Aerospace Science and Technology最新文献_第10页

A data-driven neural model predictive controller for multi-layer nonlinear vibration isolation system 多层非线性隔振系统的数据驱动神经模型预测控制器

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-07-08 DOI: 10.1016/j.ast.2025.110583

Jiyuan Jiang , Jie Tang , Mei Liu , Yinghui Li , Huatao Chen , Dengqing Cao

{"title":"A data-driven neural model predictive controller for multi-layer nonlinear vibration isolation system","authors":"Jiyuan Jiang , Jie Tang , Mei Liu , Yinghui Li , Huatao Chen , Dengqing Cao","doi":"10.1016/j.ast.2025.110583","DOIUrl":"10.1016/j.ast.2025.110583","url":null,"abstract":"<div><div>For an active multi-layer nonlinear vibration isolation system (MNVIS) with quasi-zero-stiffness (QZS) characteristics, this paper proposes a data-driven method to train the controller based on model predictive control (MPC) theory, which combines the identification of the prediction model with the solution of the optimal control law. Inspired by the framework of neural ordinary differential equations (NODEs), the substructure physics-informed neural network (PINN) is designed to establish the surrogate dynamic model (SDM) of the controlled object for the predictive controller. Instead of solving the optimal control force online, the neural network controllers are trained by minimizing the cost functions of MPC. Final results indicate that the identified SDMs accurately capture the dynamic characteristics of the true dynamic models, and the trained neural network controllers can approximate the optimal control laws. Moreover, these controllers are capable of achieving an outstanding vibration isolation performance specified by the cost functions, and further enhancing the low-frequency vibration isolation of the MNVIS.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"166 ","pages":"Article 110583"},"PeriodicalIF":5.0,"publicationDate":"2025-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144597176","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

Three-dimensional practical cooperative guidance law for salvo attack considering velocity variation 考虑速度变化的齐射攻击三维实用协同制导律

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-07-08 DOI: 10.1016/j.ast.2025.110588

Ang Huang , Xiaodong Wang , Qilun Zhao , Jianglong Yu , Xiwang Dong

引用次数: 0

A numerical study on the aerodynamic characteristics of leading-edge vortex controllers on a fighter pertinent to Su-57 苏-57型战斗机前缘涡控制器气动特性数值研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-07-08 DOI: 10.1016/j.ast.2025.110610

Yi-Lin Tsai , Wen-Lih Chen , Ming-Hsi Hu

{"title":"A numerical study on the aerodynamic characteristics of leading-edge vortex controllers on a fighter pertinent to Su-57","authors":"Yi-Lin Tsai , Wen-Lih Chen , Ming-Hsi Hu","doi":"10.1016/j.ast.2025.110610","DOIUrl":"10.1016/j.ast.2025.110610","url":null,"abstract":"<div><div>This study numerically investigated the effects of active flow control devices, LEVCONs and slats, on the aerodynamic characteristics of a triple-delta-wing configuration pertinent to the Su-57. The effects of actuating LEVCONs and slats to different deflection angles on the aerodynamic characteristics were examined individually. It was found that the effects of lift contribution and drag reduction can be superposed. The characteristics of vortex cores were also investigated by using dimensionless axial velocity and dimensionless vorticity to respectively classify vortex cores and quantify the strength of vortical flows. Flow fields were visualized using the isosurfaces of dimensionless <em>Q</em>-criterion and spatial streamlines to facilitate the understanding of the complex flow physics behind the vortical flows. The analysis indicated that the actuation of LEVCONs and slats tended to delay vortex breakdown and shift vortices outboard. This, in turn, spread out different vortex systems more evenly on the upper surface of the model. Pressure coefficients on the model surface along the spanwise direction revealed that the outboard trajectory of vortices induced a rise in local <em>-C<sub>p</sub></em>, signifying the existence of vortex lift, which was responsible for the improvement in aerodynamic characteristics within the angle-of-attack range from 0° to 40° At a higher angle-of-attack range from 26° to 40°, the deflection of LEVCONs and slats by 30° resulted in more than a 10 % increase in lift. Proper actuation of LEVCONs and slats was also found to reduce drag and lessen the unstable pitching moment.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"166 ","pages":"Article 110610"},"PeriodicalIF":5.0,"publicationDate":"2025-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144633095","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

Wall interference effects on helicopter rotor in closed and open wind tunnels 封闭风洞和开放风洞中直升机旋翼的壁面干涉效应

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-07-08 DOI: 10.1016/j.ast.2025.110585

