Aerospace Science and Technology最新文献

Aerothermal performance of different relative positions of holes and ribs of a flat-plate film cooling hole with a straight-ribbed crossflow coolant channel

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-03-06 DOI: 10.1016/j.ast.2025.110114

Shouzuo Li , Xiangyu Wang , Qiankun He , Songtao Wang , Le Cai

The integration of internally ribbed cooling channels with external film cooling is a widely adopted cooling technique for gas turbines. This study numerically investigated the effects of different relative positions of holes/ribs on the flow and heat transfer characteristics of cylindrical film-cooling holes. Nine film-cooling hole position cases, two crossflow Reynolds numbers (Re = 200,000−600,000), and four blowing ratios (M = 0.5 − 2.0) were considered. All cases used the ribbed crossflow supply method with a rib height of 0.4 D. We analyzed the change rule in the cooling performance and discharge coefficients with the relative positions of holes/ribs. In addition, we analyzed the mechanism contributing to relevant changes from the perspectives of the structure of the flow field inside and outside the holes, as well as the aerodynamic and heat transfer characteristics. The relative positions of the holes/ribs exerted a more pronounced impact at high crossflow Reynolds numbers. Across the entire range of operating conditions, positions 6 and 9 demonstrated the highest film-cooling performance and discharge coefficient, respectively. When the crossflow Reynolds number was relatively high and the blowing ratio was 1.0, the difference in the film-cooling efficiency between positions 6 and 8 was 45.9 %, which increased to 88.1 % at a blowing ratio of 2.0. Hence, the relative positions of film-cooling holes affect the degree to which the holes are affected by the crossflow, which consequently affects the flow-field structure and aerothermal properties. This research aids in achieving refinement and integration in the design of turbine blade cooling structures.

{"title":"Aerothermal performance of different relative positions of holes and ribs of a flat-plate film cooling hole with a straight-ribbed crossflow coolant channel","authors":"Shouzuo Li , Xiangyu Wang , Qiankun He , Songtao Wang , Le Cai","doi":"10.1016/j.ast.2025.110114","DOIUrl":"10.1016/j.ast.2025.110114","url":null,"abstract":"<div><div>The integration of internally ribbed cooling channels with external film cooling is a widely adopted cooling technique for gas turbines. This study numerically investigated the effects of different relative positions of holes/ribs on the flow and heat transfer characteristics of cylindrical film-cooling holes. Nine film-cooling hole position cases, two crossflow Reynolds numbers (<em>Re</em> = 200,000−600,000), and four blowing ratios (M = 0.5 − 2.0) were considered. All cases used the ribbed crossflow supply method with a rib height of 0.4 D. We analyzed the change rule in the cooling performance and discharge coefficients with the relative positions of holes/ribs. In addition, we analyzed the mechanism contributing to relevant changes from the perspectives of the structure of the flow field inside and outside the holes, as well as the aerodynamic and heat transfer characteristics. The relative positions of the holes/ribs exerted a more pronounced impact at high crossflow Reynolds numbers. Across the entire range of operating conditions, positions 6 and 9 demonstrated the highest film-cooling performance and discharge coefficient, respectively. When the crossflow Reynolds number was relatively high and the blowing ratio was 1.0, the difference in the film-cooling efficiency between positions 6 and 8 was 45.9 %, which increased to 88.1 % at a blowing ratio of 2.0. Hence, the relative positions of film-cooling holes affect the degree to which the holes are affected by the crossflow, which consequently affects the flow-field structure and aerothermal properties. This research aids in achieving refinement and integration in the design of turbine blade cooling structures.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110114"},"PeriodicalIF":5.0,"publicationDate":"2025-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143548341","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}

引用次数: 0

Numerical investigation of the velocity-coupled response of propellant burning rate in a solid rocket motor

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-03-04 DOI: 10.1016/j.ast.2025.110118

Guanyu Xu , Bing Wang , Peijin Liu , Yu Guan

Serving as one of the primary gain sources in solid rocket motors, the burning rate response crucially determines the properties of combustion instability, which, however, still remains largely unexplored, particularly velocity-coupled burning rate response. This numerical study integrates a microscopic sandwich flame model with a macroscopic rocket internal flow field, considering the gas-solid coupling process, to investigate the velocity-coupled burning rate response of solid propellants subjected to transverse acoustic forcing in a solid rocket motor. The oscillatory flow field and flame dynamics are first analyzed, examining the variation pattern of velocity fluctuation amplitude with frequency near the burning surface and the disturbance source characteristics of the flame. Subsequently, both the pressure-coupled response function (

R_{p}

) and the velocity-coupled response function (

R_{v}

) are derived to investigate the frequency response of the burning rate.

