Aerospace Science and Technology最新文献

{"title":"Dynamic response reconstruction for variable-mode aerospace structures","authors":"Bin Xia,&nbsp;Tianming Cheng,&nbsp;Cheng Wei,&nbsp;Bindi You","doi":"10.1016/j.ast.2025.110170","DOIUrl":"10.1016/j.ast.2025.110170","url":null,"abstract":"<div><div>Due to continuous changes in dynamic parameters and modal characteristics of spatial structures caused by spatial environment effects, the reconstruction and prediction of structural responses based on a time-invariant model are rendered challenging. To enable accurate reconstruction of responses of on-orbit engineering targets using continuously updated dynamic models, a dynamic response reconstruction method is introduced in this paper, which integrates the Finite Element Model (FEM) with Long Short-Term Memory (LSTM) neural networks. The parameters requiring updates are determined through adjoint sensitivity analysis. A neural network is utilized to establish a mapping between structural responses and parameters subject to updates. Frequency modulation is employed for effective mode separation during signal processing. The dynamic response reconstruction is conducted within the framework of the modal superposition method. A spatial truss and a planar antenna are selected as subjects for numerical analysis, and the outcomes are compared with those obtained from the traditional response reconstruction method. Ultimately, ground testing and verification using motion capture systems validate that improved reconstruction accuracy is provided for variable-mode aerospace structures by the proposed method.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110170"},"PeriodicalIF":5.0,"publicationDate":"2025-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143760237","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":"Effects of boundary layer transition on the vane heat transfer in an integrated intermediate turbine duct","authors":"Ziyu Kang ,&nbsp;Tayyab Raza Shah ,&nbsp;Meijie Zhang ,&nbsp;Chao Zhou","doi":"10.1016/j.ast.2025.110161","DOIUrl":"10.1016/j.ast.2025.110161","url":null,"abstract":"<div><div>As the inlet gas temperature of the high-pressure turbine further increases, the heat transfer of the intermediate turbine duct, which connects the high-pressure and low-pressure turbines, should also be considered. This paper investigates the heat transfer characteristics of the vane in an integrated intermediate turbine duct (IITD) by experimental, numerical, and analytical methods. The vane surface laminar-turbulent transition is found to have a key effect on the heat transfer of the vane. The surface heat transfer coefficient of the turbulent boundary layer after transition is <strong>more than twice higher than that of a laminar boundary layer.</strong> It is found that the acceleration features in the IITD can influence the flow transition and are accurately captured by the <span><math><mrow><mi>γ</mi><mo>−</mo><mi>R</mi><msub><mi>e</mi><mi>θ</mi></msub></mrow></math></span> model. A novel correlation related to the boundary layer transition of the IITD vane is proposed to predict the local Nusselt number on the vane and can reduce the time consumption for the heat transfer prediction by about <span><math><mrow><mn>1</mn><mo>/</mo><mn>4</mn></mrow></math></span>.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110161"},"PeriodicalIF":5.0,"publicationDate":"2025-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143792644","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":"Thermo-chemical non-equilibrium flows and aerodynamic loads of Type III shock/shock interaction on blunted lip of a Mach 12 inlet","authors":"Dengke Li ,&nbsp;Bo Sun ,&nbsp;Chunliang Dai ,&nbsp;Xiong Chen ,&nbsp;Yanjin Man","doi":"10.1016/j.ast.2025.110168","DOIUrl":"10.1016/j.ast.2025.110168","url":null,"abstract":"<div><div>The aerothermal challenges are often accentuated by shock/shock interactions (SSI) in the hypervelocity flow. Due to the small scale, the blunted inlet lip is likely to encounter an extremely harsh thermal environment among the components of an airbreathing vehicle. In the present study, an open-source solver named hy2Foam is used to obtain the unexplored flow characteristics of small-scale Type IIIa SSI at Mach 12 with incident shock angle <span><math><mi>β</mi></math></span> of <span><math><msup><mn>12</mn><mo>∘</mo></msup></math></span>, <span><math><msup><mn>15</mn><mo>∘</mo></msup></math></span> and <span><math><msup><mn>18</mn><mo>∘</mo></msup></math></span>. The transition from Type III to Type IV SSI is observed with the increase of dimensionless intercept <span><math><msub><mi>I</mi><mi>r</mi></msub></math></span>. Different from the results in the