Tianshuang Shao , Yiwen He , Haitao Zhang , Zhengzhuo Li , Aiming Shi

{"title":"Wall interference effects on helicopter rotor in closed and open wind tunnels","authors":"Tianshuang Shao , Yiwen He , Haitao Zhang , Zhengzhuo Li , Aiming Shi","doi":"10.1016/j.ast.2025.110585","DOIUrl":"10.1016/j.ast.2025.110585","url":null,"abstract":"<div><div>The wall interference effects substantially contribute to systematic errors in wind-tunnel experiments, which greatly impedes the accurate measurements of aerodynamic performance, hindering the development and optimization of helicopter rotors. This paper numerically investigates the wall interference effects on helicopter rotors in both closed and open wind tunnels based on a virtual blade model. Comprehensive analyses and comparisons are performed regarding the flowfield characteristics (including downwash flow and wake flow) and helicopter aerodynamic performance (including rotor torque coefficient and lift coefficient) under freestream, closed wind-tunnel, and open wind-tunnel conditions. Results indicate that the open and closed test sections have opposite impacts on the aerodynamic performance of the helicopter rotor. Specifically, the open test section gives rise to a more inclined rotor downwash flow, resulting in an overestimated measured rotor torque coefficient, which is however underestimated for the closed test section. At the low advance ratio, the open test section remarkably intensifies the negative lift on the fuselage, increasing the load while reducing the flat tail load. Conversely, the closed test section weakens both the fuselage and flat tail loads. Furthermore, at low advance ratios, flow breakdown is observed for both open and closed wind tunnels. Additionally, the open test section experiences wake escapement, which deflects the flow away from the return circuit, affecting its operation.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"166 ","pages":"Article 110585"},"PeriodicalIF":5.0,"publicationDate":"2025-07-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144597174","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 investigation of different transverse periodic actuator-induced flow characteristics 不同横向周期作动器诱导流动特性的实验研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-07-07 DOI: 10.1016/j.ast.2025.110601

Jiaxin Pan, Wanbo Wang, Chaoqun Li, Xinhai Zhao, Chen Qin, Kun Tang

{"title":"Experimental investigation of different transverse periodic actuator-induced flow characteristics","authors":"Jiaxin Pan, Wanbo Wang, Chaoqun Li, Xinhai Zhao, Chen Qin, Kun Tang","doi":"10.1016/j.ast.2025.110601","DOIUrl":"10.1016/j.ast.2025.110601","url":null,"abstract":"<div><div>Blowing flow control technology with air sources can enhance aircraft performance, while transverse jet technology may reduce air supply requirements and lower the pressure needed from engines or compressors. To investigate the characteristics of transverse jets, experimental studies were carried out by designing two schemes: Continuous Transverse Jet (CTJ) and Discrete Transverse Jet (DTJ). Using microcontroller technology, two forms of transverse jet actuators were developed for circular free jets that move radially. Particle Image Velocimetry (PIV) technology was used to experimentally study the flow fields of these two transverse jet actuators. By comparing the flow field characteristics under different transverse jet actuators, the mechanisms behind the structural differences in the external flow fields of the two types of actuators are analyzed. The results indicate that the main reason for the deflection of DTJ is the vortex suction effect from adjacent jets, while the deflection of CTJ is primarily due to the spanwise velocity introduced by the mechanical device at the nozzle. This leads to DTJ exhibiting self-similar, dimensionless velocity distribution across sections, while CTJ does not. In the time-averaged flow field, it is observed that the maximum flow velocity and coverage range of DTJ are larger than those of CTJ. The single jet of CTJ, after deflection, forms counter-rotating vortices at different flow directions, causing its flow velocity coverage to gradually shrink in the streamwise direction. The analysis from Proper Orthogonal Decomposition (POD) indicates that, compared to DTJ, the first two dominant modes of CTJ show a greater degree of deflection in the Z direction due to the additional spanwise velocity. The wind tunnel test verifies that, at the same flow rate, the traverse jet increases lift coefficient by up to 70 % compared to the steady jet.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"166 ","pages":"Article 110601"},"PeriodicalIF":5.0,"publicationDate":"2025-07-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144631867","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 acceleration control schedule for turbofan engine based on equal relative rotational acceleration reverse method 基于等相对旋转加速度反演法的涡扇发动机加速度控制方案研究

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-07-07 DOI: 10.1016/j.ast.2025.110563

Haolan Shi , Qian Chen , Pengxuan Wei , Bingxiong Yin , Jiacheng Li , Hanlin Sheng