R_{v}

peaks in the second acoustic mode, potentially clarifying why the second harmonic frequently exhibits the highest amplitude in the combustion instability of real solid rocket motors. The phase relationship between velocity and flame heat release fluctuations in space is analyzed, explaining the response mechanism of burning rate to the velocity oscillation frequency. The impact of oxidizer particle sizes on

R_{v}

is also explored. Smaller oxidizer particle sizes lead to a shift in the peak of

R_{v}

towards higher harmonics, emphasizing the crucial role of reaction diffusion distance in velocity-coupled responses. Our work introduces a novel approach to studying propellant burning responses, particularly addressing the gap in numerical studies of velocity-coupled responses, potentially leading to enhanced understanding and control of combustion instability.

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引用次数: 0

Physical investigation on the sound transmission loss of heterogeneous metastructures using wave-based methodologies

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-03-03 DOI: 10.1016/j.ast.2025.110110

Dongze Cui , Mohamed Ichchou , Noureddine Atalla , Abdel-Malek Zine

Existing methodologies employed for computing acoustic indicators of heterogeneous metastructures have limitations in terms of accuracy and efficiency, especially for metastructures showing complex phenomenon that involves the interaction between different wavetypes (flexural, shear, and high-order waves), which significantly influences the sound transmission characteristics of the structure. The present study focuses on providing an efficient wave-based methodology to study the wave coupling effect and the accurate estimation of Sound Transmission Loss (STL) of these metastructures. It develops the Wave Finite Element (WFE) scheme to compute the STL by applying a plane wave excitation from the ambient fluid domain to a representative Unit Cell (UC) of the periodic structures, this methodology is also exploited to study the sophisticated phenomena of wave coupling on the accurate computation of acoustic indicators. STL under Diffuse Acoustic Field (DAF) is computed by integrating the wave STL over all possible incidence angles. Various configurations, laminated glass with Polyvinyl Butyral (PVB) core, sandwich plates with a Shape Memory Polymer (SMP) core, sandwich plates with a thick soft core, Cross-Laminated Timber (CLT) plate, and a curved structure configuration, are presented to highlight the advantages of the proposed wave-based methodology for investigating the physics of sound transmission in heterogeneous metastructures.

{"title":"Physical investigation on the sound transmission loss of heterogeneous metastructures using wave-based methodologies","authors":"Dongze Cui , Mohamed Ichchou , Noureddine Atalla , Abdel-Malek Zine","doi":"10.1016/j.ast.2025.110110","DOIUrl":"10.1016/j.ast.2025.110110","url":null,"abstract":"<div><div>Existing methodologies employed for computing acoustic indicators of heterogeneous metastructures have limitations in terms of accuracy and efficiency, especially for metastructures showing complex phenomenon that involves the interaction between different wavetypes (flexural, shear, and high-order waves), which significantly influences the sound transmission characteristics of the structure. The present study focuses on providing an efficient wave-based methodology to study the wave coupling effect and the accurate estimation of Sound Transmission Loss (STL) of these metastructures. It develops the Wave Finite Element (WFE) scheme to compute the STL by applying a plane wave excitation from the ambient fluid domain to a representative Unit Cell (UC) of the periodic structures, this methodology is also exploited to study the sophisticated phenomena of wave coupling on the accurate computation of acoustic indicators. STL under Diffuse Acoustic Field (DAF) is computed by integrating the wave STL over all possible incidence angles. Various configurations, laminated glass with Polyvinyl Butyral (PVB) core, sandwich plates with a Shape Memory Polymer (SMP) core, sandwich plates with a thick soft core, Cross-Laminated Timber (CLT) plate, and a curved structure configuration, are presented to highlight the advantages of the proposed wave-based methodology for investigating the physics of sound transmission in heterogeneous metastructures.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110110"},"PeriodicalIF":5.0,"publicationDate":"2025-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143548342","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}

引用次数: 0

Aeroacoustics evaluation and mechanism of Krueger flap

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-03-02 DOI: 10.1016/j.ast.2025.110085

Jiamin Xie , Xiaoquan Yang , Jue Ding , Peifen Weng

Noise generated by high-lift devices is a major contributor to aircraft noise during approach and landing. Most published research on high-lift device noise focuses on slat configurations, with noise reduction measures applied to mitigate slat noise, such as droop nose devices or long-chord slat devices. Another alternative for laminar-flow wing technology is the Krueger leading-edge flap. In this study, numerical simulations were conducted to analyze the flow field, noise sources, and detailed characteristics around a high-lift Krueger flap configuration, including both a baseline configuration with a Krueger storage cavity and a configuration without the cavity. Far-field noise propagation was calculated using the Ffowcs Williams-Hawkings equation. The results indicate that the baseline configuration with the cavity exhibited strong tonal noise at low frequencies, while the cavity's influence on the Krueger flap noise was primarily in the form of broadband noise within the mid-to-high frequency range. The impact of angle-of-attack variations on overall noise was also studied, revealing that changes in the angle of attack significantly affected the flow field around the Krueger flap and its slot region. However, the impact of the cavity on the downstream flow field and noise is not significant. Notably, a substantial reduction in Krueger flap noise was observed at specific angles of attack, which is a factor that is essential in the study of noise associated with actual aircraft.

