Aerospace Science and Technology最新文献_第8页

Prediction of pressure distribution and aerodynamic coefficients for a variable-sweep wing 预测变掠翼的压力分布和空气动力系数

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-31 DOI: 10.1016/j.ast.2024.109706

Yuqi Lei , Xiaomin An , Yihua Pan , Yue Zhou , Qi Chen

{"title":"Prediction of pressure distribution and aerodynamic coefficients for a variable-sweep wing","authors":"Yuqi Lei , Xiaomin An , Yihua Pan , Yue Zhou , Qi Chen","doi":"10.1016/j.ast.2024.109706","DOIUrl":"10.1016/j.ast.2024.109706","url":null,"abstract":"<div><div>To satisfy the performance requirements across multiple speed ranges, a variable-sweep wing (sweep angle range from 25° to 40°) is derived from the BQM-34 “Firebee” drone model. However, predicting aerodynamic characteristics across various flight conditions and sweep angles is a challenging task. Traditional methods like CFD and wind tunnel testing are both time consuming and expensive. In order to efficiently predict the pressure distributions and aerodynamic coefficients, a novel network that combines a Radial Basis Function Network (RBFN) and a Convolutional Auto-Encoder (CAE) is proposed. Two distinct loss function methods, the standard Pressure-Targeted Method (PTM) and the newly developed Comprehensive Evaluation Method (CEM), are employed to optimize the network's predictive performance. These methods are evaluated on datasets with both trained and untrained sweep angles. The results show that while both PTM and CEM accurately predict pressure distributions, the enhanced CEM provides more uniform and reliable predictions. Moreover, the CEM method significantly outperforms PTM in predicting aerodynamic coefficients, reducing errors by over 50%. The proposed RBFN-CAE network with the CEM loss function offers an effective way to predict the aerodynamic characteristics of a variable-sweep wing, improving predictive models in aerodynamic applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109706"},"PeriodicalIF":5.0,"publicationDate":"2024-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142586304","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 study on loss and flow mechanism of variable stator vanes in high-pressure compressor with bleed 带排气的高压压缩机中可变定子叶片的损耗和流动机理的实验研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-31 DOI: 10.1016/j.ast.2024.109686

Chen Xu, Shaowen Chen, Zehao Li

{"title":"Experimental study on loss and flow mechanism of variable stator vanes in high-pressure compressor with bleed","authors":"Chen Xu, Shaowen Chen, Zehao Li","doi":"10.1016/j.ast.2024.109686","DOIUrl":"10.1016/j.ast.2024.109686","url":null,"abstract":"<div><div>In modern compressors, variable stator vanes are increasingly utilized. These vanes require a specific gap between their leading and trailing edges and the casing/hub to prevent contact during rotation. For multi-stage axial compressors employing variable stator vanes, understanding the impact of clearance variations on compressor performance is crucial during design. This study focuses on experimental research conducted on a high-pressure compressor equipped with variable stator vanes and bleed, using a real engine structure. The investigation delves into the loss characteristics and flow mechanisms within the variable mechanism's flow field. Results show that, with the identical penny diameter, increasing radial clearance initially decreases flow field loss, but then loss rises, reaching a minimum with a 2 mm (1.25% blade height) clearance. Conversely, with the same radial clearance, increasing penny diameter initially increases loss, which then decreases, with larger penny diameters resulting in smaller losses. Based on these findings, it can be inferred that a clearance of around 2 mm substantially reduces losses within the vane. Losses within 0–10% of the blade height from the endwall mainly stem from penny leakage vortex and their interaction with passage vortex, while losses within 10–20% of the blade height primarily arise from passage vortex, thus mitigating overall losses. The study demonstrates that, compared to zero-clearance vanes, variable stator vanes with a partial gap resulted in lower total pressure losses and better flow field control.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109686"},"PeriodicalIF":5.0,"publicationDate":"2024-10-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142552909","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

Fast aerodynamic analysis method for three-dimensional morphing wings based on deep learning 基于深度学习的三维变形机翼快速气动分析方法

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-29 DOI: 10.1016/j.ast.2024.109690