{"title":"Research on acceleration control schedule for turbofan engine based on equal relative rotational acceleration reverse method","authors":"Haolan Shi , Qian Chen , Pengxuan Wei , Bingxiong Yin , Jiacheng Li , Hanlin Sheng","doi":"10.1016/j.ast.2025.110563","DOIUrl":"10.1016/j.ast.2025.110563","url":null,"abstract":"<div><div>Existing design methods for acceleration control schedules focus only on acceleration time, neglecting significant overshoot and fluctuation in thrust at the end of acceleration, which can adversely affect actual flight. To achieve better actual flight effects, this study aims to develop an improved acceleration control schedule that simultaneously minimizes acceleration time while controlling end-of-acceleration disturbances. Toward this goal, the Equal Relative Rotational Acceleration Reverse Method (EARM) is proposed. Initially, the Dynamic Steady Reverse Model (DSRM) is established to achieve dynamic performance simulation of the target rotational acceleration and speed. Then, the Search Enhancement Strategies-Chaotic Particle Swarm Optimization (SES-CPSO) algorithm is introduced to tackle the complex optimization problems associated with the DSRM. Based on the above two, by coordinately planning the dual rotor acceleration process, an optimization of multiple control variables is conducted to obtain a multivariable control schedule. Simulation results show that under the condition of <em>H</em> = 0 km, <em>Ma</em> = 0, compared with the schedule designed by the Transient-state Reverse Method (TRM), acceleration time is reduced from 3.86 seconds to 3.71 seconds, a reduction of 4.04%, and thrust overshoot is reduced from 2.76% to 0.665%, a reduction of 75.91%. It is concluded that the proposed method can effectively reduce the fluctuation and overshoot of rotational speeds and thrust at the end of acceleration while minimizing the acceleration time.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"166 ","pages":"Article 110563"},"PeriodicalIF":5.0,"publicationDate":"2025-07-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144623266","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

Integrated attitude and morphing control for morphing aircrafts: A method to improve aerodynamic efficiency 变形飞行器姿态与变形综合控制：一种提高气动效率的方法

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-07-07 DOI: 10.1016/j.ast.2025.110553

Hui Zheng , Guangbin Cai , Yongchao Wang , Bin Zhou

{"title":"Integrated attitude and morphing control for morphing aircrafts: A method to improve aerodynamic efficiency","authors":"Hui Zheng , Guangbin Cai , Yongchao Wang , Bin Zhou","doi":"10.1016/j.ast.2025.110553","DOIUrl":"10.1016/j.ast.2025.110553","url":null,"abstract":"<div><div>This article delves into the study of a morphing aircraft characterized by symmetrically adjustable wingspan and sweep angle, proposing an innovative integrated control method for both attitude and deformation. By establishing a hierarchical structure for control tasks, this method allows the aircraft to prioritize and fulfill attitude control (high-priority task) while allocating any remaining control capability to improve aerodynamic efficiency (low-priority task), without negatively impacting the performance of the high-priority task. Firstly, considering the wingspan and sweep angle as auxiliary control variables, the incremental modeling technique is employed to approximate the nonlinear and uncertain longitudinal model of the morphing aircraft with minimal reliance on pre-existing models. Based on these incremental models, a model predictive control strategy is employed to design the attitude control law, ensuring that the aircraft's angle of attack accurately tracks a reference trajectory while satisfying to any input and state constraints. Secondly, with the goal of maximizing aerodynamic efficiency, a morphing control law is formulated. This law incorporates the dynamic consistency principle to enhance aerodynamic performance while simultaneously fulfilling attitude control requirements, thereby achieving seamless integration of attitude and morphing control. Subsequently, closed-loop stability analysis is conducted for the aforementioned control laws using the practical Lyapunov theorem. Finally, numerical simulations are carried out, demonstrating that the proposed controller exhibits robust performance, minimal model dependency, and a notable improvement in aerodynamic efficiency.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"166 ","pages":"Article 110553"},"PeriodicalIF":5.0,"publicationDate":"2025-07-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144632354","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

Design, analysis, and development of a flexible positioning and vibration isolation integrated hexapod 柔性定位与隔振集成六足架的设计、分析与开发

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-07-07 DOI: 10.1016/j.ast.2025.110587