{"title":"Aeroacoustics evaluation and mechanism of Krueger flap","authors":"Jiamin Xie , Xiaoquan Yang , Jue Ding , Peifen Weng","doi":"10.1016/j.ast.2025.110085","DOIUrl":"10.1016/j.ast.2025.110085","url":null,"abstract":"<div><div>Noise generated by high-lift devices is a major contributor to aircraft noise during approach and landing. Most published research on high-lift device noise focuses on slat configurations, with noise reduction measures applied to mitigate slat noise, such as droop nose devices or long-chord slat devices. Another alternative for laminar-flow wing technology is the Krueger leading-edge flap. In this study, numerical simulations were conducted to analyze the flow field, noise sources, and detailed characteristics around a high-lift Krueger flap configuration, including both a baseline configuration with a Krueger storage cavity and a configuration without the cavity. Far-field noise propagation was calculated using the Ffowcs Williams-Hawkings equation. The results indicate that the baseline configuration with the cavity exhibited strong tonal noise at low frequencies, while the cavity's influence on the Krueger flap noise was primarily in the form of broadband noise within the mid-to-high frequency range. The impact of angle-of-attack variations on overall noise was also studied, revealing that changes in the angle of attack significantly affected the flow field around the Krueger flap and its slot region. However, the impact of the cavity on the downstream flow field and noise is not significant. Notably, a substantial reduction in Krueger flap noise was observed at specific angles of attack, which is a factor that is essential in the study of noise associated with actual aircraft.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110085"},"PeriodicalIF":5.0,"publicationDate":"2025-03-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143526635","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}

引用次数: 0

An intelligent prediction method for supersonic flow field in scramjet isolator enhanced by feature details

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-03-02 DOI: 10.1016/j.ast.2025.110116

Ye Tian , Yitong Zhao , Xue Deng , Maotao Yang , Erda Chen , Mengqi Xu , Hu Ren

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.

{"title":"An intelligent prediction method for supersonic flow field in scramjet isolator enhanced by feature details","authors":"Ye Tian , Yitong Zhao , Xue Deng , Maotao Yang , Erda Chen , Mengqi Xu , 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}

引用次数: 0

The influence of different initial parameters on the operational characteristics of a Kerosene/air two-phase rotating detonation engine

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-03-01 DOI: 10.1016/j.ast.2025.110117

Xiafei Li , Jianzhong Li , Wu Jin , Qian Yao , Qiongyao Qin , Li Yuan

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 %.

{"title":"The influence of different initial parameters on the operational characteristics of a Kerosene/air two-phase rotating detonation engine","authors":"Xiafei Li , Jianzhong Li , Wu Jin , Qian Yao , Qiongyao Qin , 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}

引用次数: 0

Experimental and numerical investigation on the impact response of a riveted structure subjected to bird strike

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-28 DOI: 10.1016/j.ast.2025.110111

Tengfei Ren , Cunxian Wang , Yongshuai Wang , Jintao Wu , Haodong Wang , Tao Suo

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.

{"title":"Experimental and numerical investigation on the impact response of a riveted structure subjected to bird strike","authors":"Tengfei Ren , Cunxian Wang , Yongshuai Wang , Jintao Wu , Haodong Wang , 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<sup>−5</sup> 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}

引用次数: 0

Modeling impact of drones on flat plates

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-27 DOI: 10.1016/j.ast.2025.110103

Jay McNeill , Randall VanDyk , C.H.M. Simha , Azzedine Dadouche , David Backman , Manouchehr Nejad Ensan , Javad Gholipour

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.

{"title":"Modeling impact of drones on flat plates","authors":"Jay McNeill , Randall VanDyk , C.H.M. Simha , Azzedine Dadouche , David Backman , Manouchehr Nejad Ensan , 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}

引用次数: 0

Bird strike resistance analysis for engine fan blade filled with triply periodic minimal surface

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-27 DOI: 10.1016/j.ast.2025.110109

Siqi Wang , Chuangyu Jiang , Cunfu Wang , Baoqiang Zhang , Huageng Luo , Wujun Feng

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.

{"title":"Bird strike resistance analysis for engine fan blade filled with triply periodic minimal surface","authors":"Siqi Wang , Chuangyu Jiang , Cunfu Wang , Baoqiang Zhang , Huageng Luo , 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}

引用次数: 0

Research on inverse design method of pitching moment for the scramjet nozzle under strong geometric constraint

IF 5 1区工程技术 Q1 ENGINEERING, AEROSPACE

Aerospace Science and Technology

Pub Date : 2025-02-27 DOI: 10.1016/j.ast.2025.110107

Shuhong Tong , Maotao Yang , Ye Tian , Yue Ma , Jialing Le , Heng Wang

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.

{"title":"Research on inverse design method of pitching moment for the scramjet nozzle under strong geometric constraint","authors":"Shuhong Tong , Maotao Yang , Ye Tian , Yue Ma , Jialing Le , 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}

引用次数: 0