Ruolong Xie , Zhiqiang Wan , De Yan , Wenwei Qiu

引用次数: 0

Closed-loop AI-aided image-based GNC for autonomous inspection of uncooperative space objects 基于图像的闭环人工智能辅助 GNC，用于自主检测不合作的空间物体

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-29 DOI: 10.1016/j.ast.2024.109700

Andrea Brandonisio , Michele Bechini , Gaia Letizia Civardi, Lorenzo Capra, Michèle Lavagna

引用次数: 0

Numerical study of aluminum combustion with agglomerate size distribution in solid rocket motor 固体火箭发动机中带有结块粒度分布的铝燃烧数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-28 DOI: 10.1016/j.ast.2024.109696

He Chen , Wenjing Yang , Qingyun Sheng , Huangpeng Wang , Yan Ba , Peijin Liu , Wen Ao

{"title":"Numerical study of aluminum combustion with agglomerate size distribution in solid rocket motor","authors":"He Chen , Wenjing Yang , Qingyun Sheng , Huangpeng Wang , Yan Ba , Peijin Liu , Wen Ao","doi":"10.1016/j.ast.2024.109696","DOIUrl":"10.1016/j.ast.2024.109696","url":null,"abstract":"<div><div>The aluminum agglomerate size distribution plays an important role in influencing the particle distributed combustion in motor, which subsequently affects the performance of solid rocket motor significantly. In this work, a three-phase model to describe distributed combustion of aluminum agglomerates is established based on the Eulerian-Lagrangian method. Then, the agglomerate size, including mono size and distributed size, is studied to reveal its effect on aluminum combustion and motor flow field. The simulated results indicate that the increasing agglomerate mono size observes the obvious decrease of the average temperature inside the motor combustion chamber, implying the low combustion efficiency of large agglomerate size. When considering the agglomerate size distribution, the size distribution mode and the mean size <em>D</em><sub>43</sub> determine the combustion efficiency together. In particular, even the mean size is similar, with different distribution mode, like skewed distribution, bimodal or trimodal distribution, the combustion efficiency and flow field parameters are nonnegligible different. However, when the size distribution mode is the same and the peak range is similar, the mean size <em>D</em><sub>43</sub> becomes the only and predominant factor as the mono size.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109696"},"PeriodicalIF":5.0,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142571523","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 study on the mechanism of leakage flow influence on the performance of high-speed diffuser cascade 泄漏流对高速扩散器级联性能影响机理的实验和数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-28 DOI: 10.1016/j.ast.2024.109698

Tianshuo Huang , Xiaozhi Kong , Huawei Lu , Zhengyang Dong , Pengwei Fan

{"title":"Experimental and numerical study on the mechanism of leakage flow influence on the performance of high-speed diffuser cascade","authors":"Tianshuo Huang , Xiaozhi Kong , Huawei Lu , Zhengyang Dong , Pengwei Fan","doi":"10.1016/j.ast.2024.109698","DOIUrl":"10.1016/j.ast.2024.109698","url":null,"abstract":"<div><div>For the purpose of further enhancing the performance of the cascade, this study takes the high-load diffuser cascade as the research object. By simplifying the design of the cascade with leakage flow in experiments, tests and numerical simulation were conducted at design incidence angle of 0° and the minimum loss incidence angle of -4° for different leakage flow rates and leakage inflow angles. The results show that changes in leakage flow rates and inflow angles will lead to variations in the momentum thickness of the boundary layer at the leading edge of the cascade, thereby affecting the cascade performance. Increasing the leakage flow rate results in an increase in the spanwise and tangential momentum of the leakage flow, a thickening in the axial momentum thickness of the boundary layer at the cascade leading edge, a reduction in the static pressure on the endwall within the cascade passage, a decrease in the expansion capability, and a raising in losses. Increasing the leakage inflow angle results in no change in the spanwise momentum of the leakage flow, an increase in the tangential momentum, a thickening in the tangential momentum thickness of the boundary layer at the cascade leading edge, a gradual increase in the static pressure at the leading edge, but a decrease in the static pressure within the cascade passage, leading to a decrease in the expansion capability. Changes in the tangential momentum of the leakage flow mainly affect the passage vortex, the trailing shedding vortex and the concentrated shedding vortex within the cascade passage.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109698"},"PeriodicalIF":5.0,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142560591","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 study on the combustion characteristics and performances of single and multi-injectors in a scramjet combustor 关于争气式喷气燃烧器中单喷射器和多喷射器的燃烧特性和性能的数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-28 DOI: 10.1016/j.ast.2024.109697

