatial Clustering of Applications with Noise (DBSCAN) algorithm, called the DMD-DBSCAN method. Combined with the proposed rank stabilization diagram, the spurious modes produced by the DMD technique can be effectively cleaned by using DBSCAN algorithm to obtain the physical modal parameter. A numerical case of a composite wing model is presented to validate the proposed method, particularly when identifying the closely spaced modes. It has been shown that the rank stabilization diagram is more appropriate for DMD technique when compared with the solely existing sampling frequency stabilization diagram. An experiment on an aircraft model with response from three-dimensional optical technique is used to demonstrate the method's ability to deal with real complex structures. Compared with traditional methods, results show that the proposed DMD-DBSCAN method can accurately identify modal parameters of complex structures and has excellent operational efficiency because it is free from high order Hankel matrix construction. The proposed data-driven modal parameter identification method is efficient and promising for analysis of complex structures with large datasets.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110112"},"PeriodicalIF":5.0,"publicationDate":"2025-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143578566","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":"Experimental and numerical investigation on the impact response of a riveted structure subjected to bird strike","authors":"Tengfei Ren ,&nbsp;Cunxian Wang ,&nbsp;Yongshuai Wang ,&nbsp;Jintao Wu ,&nbsp;Haodong Wang ,&nbsp;Tao Suo","doi":"10.1016/j.ast.2025.110111","DOIUrl":"10.1016/j.ast.2025.110111","url":null,"abstract":"<div><div>The present study deals with the impact response of a certain type of riveted structure, comprised of three Ti6Al4V plates jointed by ten rivets, under bird strike. At first, bird impact tests were conducted on the riveted structure at different impact velocities. Results indicated that failure mode of the riveted structure manifested as fracture of all the rivets on one side of the structure. And the threshold impact velocity for the current 50-g cylindrical gelatin bird projectile to cause failure of the riveted structure fell within the range of 115 m/s to 127 m/s. In order to realize the utilization of simplified connectors in bird strike simulations in place of actual rivets, a novel connector model incorporating the coupling effects of loading state and loading rate was introduced. Subsequently, based on the force-displacement curves of the currently employed riveted joint under five distinct loading states and three varying loading speeds (5 × 10⁻⁵ m/s, 12 m/s and 17 m/s) reported in preceding study, the capability of this model in characterizing the nonlinear and failure behavior of the riveted joint under complex loading conditions was verified by implementing it into finite element codes. At last, bird impact simulations for the riveted structure were carried out using a simplified model, where the connected plates and rivets were modeled with shell elements and simplified connectors, respectively. Remarkable consistency was observed between the simulations and the experimental results, notably in regards to the threshold impact velocity, high-speed photographs, failure mode and strain responses. Consequently, it is concluded that the present simplification approach for simulating bird strikes on structures incorporating rivets demonstrates exceptional reliability.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110111"},"PeriodicalIF":5.0,"publicationDate":"2025-02-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143548335","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":"Nonlinear model predictive control method for high-speed helicopter power system based on integrated onboard model","authors":"Jie Song ,&nbsp;Yu Chen ,&nbsp;Wenbo Li ,&nbsp;Yong Wang ,&nbsp;Haibo Zhang","doi":"10.1016/j.ast.2025.110093","DOIUrl":"10.1016/j.ast.2025.110093","url":null,"abstract":"<div><div>To mitigate severe fluctuations in engine power turbine speed caused by changes in coaxial rotors, propellers, and aero-surfaces during the mode transition in coaxial high-speed helicopter (CHH), this paper presents a nonlinear model predictive control (NMPC) method for the CHH power system based on an integrated onboard model. Firstly, a digital simulation framework is deployed, incorporating a CHH onboard model based on a T-S fuzzy model and an onboard composite model of variable speed turboshaft engine based on a stacked Long Short-Term Memory-State Variable Model (LSTM-SVM). Subsequently, a nonlinear model predictive control method is devised for the CHH power system. By integrating flight prediction data from the integrated onboard model, an optimized objective function is formulated, taking into account both speed control objectives and the dynamic response characteristics of the turboshaft engine's output shaft. Through rolling optimization and feedback correction methods, real-time optimized control parameters for the turboshaft engine are obtained, ensuring rapid responsiveness in the engine control system. Simulation results demonstrate that the developed integrated onboard model accurately represents the variations in performance parameters during high-speed helicopter flight. Additionally, the nonlinear model predictive control law effectively tracks the variable speed reference commands of the power turbine, maintaining a maximum power turbine speed fluctuation of under 0.46%, thereby significantly enhancing both the engine's response and control quality while preserving computational real-time performance.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110093"},"PeriodicalIF":5.0,"publicationDate":"2025-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143563696","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":"Bird strike resistance analysis for engine fan blade filled with triply periodic minimal surface","authors":"Siqi Wang ,&nbsp;Chuangyu Jiang ,&nbsp;Cunfu Wang ,&nbsp;Baoqiang Zhang ,&nbsp;Huageng Luo ,&nbsp;Wujun Feng","doi":"10.1016/j.ast.2025.110109","DOIUrl":"10.1016/j.ast.2025.110109","url":null,"abstract":"<div><div>The continuous advancement of modern aero engines places higher demands on fan blades, requiring lighter weight without compromising mechanical properties, such as bird strike resistance. The triply periodic minimal surface (TPMS) structure, a lattice structure, has garnered significant attention due to its lightweight, controllable, and excellent mechanical properties. The progress of additive manufacturing (AM) technology has made it possible to use TPMS structures as fillers for fan blades. This study addresses the challenge of impact resistance in wide-chord hollow fan blades and, for the first time, proposes the use of TPMS structures as the filling layer for such blades. Using a multi-level filling structure impact analysis framework, the blade designs are categorized into three levels of simulation and experimental verification, namely, the material-level, the element-level, and the component-level. To reduce the computational cost of numerical simulations, homogenization models were developed for element-level and component-level specimens. The experimental and simulation results show good consistency between the two, while revealing some unique properties of TPMS as the fan blade filling layer. The research demonstrates that TPMS structure has great potential as a new filling core layer for wide-chord hollow fan blades.