Aerospace Science and Technology最新文献

{"title":"Improved extended disturbance observer-based integral backstepping sliding mode control for quadrotor slung-load system","authors":"Xinyu Chen ,&nbsp;Yunsheng Fan ,&nbsp;Guofeng Wang ,&nbsp;Dongdong Mu","doi":"10.1016/j.ast.2025.110042","DOIUrl":"10.1016/j.ast.2025.110042","url":null,"abstract":"<div><div>Quadrotor slung-load (QSL) systems are commonly employed in aerial transportation tasks, where precise trajectory tracking and effective load swing suppression are critical challenges. These objectives are challenged by model uncertainties and unknown environmental disturbances, such as wind, which can compromise system stability and control accuracy. This paper addresses these challenges by developing a novel control strategy for QSL systems, where the system dynamics are divided into the attitude, position, and swing angle of the slung-load. Wind disturbances, including turbulence and wind shear, are modeled to simulate realistic outdoor scenarios. The integration backstepping control method forms the basis of the controller design, the sliding mode control is added to enhance the control accuracy and robustness while reducing steady-state error. An improved extended disturbance observer (IEDO) is incorporated to estimate and compensate for unknown disturbances and model uncertainties. The stability of the proposed controller and the convergence of the disturbance observer are rigorously analyzed using Lyapunov theory. Simulation results demonstrate the effectiveness of the proposed approach, achieving significant reductions in trajectory tracking errors and slung-load swing, even under complex and varying disturbance conditions.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110042"},"PeriodicalIF":5.0,"publicationDate":"2025-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143387895","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":"Augmenting mesh-based data-driven models with physics gradients","authors":"David Massegur,&nbsp;Andrea Da Ronch","doi":"10.1016/j.ast.2025.110037","DOIUrl":"10.1016/j.ast.2025.110037","url":null,"abstract":"<div><div>Deep learning technologies are increasingly used in various applications, with significant potential in aerospace for reduced-order modelling due to their ability to handle nonlinear systems. The effectiveness of data-driven methods relies on the adequacy and volume of training data, which poses a challenge in a design environment. To address this, physics-informed machine learning, which integrates physics knowledge into data-driven frameworks, has emerged as a promising solution. Directly applying physics terms to aircraft surfaces is complex, so this study utilizes solution gradients to effectively capture flow features. We introduce a hybrid framework that combines geometric deep learning with gradient terms, building on a previous data-driven approach for aerodynamic modelling on large-scale, three-dimensional unstructured grids. We evaluated various hybrid schemes to enhance prediction accuracy. Two gradient-enhanced approaches were found to outperform the purely data-driven model: the first integrates output differentiation into the training loss, achieving the highest accuracy at an increased training cost; the second employs a masking technique to weight regions with large gradients, providing a reasonable accuracy improvement at a lower training cost. This study focuses on predicting distributed aerodynamic loads around the NASA Common Research Model wing/body configuration under various transonic flight conditions. Our findings show that incorporating gradient information into deep learning models significantly improves the accuracy of the predictions and can compensate for a smaller dataset without compromising accuracy. Furthermore, the approaches proposed herein are directly applicable to any problem with discretised spatial domain.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110037"},"PeriodicalIF":5.0,"publicationDate":"2025-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143395480","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":1,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"OA","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

{"title":"Numerical study on plasma layer manipulation for blackout mitigation by pulsed magnetic field","authors":"Shunhao Peng ,&nbsp;Yongliang Feng ,&nbsp;Xiaojing Zheng","doi":"10.1016/j.ast.2025.110039","DOIUrl":"10.1016/j.ast.2025.110039","url":null,"abstract":"<div><div>Radio communication blackout is one of the most significant obstacles to the operation and telemetry of hypersonic vehicles. The plasma manipulation with a pulsed magnetic field has been identified as a promising solution to the blackout problem through laboratory observations. To evaluate the effect of the pulsed magnetic field in realistic hypersonic flight conditions, this work numerically studies pulsed magnetic field manipulation for the plasma layer of hypersonic vehicles based on the magnetohydrodynamic model coupled with the high-temperature gas effect. The Wentzel-Kramer-Brillouin (WKB) method is used to analyze the transmission characteristics of electromagnetic waves in a magnetized plasma. The numerical results show that the pulsed magnetic field with suitable pulse duration can reduce electron density and radio attenuation near the antenna. The communication window created by the pulsed magnetic field allows lower-frequency radio to transmit through the plasma layer and the duration of the window can last more than 0.1 ms. Besides, the effect of blackout mitigation by the pulsed magnetic field is significantly enhanced with increasing magnetic field strength at each flight altitude. These investigations can provide useful information for designing and optimizing electromagnetic manipulation for blackout mitigation.