Seung-Min Jeong , Jae-Eun Kim , Min-Su Kim , Bu-Kyeng Sung , Jeong-Yeol Choi , Kenneth H. Yu

{"title":"Numerical study on the combustion characteristics and performances of single and multi-injectors in a scramjet combustor","authors":"Seung-Min Jeong , Jae-Eun Kim , Min-Su Kim , Bu-Kyeng Sung , Jeong-Yeol Choi , Kenneth H. Yu","doi":"10.1016/j.ast.2024.109697","DOIUrl":"10.1016/j.ast.2024.109697","url":null,"abstract":"<div><div>The present study numerically investigates the combustion characteristics and performance of a direct-connect gaseous hydrogen-fueled scramjet combustor depending on the injector scheme. A comprehensive numerical simulation was conducted with an improved delayed detached eddy simulation (IDDES) approach. The framework utilized a high-order accurate numerical scheme to ensure the high fidelity of the results. A total of ten cases were considered combining two injector schemes and five injection pressure conditions. Each injector scheme had a similar range of global equivalence ratios. Numerical results revealed the differences in the local dynamics of the counter-rotating vortex pair. The multi-injector case did not maintain the jet's systemic vortex structure, which plays a primary role in the fuel-air mixing and burning. It owes to the interactions between the jet-jet and the jet-wall surface, where the interaction leads to the loss of momentum. This characteristic of the multi-injector makes the fuel-air mixing contact surface get closer to a thin-flat layer, resulting in the flame being anchored on a flat shear layer over the entire combustor. As a result, the combustion efficiency of the multi-injector is much lower than that of the single injector under a similar equivalence ratio range. Present results indicate that the multi-injector, which is expected to increase the combustion performance by maximizing the fuel-air contact surface, may operate in contrast to its original anticipation under certain configurations and conditions. It also suggests that optimizing the combustion performance requires careful design of injector distributions considering the distances and interactions between injector-to-injector and injector-to-wall.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109697"},"PeriodicalIF":5.0,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142662557","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

Iterative control framework with application to guidance and attitude control of rockets 应用于火箭制导和姿态控制的迭代控制框架

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-28 DOI: 10.1016/j.ast.2024.109691

Xun Liu, Hashem Ashrafiuon, Sergey G. Nersesov

{"title":"Iterative control framework with application to guidance and attitude control of rockets","authors":"Xun Liu, Hashem Ashrafiuon, Sergey G. Nersesov","doi":"10.1016/j.ast.2024.109691","DOIUrl":"10.1016/j.ast.2024.109691","url":null,"abstract":"<div><div>Traditional control methods for nonlinear dynamical systems are predicated on verification of complex mathematical conditions related to the existence of a positive-definite Lyapunov function whose value must strictly decrease with time. Rigorous verification of Lyapunov conditions can be extremely difficult in real-world systems with high-dimensional and complex dynamics. In this paper, we present a novel control logic that can be readily applied to a general class of nonlinear systems irrespective of the complexities in their dynamics. The Iterative Control Framework (ICF) is designed to guarantee the convergence of the closed-loop system state to zero <em>without</em> a priori verification of Lyapunov-like conditions. The underlying computational routine runs in the background in real time and reconfigures the control vector at each time step in such a way that when the control input is applied to the system, the system trajectory reaches closer to the desired state. The technique is applicable to a broad class of complex nonlinear systems but is particularly suitable for systems inherently admitting control action of short duration such as missiles, rockets, satellites, and space vehicles. In this work, we focus on the application of ICF to guidance and attitude control of rockets and missiles where actuation is provided via single-use thrusters.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109691"},"PeriodicalIF":5.0,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142552910","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