previous study, the shear layer in Type IIIa SSI doesn't directly attach but deflects twice before the final attachment. This phenomenon stems from the coupling between the shear layer attachment process and the shock wave/shear layer interaction. As <span><math><msub><mi>I</mi><mi>r</mi></msub></math></span> increases, the Mach reflection (MR) within Type IIIa SSI can transform to regular reflection (RR) owing to the decrease of the first deflection angle of shear layer, and the flows remain steady during the transition process from Type IIIa SSI to Type IV SSI. The flow within a valley region between the shear layer and the cylinder surface is the closest to thermal equilibrium and chemical equilibrium in the whole flow field. Due to the strong recompression shock generated by the final attachment of the shear layer, the peak of pressure and heat transfer at the critical state transitioning from Type IIIa to Type IV SSI is the highest for Type IIIa SSI, achieving 30.8 and 40.08 times to the stagnation values in undisturbed flow, respectively. Finally, a new power-law correlation between pressure and heat transfer intensifications for Type III SSI on the blunted lip of a Mach 12 inlet is obtained. Those insights in this research are poised to provide a reference for the thermal protection design of high Mach number inlets.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110168"},"PeriodicalIF":5.0,"publicationDate":"2025-03-26","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143746876","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":"Supersonic combustion flow field reconstruction in a scramjet based on deep learning method","authors":"Shicai Huang ,&nbsp;Ye Tian ,&nbsp;Xue Deng ,&nbsp;Maotao Yang ,&nbsp;Erda Chen ,&nbsp;Hua Zhang","doi":"10.1016/j.ast.2025.110169","DOIUrl":"10.1016/j.ast.2025.110169","url":null,"abstract":"<div><div>Efficiently predicting combustion flow in scramjet engines enhances early state awareness, which is crucial for facilitating active flow control and ensuring reliable and stable engine operation. Aiming at the problem that the traditional optical test method of ground wind tunnel test is limited by complex and narrow space and difficult to obtain data, the study introduces a supersonic flow field reconstruction model that utilizes local-global feature grouping and fusion to realize fast reconstruction of flow field schlieren image based on sparse pressure data obtained by tiny wall pressure sensor. To prevent the loss of many shallow gradients in the transmission process, a two-layer gradient calculation strategy is designed to preserve the shallow gradient features to the maximum extent. To reduce the number of model parameters and enhance the information crafty interaction between different flow fields, a binary segmentation mask strategy is designed to transform the image dimensionality and block. To assess the effectiveness of the proposed model, experiments were conducted using hydrogen fuel combustion test data obtained from a pulse combustion wind tunnel with an inflow Mach number of 2.5. When compared to other models, our model demonstrated a significant 14.37 % improvement in structural similarity and an 8.35 % improvement in peak signal-to-noise ratio indicators. Most notably, these improvements were achieved while maintaining the lowest computational complexity.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110169"},"PeriodicalIF":5.0,"publicationDate":"2025-03-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143725414","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":"Prescribed-time fault-tolerant tracking control for quadrotor UAV with guaranteed performance","authors":"Miaomiao Tian ,&nbsp;Nan Wang ,&nbsp;Zhikai Wang ,&nbsp;Zhumu Fu ,&nbsp;Fazhan Tao","doi":"10.1016/j.ast.2025.110162","DOIUrl":"10.1016/j.ast.2025.110162","url":null,"abstract":"<div><div>During the actual flight of unmanned aerial vehicle (UAV), there are widespread actuator faults, system uncertainties and external disturbances, which bring significant threats to its steady flight. This paper studies the problem of prescribed-time fault-tolerant tracking control for quadrotor UAV with guaranteed performance. By integrating error reconstruction and dynamic adjustment strategies, this paper ensures that the position and attitude tracking errors converge to the preset performance range within the prescribed time. Furthermore, this paper utilizes the disturbance observer failure compensation method to simultaneously handle the multiplicative and additive failures of the actuator simultaneously, and presents a nonlinear observer-based adaptive strategy to estimate additive faults and unknown external disturbances acting on the UAV. Simulation results show that the position and attitude tracking errors converge to the preset accuracy within the prescribed time without actuator failures. When actuator failures occur, the attitude tracking error still converges on time, and the convergence rate of position error is minimally affected. Thus, the proposed control algorithm for quadrotor UAV is validated.