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110109"},"PeriodicalIF":5.0,"publicationDate":"2025-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143548333","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":"Modeling impact of drones on flat plates","authors":"Jay McNeill ,&nbsp;Randall VanDyk ,&nbsp;C.H.M. Simha ,&nbsp;Azzedine Dadouche ,&nbsp;David Backman ,&nbsp;Manouchehr Nejad Ensan ,&nbsp;Javad Gholipour","doi":"10.1016/j.ast.2025.110103","DOIUrl":"10.1016/j.ast.2025.110103","url":null,"abstract":"<div><div>Experiments on the impact of cannon-launched Phantom DJI 3 quadcopters onto 1-m square aircraft-grade aluminum flat plates (1.6 mm and 6.35 mm thick) at velocities of 130 m/s (250 knots) and 70 m/s (140 knots) are presented, and finite element modeling of the impacts is also described. Load histories at the corners of the plate, central deflection, and possible perforation of the plate are modeled and compared with experimental results. Failure of drone components was modeled, as they were significantly damaged in all of the tests. Failure of the plate was also modeled, as in the high-speed tests with thin plates, the drone perforated the plate. Predictions of the total peak load on the plates are within 20% of the experimental values and the central deflections are within 10% of the experimental values. Additionally, modal analysis reveals that the characteristic half period of 5-6 ms observed in the load histories corresponds to the natural frequencies of the structure that holds the plate in the test. Using the insights gained from the simulations, simple analytical models, wherein the components of the drone are modeled as blunt, rigid objects and the target is modeled as mass and dashpot, were developed. These yield second-order ordinary differential equations whose solutions provide rapid estimates of the peak load and deflection in all tests to within 15% of the experimental values. To estimate the threshold impact velocity to perforate the plate, an analytical model is presented. The major contributions of this article are validated work flows to develop drone finite element models that do not require extensive characterization of drone components, and simplified analytical models for rapid assessment of drone impacts.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110103"},"PeriodicalIF":5.0,"publicationDate":"2025-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143519634","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":"Research on inverse design method of pitching moment for the scramjet nozzle under strong geometric constraint","authors":"Shuhong Tong ,&nbsp;Maotao Yang ,&nbsp;Ye Tian ,&nbsp;Yue Ma ,&nbsp;Jialing Le ,&nbsp;Heng Wang","doi":"10.1016/j.ast.2025.110107","DOIUrl":"10.1016/j.ast.2025.110107","url":null,"abstract":"<div><div>The traditional forward design method of the scramjet nozzle is difficult to obtain good performance under strong geometric constraints. Meanwhile, the existing optimal design methods rarely design from the perspective of the overall torque balance of the engine, and often only take into account the performance of the nozzle itself. This paper introduces an innovative inverse design method for the pitching moment of Single Expansion Ramp Nozzles (SERN). The core of this method integrates the Particle Swarm Optimization (PSO) algorithm with the Grey Wolf Optimization-based Kernel Extreme Learning Machine (GWO-KELM). A high-precision surrogate model of nozzle performance is constructed using a data-driven approach. Based on this surrogate model, performance constraints for PSO are established according to the desired moment. Nozzle design parameters are then iteratively optimized to achieve maximum thrust and minimum moment. The proposed method's effectiveness and accuracy are verified using Computational Fluid Dynamics (CFD). In twelve inverse design experiments, the average absolute percentage error between the designed and expected moment is 0.75 %. Compared to the reference nozzle profile, these designs achieve precise moment control while significantly improving thrust and reducing drag under strict geometric constraints. In conclusion, this paper presents an effective SERN design method, enhancing integration in hypersonic vehicles.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110107"},"PeriodicalIF":5.0,"publicationDate":"2025-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143529679","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":"Two-stage three-dimensional obstacle avoidance and impact angle control guidance law","authors":"Rui Zhao ,&nbsp;Xiang Yu ,&nbsp;Dechuan Wang ,&nbsp;Peng Yao","doi":"10.1016/j.ast.2025.110104","DOIUrl":"10.1016/j.ast.2025.110104","url":null,"abstract":"<div><div>Aiming at the problems of avoiding obstacle and solving impact angle control in terminal guidance in three-dimensional scene, a two-stage guidance law which consists of three-dimensional softmax modified vector field guidance (SMVFG) and sliding mode impact angle control guidance (SMIACG) is proposed in this paper. In the first stage, the three-dimensional SMVFG law is designed to avoid static obstacles encountered in terminal guidance. In the second stage, the three-dimensional SMIACG law is designed to control the impact angle of the terminal under the premise of ensuring zero miss distance. Furthermore, the accessibility and safety of the whole guidance process are proved theoretically. Several numerical simulations are carried out to verify the accessibility and safety of the proposed guidance laws in different scenarios.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110104"},"PeriodicalIF":5.0,"publicationDate":"2025-02-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143535291","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}