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110039"},"PeriodicalIF":5.0,"publicationDate":"2025-02-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143387896","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":"Multidisciplinary design optimization of the first-stage waverider based on boost-glide flight trajectory","authors":"Jun-xue Leng,&nbsp;Zan Xie,&nbsp;Wei Huang,&nbsp;Yang Shen,&nbsp;Zhen-guo Wang","doi":"10.1016/j.ast.2025.110033","DOIUrl":"10.1016/j.ast.2025.110033","url":null,"abstract":"<div><div>Multistage waverider vehicles based on the combined trajectory flight possess aerodynamic performance advantages, offer more flexible trajectories, and can achieve extended ranges. However, current multistage waverider design technology remains underdeveloped and is still in the preliminary theoretical research stage. This paper extends the design methodology for two-stage waverider vehicles, enabling the design of a first-stage wide-speed-range waverider that conforms to the leading edge of a given irregular second-stage airbreathing lifting-body configuration, thus forming a two-stage waverider structure. According to the specific optimization requirements, we refined the multi-fidelity data-mining-based MDO (Multidisciplinary Design Optimization) framework, yielding an optimized first-stage wide-speed-range lifting body configuration with superior performance under viscous conditions. Compared with the initial configuration, the optimized first-stage vehicle, with a constant takeoff mass, achieved a 5.84 % increase in range for the boost-glide combined trajectory, further verifying the effectiveness and flexibility of the multi-fidelity data-mining-based MDO framework.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110033"},"PeriodicalIF":5.0,"publicationDate":"2025-02-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143378773","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":"Large eddy simulation of compound angle film cooling with round holes embedded in ginkgo-shaped craters","authors":"Zhiyuan Zhao ,&nbsp;Fengbo Wen ,&nbsp;Zuobiao Li ,&nbsp;Jiajun Han ,&nbsp;Yu Li ,&nbsp;Xinghong Zhang ,&nbsp;Songtao Wang","doi":"10.1016/j.ast.2025.110047","DOIUrl":"10.1016/j.ast.2025.110047","url":null,"abstract":"<div><div>Film cooling holes embedded in craters or trenches are gaining attention as recent advancements in gas turbines due to significant improvements in film cooling effectiveness. Inspired by ginkgo leaves, a novel ginkgo-shape film cooling crater with two spreading lobes has been investigated using large eddy simulation (LES), achieving considerable enhancements in film cooling performance. A comprehensive evaluation of coolant film distribution and vortical structure variation is illustrated to understand the flow dynamics of compound cooling jets emerging from cooling holes embedded in the ginkgo craters at the blowing ratio of <em>M</em> = 1.0 and the density ratio of DR = 2.0. The film cooling effectiveness is greatly improved with compound angles of 0 deg and 30 deg due to the wide lateral expansion of coolant film and less coolant separation in the streamwise direction. However, the ginkgo crater deteriorates the cooling performance with a compound angle of 60 deg because of the enlarged uncooled gap between the adjacent holes. Instantaneous and time-averaged vortical structures are examined, showing that the upwash counter-rotating vortex pair (CRVP) and the asymmetric vortex (ASV) are greatly weakened. The origination and evolvement of the shear layer vortex and the hairpin vortex are discussed in detail with the effect of the ginkgo crater in the current work.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110047"},"PeriodicalIF":5.0,"publicationDate":"2025-02-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143402509","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":"Load split design strategy of tandem stators in a highly loaded micro axial compressor","authors":"Xiaochen Mao ,&nbsp;Fu Lei ,&nbsp;Yunyu Wang ,&nbsp;Zhihua Ding ,&nbsp;Hao Cheng ,&nbsp;Bo Liu","doi":"10.1016/j.ast.2025.110040","DOIUrl":"10.1016/j.ast.2025.110040","url":null,"abstract":"<div><div>To investigate the load split (LS) effects on the performance and flow mechanisms of a cantilevered tandem stator in a highly loaded micro axial compressor, three typical tandem blade schemes were thoroughly studied from multiple perspectives using