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110162"},"PeriodicalIF":5.0,"publicationDate":"2025-03-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143704200","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":"Fuel stratification effects on thermoacoustic instability for swirl spray flame in an aero-engine centrally-staged combustor","authors":"Ziyu Qin ,&nbsp;Heng Song ,&nbsp;Xiao Han ,&nbsp;Lei Li ,&nbsp;Yuzhen Lin ,&nbsp;Liangliang Xu","doi":"10.1016/j.ast.2025.110163","DOIUrl":"10.1016/j.ast.2025.110163","url":null,"abstract":"<div><div>The centrally-staged combustor features a flexible radial fuel stratification to achieve well-organized energy utilization but still faces serious thermoacoustic instability. In this study, we conducted experiments with four stratification ratios (SRs) under the realistic stratified swirl spray flame configuration. The stratification effect on thermoacoustic instability is investigated using the 20 kHz simultaneous PIV and CH₂O-PLIF optical diagnostic. The combustor is prone to severe thermoacoustic oscillation at lower SR, in which the pressure fluctuation substantially follows the heat release dynamic with a short time delay. At higher SR, the relative phase between them becomes irregular accompanied by intermittent oscillations. Two types of flame dynamics are found. The heat release region features an axial mode for lower SR, while it presents the transverse oscillation which destroys the thermoacoustic coupling for higher SR. Further, a coupling metric quantifying the similarity between the vortex probability distribution and flame surface density is proposed to measure the vortex-flame coupling. The highest value for the lowest SR is attributed to the strong flame-flow interaction downstream of the primary recirculation zone, which contributes to the unsteady heat release. Finally, it is found that the local flame stabilization is similar to the counterflow flame.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110163"},"PeriodicalIF":5.0,"publicationDate":"2025-03-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143746874","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":"Investigations on the competition between acoustic and intrinsic thermoacoustic modes due to multi-flame interaction","authors":"Siyi Zhang ,&nbsp;Xiaokang Liu ,&nbsp;Yu Tian ,&nbsp;Dongbin Wang ,&nbsp;Jingxuan Li ,&nbsp;Lijun Yang","doi":"10.1016/j.ast.2025.110159","DOIUrl":"10.1016/j.ast.2025.110159","url":null,"abstract":"<div><div>Thermoacoustic instabilities typically consist of two modes: the acoustic instability mode and the intrinsic thermoacoustic (ITA) mode. These modes can coexist and compete under certain conditions within a combustor. This paper investigates the impact of multi-flame interaction on mode competition within a model combustor – a length-adjustable Rijke tube. Mode competition was explored by independently varying the chamber's acoustic characteristics (via Rijke tube length) and the multi-flame response characteristics (through injector hole distribution). The thermoacoustic response of the multi-flame system was examined using an acoustic pressure sensor and CH* chemiluminescence technique. The dynamic properties of the multi-flame flow field were captured with a high-speed camera and particle image velocimetry (PIV). Results showed that different multi-flame interactions can alter the flame transfer function (FTF), leading to combustion instability dominated by either the acoustic mode or the ITA mode. The experimental results were combined with a low-order acoustic network model (LOM) to study the transition and competition between acoustic and ITA instability under multi-flame interactions. The predictions of the LOM for the eigenfrequencies and growth rates of the combustion system can accurately describe the occurrence trend of the acoustic and ITA modes.