Jinyuan Mei , Chunyang Han , Zhenbang Xu , Anpeng Xu , Chao Qin

{"title":"Design, analysis, and development of a flexible positioning and vibration isolation integrated hexapod","authors":"Jinyuan Mei , Chunyang Han , Zhenbang Xu , Anpeng Xu , Chao Qin","doi":"10.1016/j.ast.2025.110587","DOIUrl":"10.1016/j.ast.2025.110587","url":null,"abstract":"<div><div>To achieve high-precision control of the primary mirror shape for a segmented space telescope (SST), a Flexible Positioning and Vibration Isolation Integrated Hexapod (FPVI hexapod) has been proposed, which can achieve high-precision positioning and vibration isolation for mirror segments. First, flexure hinges and flexure membranes with complementary flexibility were designed based on the constraints of the motion degrees of freedom (DOF), and the compliance characteristics of flexure hinges based on the quadratic rational Bézier curves with different numbers of sensitive axes were modeled. Kinematic and dynamic models of the FPVI hexapod, considering the axis configuration of flexure hinges and parasitic stiffness, were established. Next, a rigid-flexible coupled mechatronic co-simulation system was developed to verify the correctness of the kinematic model of the FPVI hexapod. Finally, a prototype and experimental system were constructed to validate the positioning and vibration isolation performance of the FPVI hexapod. The experimental results show that the resolution of translation and rotation motions can reach 20 nm and 0.1 arcsec, respectively. The repeatability of translation and rotation motions are at least 37.88 nm and 0.248 arcsec, respectively. Furthermore, under active vibration isolation, resonance peaks caused by the FPVI hexapod in all directions within the 2Hz-100 Hz frequency range can be effectively suppressed. The designed FPVI hexapod can be used for SST primary mirror shape adjustment and maintenance.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"166 ","pages":"Article 110587"},"PeriodicalIF":5.0,"publicationDate":"2025-07-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144653921","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

Aerodynamic shape optimization via active learning-driven design space refinement 气动形状优化通过主动学习驱动的设计空间细化

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-07-07 DOI: 10.1016/j.ast.2025.110606

Jiarui Liu , Ying Jiang , Jun Tao , Guanghui Wu

{"title":"Aerodynamic shape optimization via active learning-driven design space refinement","authors":"Jiarui Liu , Ying Jiang , Jun Tao , Guanghui Wu","doi":"10.1016/j.ast.2025.110606","DOIUrl":"10.1016/j.ast.2025.110606","url":null,"abstract":"<div><div>In Aerodynamic Shape Optimization (ASO) studies, the ranges of design variables critically influence both optimization efficiency and solution quality. Traditional approaches typically maintain fixed boundaries based on experiential knowledge, struggling to balance computational efficiency with optimization outcomes. This paper proposes an innovative design space refinement framework driven by active learning. This framework offers a flexible and efficient strategy to identify a compact design space encompassing high-performance designs. Active learning enhances sampling efficiency, while the refinement mechanism progressively directs the optimization focus toward higher-performing designs. The proposed framework is validated through a comparative analysis with Principal Components Analysis (PCA), a prevalent method for reducing the number of design variables, on supercritical airfoil optimization. The results demonstrate that dynamically refining the boundaries of design variables can significantly improve the efficiency and effectiveness of ASO. By integrating active learning with adaptive design space refinement, the proposed approach effectively focuses the optimization process on regions likely to contain superior designs.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"166 ","pages":"Article 110606"},"PeriodicalIF":5.0,"publicationDate":"2025-07-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144631868","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

Full-size mechanical evaluation for large aircraft cabin door with complex fabric rubber composite seal structures 大型飞机舱门复杂织物橡胶复合密封结构的全尺寸力学评价

IF 5 1区工程技术

Aerospace Science and Technology Pub Date : 2025-07-07 DOI: 10.1016/j.ast.2025.110581

Xiaoyao Xu, Han Yan, Guowen Wang, Xuefeng Yao

{"title":"Full-size mechanical evaluation for large aircraft cabin door with complex fabric rubber composite seal structures","authors":"Xiaoyao Xu, Han Yan, Guowen Wang, Xuefeng Yao","doi":"10.1016/j.ast.2025.110581","DOIUrl":"10.1016/j.ast.2025.110581","url":null,"abstract":"<div><div>The fulfillment of expected functions for cabin mechanisms directly determines the flight safety and reliability of high-performance aerospace components. Complex fabric rubber composites are widely designed as seal composites for aircraft doors and moving surfaces, whose complex configurations and compositions bring long-term obstacles to their fine evaluation. In this work, the interaction mechanics involving the full-size cabin door complex composite seal structure are studied to reveal its motion, deformation and mechanical performance within a structural range of approximately 2 <em>m</em> × 1 m. The high-fidelity simulation results are in order of magnitude agreement with existing segment-level experiments and simulations, and are mutually verified with the full-size field experiments. The compression load change can be divided into three main stages, and their stress distributions are related to compression and boundary conditions. An empirical formula for predicting the overall compression load is proposed based on mechanical and statistical methods and applied to combinations of seal/fixture friction conditions. To our knowledge, this is the first systematic study on the full-size cabin door composite seal structure, and our results provide benchmarks for further research on the evaluation and optimization of large aircraft composite seal structures.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"166 ","pages":"Article 110581"},"PeriodicalIF":5.0,"publicationDate":"2025-07-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"144633094","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