steady-state numerical simulations. The results show that in the <em>LS</em> design of the tandem blades, the trade-off effects between highly and lowly loaded conditions are essential to achieve superior overall performance. The gap jet serves a pivotal function in leakage flow behaviors, acting as a vital link between the leakage flow from the front blade (FB) and rear blade (RB). Furthermore, the mixing effects between the front blade wake and gap jet is one of the main entropy generation sources in the tandem stators. In addition, the spanwise <em>LS</em> distribution remarkably affects the load distribution of the stator in spanwise direction by altering the body force. Specifically, in the tandem stators with lower <em>LS</em>, the overall load near the hub is smaller, but in the range of the midspan and near the casing, the overall load on both the rotor and stator is increased. The former increases overall efficiency, while the latter triggers an earlier stall near the rotor tip.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110040"},"PeriodicalIF":5.0,"publicationDate":"2025-02-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143387893","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":"An investigation on bleed flow control of an axisymmetric supersonic intake based on parametric outline optimization design","authors":"Peimin Xie ,&nbsp;Yuanhua Liu ,&nbsp;Wei Yuan","doi":"10.1016/j.ast.2025.110027","DOIUrl":"10.1016/j.ast.2025.110027","url":null,"abstract":"<div><div>The intake plays an important role in the supersonic propulsion system, which restricts the performance of the entire propulsion system. It has been a challenge to ensure that the intake performs well in wide operating range. In this study, based on the multi-objective genetic algorithm, the baseline geometry of the intake is firstly optimized with <em>Ma</em>4 as the design point, and the total pressure coefficient at the outlet of the intake is 0.574. Secondly, in response to the performance decline and starting issues of the intake at off-design points, research is conducted on the scheme and physical mechanisms involving bleed flow control and the axial relative movement of the center body. The axial relative displacement of the center body decreases by 8.98 % due to the introduction of bleed slots, enabling the intake to start under conditions of larger internal contraction ratio. The mass flow rate loss caused by the bleed slots can be compensated by moving the center body and increasing the internal contraction ratio, as it enlarges the capture area of the intake. At <em>Ma</em>₀=4, the intake achieves a 2.58% increase in total pressure recovery with a 1.284 % bleed flow rate for the separation bubble eliminated. At <em>Ma</em>₀=1.5, the intake achieves a 6.47 % increase in total pressure recovery with a 6.6 % bleed flow rate, because the internal contraction ratio of the intake is enlarged and the terminal shock wave/boundary layer interaction is suppressed. But excessive bleed flow rate leads to the enhancement of terminal shock wave train which is detrimental.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 110027"},"PeriodicalIF":5.0,"publicationDate":"2025-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143379048","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 uniform profile tolerance on aerodynamic performance eligibility of high subsonic cascade","authors":"Guang Yang ,&nbsp;Limin Gao ,&nbsp;Panpan Tu ,&nbsp;Yue Dan","doi":"10.1016/j.ast.2025.110028","DOIUrl":"10.1016/j.ast.2025.110028","url":null,"abstract":"<div><div>In this paper, the concept of “aerodynamic performance tolerance”, which is used to measure the aerodynamic performance eligibility of the cascade, is proposed by analogy with the concept of profile tolerance which is used to constrain profile geometry. Then, the mathematical model of profile with random machining error is established based on random process. After that, taking a high subsonic cascade as the research object, the influence of uniform profile tolerance on aerodynamic performance eligibility under <em>i</em> = 0°, <em>i</em> = 2.4° and <em>i</em> = 4° at <em>Ma</em>=0.8 by SG-NIPC(Sparse Grid -Non Instrusive Polynomial Chaos) uncertainty quantification method. The mechanism analysis of the reasons for the change of aerodynamic eligibility is carried out. The results show that the aerodynamic performance eligibility is the lowest under <em>i</em> = 4°, and the aerodynamic performance eligibility shows a nonlinear decreasing trend with the increase of uniform profile tolerance. With the increase of uniform profile tolerance, the fluctuation of boundary layer loss in the first 10 % arc length of the suction surface will be aggravated, which will affect the downstream flow field, resulting in the increase of the fluctuation of separation loss, and ultimately the qualification of the overall aerodynamic parameters, like total pressure loss coefficient, will be reduced.