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110159"},"PeriodicalIF":5.0,"publicationDate":"2025-03-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143746873","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":"Composite anti-unwinding sliding mode attitude tracking control for rigid spacecraft: A prescribed-time method","authors":"Haibin Sun ,&nbsp;Yi Xu ,&nbsp;Linlin Hou ,&nbsp;Dong Yang ,&nbsp;Ticao Jiao","doi":"10.1016/j.ast.2025.110158","DOIUrl":"10.1016/j.ast.2025.110158","url":null,"abstract":"<div><div>This study addresses the prescribed-time anti-unwinding attitude tracking control problem for a rigid spacecraft. First, a prescribed-time sliding mode disturbance observer is designed to estimate the disturbances. To ensure prescribed-time convergence and avoid the unwinding phenomenon, a new prescribed-time sliding mode surface is established by introducing a hyperbolic sine function such that the designed sliding surface includes two equilibrium points. Subsequently, an attitude tracking control law with a disturbance compensation term is designed to guarantee that the system states converge to the sliding surface in a prescribed-time. The simulation results reveal that anti-unwinding prescribed-time attitude tracking of a rigid spacecraft can be achieved by using the developed attitude control law.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110158"},"PeriodicalIF":5.0,"publicationDate":"2025-03-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143687627","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":"Study on the interaction mechanism between incident oblique shock wave and transpiration cooling and optimization of porosity","authors":"Xiaojuan Wang,&nbsp;Xiaoqiang Fan,&nbsp;Bing Xiong","doi":"10.1016/j.ast.2025.110154","DOIUrl":"10.1016/j.ast.2025.110154","url":null,"abstract":"<div><div>Transpiration cooling, due to its high cooling efficiency, is used for thermal protection in hypersonic aircraft. However, oblique shock waves incident on a structural surface can reduce cooling effectiveness, risking thermal protection failure. Additionally, the cooling film changes the wave structure in the main flow, reducing the aerodynamic performance. This study employs numerical methods to analyze the effects of oblique shock waves on transpiration cooling at various shock incidence angles and coolant blowing ratios, as well as the influence of transpiration cooling on the main flow field. The cooling efficiency curve is segmented into four intervals based on the flow mechanisms, with the corresponding optimization objectives proposed. A segmented porosity design method driven by pressure difference is adopted, improving the surface temperature uniformity at the hot end of the transpiration zone by 82.7%.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"161 ","pages":"Article 110154"},"PeriodicalIF":5.0,"publicationDate":"2025-03-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143685461","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":"Kriging-assisted valid-screening optimization (KVSO) to study optimal steering strategies for multi-struts aircraft","authors":"XiaZheng Shi ,&nbsp;Hong Nie ,&nbsp;Ming Zhang ,&nbsp;XiWen Gui ,&nbsp;YuTing Zheng ,&nbsp;YuHan Xu ,&nbsp;TianYang Hu","doi":"10.1016/j.ast.2025.110157","DOIUrl":"10.1016/j.ast.2025.110157","url":null,"abstract":"<div><div>During ground maneuvering of multi-strut aircraft (MSA), certain main landing gears (MLGs) require steering capabilities to coordinate with the nose landing gears (NLGs) for minimizing steering radius and maintaining stability. Inappropriate MLG steering angles may lead to tire sideslip and potential aircraft rollover in extreme cases. This article presents a Kriging-assisted valid-screening optimization (KVSO) method for predicting optimal steering strategies of MSA under complex constraints, determining optimal coordination angles for the MLGs. The proposed method first introduces a penalty-based pre-screening filter (PBPF) mechanism that selects samples by comprehensively evaluating multiple constraint violations, thereby enhancing the algorithm's optimization efficiency. Subsequently, a valid constraint screening (VCS) mechanism, based on normal distribution principles, is proposed to reduce computational costs. Furthermore, a region of interest sampling surrogate model update mechanism is developed based on the constraint boundary sampling (CBS) criterion. This mechanism constructs high-precision surrogate models for both optimization objective regions and constraint boundaries, thus accelerating global optimization convergence. The effectiveness of the proposed method is validated through two engineering case studies. The results demonstrate superior computational efficiency and optimization accuracy in resolving the optimal steering strategy for MSA. This method provides theoretical foundations for MLGs steering angle design.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"162 ","pages":"Article 110157"},"PeriodicalIF":5.0,"publicationDate":"2025-03-22","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143863644","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}