Non-equilibrium plasma distribution in the wake of a slender blunted-nose cone in hypersonic flight and its effect on the radar cross section 高超音速飞行中细长钝头锥尾流中的非平衡等离子体分布及其对雷达截面的影响

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-28 DOI: 10.1016/j.ast.2024.109699

Salvatore Esposito , Andrea Scarabosio , Giuseppe Vecchi , Domenic D'Ambrosio

{"title":"Non-equilibrium plasma distribution in the wake of a slender blunted-nose cone in hypersonic flight and its effect on the radar cross section","authors":"Salvatore Esposito , Andrea Scarabosio , Giuseppe Vecchi , Domenic D'Ambrosio","doi":"10.1016/j.ast.2024.109699","DOIUrl":"10.1016/j.ast.2024.109699","url":null,"abstract":"<div><div>This paper presents numerical results in hypersonic aerothermodynamics, a critical field within aerospace engineering, traditionally focusing on reentry capsules and more recently, slender hypersonic vehicles. While capsules typically undergo near-field analysis to assess heat flux and pressure distributions for Thermal Protection System sizing, slender bodies demand additional attention to wake dynamics due to plasma presence. Plasma can significantly affect the Radar Cross Section (RCS) of these vehicles, which require tracking during flight due to their maneuvering and sustained flight capability.</div><div>Utilizing Computational Fluid Dynamics tools, we explore plasma distribution around a slender blunted cone, considering altitudes and Mach number regimes that may characterize gliding or sustained atmospheric hypersonic flight, emphasizing its impact on RCS. Our study integrates an aerothermodynamic model incorporating non-equilibrium relaxation equations for gas composition and energy. By evaluating characteristic plasma quantities, we underscore the importance of wake plasma for subsequent electromagnetic wave analysis, crucial for understanding RCS. Furthermore, we highlight the necessity for collaborative efforts between Computational Fluid Dynamics (CFD) and Computational Electro-Magnetics (CEM) disciplines to address this challenging interdisciplinary problem.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109699"},"PeriodicalIF":5.0,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142586302","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

Shock wave and fully turbulent boundary layer interaction controlled by surface arc plasma actuation 由表面电弧等离子体驱动控制的冲击波和全湍流边界层相互作用

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2024-10-28 DOI: 10.1016/j.ast.2024.109687

Qiong Wang, Tian Gan, Xiaoyue Xie

{"title":"Shock wave and fully turbulent boundary layer interaction controlled by surface arc plasma actuation","authors":"Qiong Wang, Tian Gan, Xiaoyue Xie","doi":"10.1016/j.ast.2024.109687","DOIUrl":"10.1016/j.ast.2024.109687","url":null,"abstract":"<div><div>Experiments were performed to examine the control effect of surface arc plasma actuators on a fully turbulent boundary layer interaction over a 26-deg ramp in a supersonic flow. The experiments utilized a non-invasive schlieren measurement device, along with comprehensive statistical processing techniques. Time-resolved schlieren up to 25 kHz were performed for visualization. Root Mean Square (RMS), Fast Fourier Transformation (FFT), and Proper Orthogonal Decomposition (POD) were performed on the schlieren dataset for structure identification in the interaction flow. A discharge is created between an electrode pair located upstream of a ramp to induce significant disturbances in the turbulent boundary layer. The discharge frequencies employed are <em>f<sub>a</sub></em>=0.5, 1, 2, and 5 kHz. The findings indicate that lower excitation frequencies result in a greater instantaneous energy input to the flow field, while the highest cumulative energy is obtained at 5 kHz over time. The separation region inhibited effect is further verified through the RMS of the schlieren intensity. The separation shock weaken is verified through the FFT of the schlieren intensity. The results indicate that perturbations in the fully turbulent boundary layer interaction flow pattern are more effective for separation shock control and separation region inhibition. It is important to appropriately increase the actuation frequency in order to achieve a certain level of control over the reattachment shock. This control effect is dependent on the total energy injected into the flow field rather than a large energy of a single pulse.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109687"},"PeriodicalIF":5.0,"publicationDate":"2024-10-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142552908","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