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110028"},"PeriodicalIF":5.0,"publicationDate":"2025-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143402510","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":"Vibration-attitude integrated control of a large two-dimensional planar phased array antenna","authors":"Li Pei ,&nbsp;Liu Xiang ,&nbsp;Cai Guoping ,&nbsp;Sun Jun ,&nbsp;Zhu Dongfang","doi":"10.1016/j.ast.2025.110030","DOIUrl":"10.1016/j.ast.2025.110030","url":null,"abstract":"<div><div>Phased array antennas are pivotal for observing, identifying, and tracking targets, serving both military and civilian needs. They are growing larger and more complex to meet the demand for high-resolution Earth observation. However, their intricate design, low-frequency density, and significant coupling make dynamic analysis and control design challenging. This paper introduces a novel large-scale, space-deployable, two-dimensional planar phased array antenna and investigates its dynamic modeling and active control. Unlike traditional one-dimensional phased array antenna, this antenna can scan in two directions, providing a larger scanning area. To suppress antenna vibration, the paper proposes a control strategy using ropes as actuators. Firstly, the paper details the structure of the phased array antenna, including its attitude and vibration actuators. Then, using the hybrid coordinate method and the velocity variation principle, it derives the antenna's rigid-flexible coupled dynamic model. Subsequently, the paper designs an attitude-vibration controller for the antenna, integrating the computed torque control method, Linear Quadratic Regulator (LQR), and Bang-Bang control theory. This includes considering the unidirectionality and saturation of the rope control forces and optimizing the placement of rope actuators using Particle Swarm Optimization (PSO). Finally, numerical simulations validate the effectiveness and accuracy of the theoretical investigation. The results indicate that the antenna model possesses characteristics of low-frequency density and robust rigidity-flexibility coupling, with optimization of actuator quantity and placement enhancing control efficiency. Furthermore, the dynamic model accurately describes the antenna's behavior, achieving results consistent with ADAMS software. The attitude-vibration coupled controller maintains precise directional accuracy, effectively suppressing vibrations.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"160 ","pages":"Article 110030"},"PeriodicalIF":5.0,"publicationDate":"2025-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143402511","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":"Research on integrated design method of wide-range hypersonic vehicle/engine based on dynamic multi-objective optimization","authors":"Zeyang Zhao ,&nbsp;Yue Ma ,&nbsp;Ye Tian ,&nbsp;Zhijian Ding ,&nbsp;Hua Zhang ,&nbsp;Shuhong Tong","doi":"10.1016/j.ast.2025.110031","DOIUrl":"10.1016/j.ast.2025.110031","url":null,"abstract":"<div><div>A hypersonic vehicle powered by an air-breathing engine enables efficient long-range delivery and high-speed flexible access to space. The key to achieving high-performance operation of hypersonic vehicles lies in high-efficiency and well-matched hypersonic vehicle/engine integration configuration design. While machine learning-assisted intelligent optimization has shown initial success in hypersonic vehicle/engine integration design, over-reliance on basic and simplistic intelligent methods has led to a significant dependency on sample size and a tendency to easily converge to local optima. This study addresses the need for wide-speed-range, small-sample, and multi-criteria hypersonic vehicle/engine integration design by developing a parametric model for the hypersonic vehicle/engine configuration. Leveraging computational fluid dynamics (CFD) technology, the study uses the Deep Active Subspace (DAS) model along with the Improved Multi-Objective Coati Optimization Algorithm (IMOCOA). This approach is applied to small-sample dynamic multi-point and multi-objective optimization design with the objective of achieving an optimal hypersonic vehicle/engine configuration design characterized by low drag, a high lift-drag ratio, and a high total pressure recovery coefficient across various operating conditions. The results indicate that the Mean Absolute Percentage Error (MAPE) for predicting hypersonic vehicle/engine integration performance using the DAS model is &lt;2 %. Validation of the Pareto solution set from multi-objective optimization shows that dynamic multi-objective optimization enhances performance by &gt;3 % compared to static multi-objective optimization. In comparison to the pre-optimization configuration, the optimized configuration demonstrates a 12.97 % reduction in total drag, with a 9.77 % improvement in lift-drag ratio and a 10.27 % enhancement in total pressure recovery coefficient, highlighting rapid and efficient hypersonic vehicle/engine integration configuration design and performance improvement.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"159 ","pages":"Article 110031"},"PeriodicalIF":5.0,"publicationDate":"2025-02-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"143379050","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}