Aerospace Science and Technology最新文献

{"title":"Robust optimization design of a blended wing-body drone considering influence of propulsion system","authors":"Yiwen Wang ,&nbsp;Jiecheng Du ,&nbsp;Tihao Yang ,&nbsp;Jingsai Zhou ,&nbsp;Bo Wang ,&nbsp;Yayun Shi ,&nbsp;Junqiang Bai","doi":"10.1016/j.ast.2024.109751","DOIUrl":"10.1016/j.ast.2024.109751","url":null,"abstract":"<div><div>In contrast to conventional configurations, blended wing-body drones exhibit a pronounced coupling between their aerodynamic and propulsion system. While this configuration significantly enhances aerodynamic efficiency, perturbations in flight conditions substantially influence aerodynamic performance. To fully exploit the performance benefits inherent in this configuration, this paper integrates the calculation of the total pressure recovery coefficient and distortion coefficient into the flow field solution and achieves the gradient evaluation of these parameters. This allows the effects of the propulsion system to be considered in the gradient-based optimization. Additionally, utilizing the Gradient-enhanced polynomial chaos expansion (GPCE) method, we construct statistical moment related to the mean and variance and analytically compute the gradients of the moment with respect to the design variables. Consequently, a gradient-based uncertainty optimization framework that accounts for the effects of the propulsion system is established. The framework can accommodate large-scale deterministic design variables and several uncertain parameters. Using this framework, both deterministic and uncertainty-based optimizations that consider the effects of the propulsion system are performed. The objective functions include statistical moments accounting for flight conditions uncertainties. The comparison reveals a 11.89% reduction in statistical moment with robust optimization, highlighting the efficacy of the framework in future robust design optimization of propulsion-airframe integration.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"156 ","pages":"Article 109751"},"PeriodicalIF":5.0,"publicationDate":"2024-11-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702004","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":"Rotorcraft in-ground effect models in axial and forward flight","authors":"Xiang He ,&nbsp;Kam K. Leang","doi":"10.1016/j.ast.2024.109748","DOIUrl":"10.1016/j.ast.2024.109748","url":null,"abstract":"<div><div>This paper presents in-ground effect (IGE) models that incorporate the rotor advance ratio and vehicle's climbing velocity to predict the IGE thrust variation in axial (vertical) and forward flight for rotor-based aerial vehicles, such as quadcopter uncrewed aerial vehicles (UAVs). Extensive experiments were conducted to validate each and every component of the new IGE models. Discrepancies between the analytical and experimental results in forward flight were found to be consistent with the two characteristic flow regimes of recirculation and ground vortex. Specifically, an additional increase in thrust was observed at a low advance ratio (<em>μ</em>&lt;0.04) in the extreme ground-effect regime (<span><math><mi>z</mi><mo>/</mo><mi>R</mi><mo>&lt;</mo></math></span>0.5). The results of this study can be leveraged to develop new vehicle motion control and path planning algorithms for flying near obstacles.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"156 ","pages":"Article 109748"},"PeriodicalIF":5.0,"publicationDate":"2024-11-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142748136","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":"Aerodynamics evaluation and flight test of a vertical take-off and landing fixed-wing UAV with joined-wing configuration in transition flight state","authors":"Mi Baigang","doi":"10.1016/j.ast.2024.109759","DOIUrl":"10.1016/j.ast.2024.109759","url":null,"abstract":"<div><div>The transition states between the cruising flight and the taking-off/landing process of a vertical take-off and landing (VTOL) fixed-wing UAV of joined-wing configuration are subject to significant unsteady aerodynamic interference. In this paper, the aerodynamic characteristics of this VTOL UAV during transition flights are evaluated by CFD with and without crosswind interference, in order to reveal the underlying mechanisms of the transition process. Based on these CFD-derived parameters, a flight test with a specifically-designed joined-wing VTOL UAV is proposed. The obtained results demonstrate that the forward flight speed is a crucial parameter during the takeoff transition phase. In the time interval of 5–15 s, significant disturbances are observed in the forces and moments due to the rotor deceleration and forward propeller acceleration, which result in slipstream and downwash flow effects. When crosswind disturbance is added, significant roll and yaw moments arise due to the vast vertical stabilizer area, which requires coordinated attitude adjustments between the rotor and the fixed-wing rudder surface. The descent transition phase is set a duration of 10 s. Four seconds later, as the rotor downwash flow intensifies, the lift force of the fixed wing is transferred to the rotor. When the combined lift becomes insufficient, the flight altitude decreases. When introducing crosswind disturbance, the entire aircraft undergoes significant additional pitch, yaw, and roll moments, with a maximum wave momentum greater than 200 %. Flight tests are then conducted using simulated parameters. The obtained results show that the take-off and landing transition responses without crosswinds are consistent with the predicted outcomes, which demonstrates the high effectiveness of the CFD simulations in predicting these transitions.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109759"},"PeriodicalIF":5.0,"publicationDate":"2024-11-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142696822","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":"Adaptive neural network based fixed-time attitude tracking control of spacecraft considering input saturation","authors":"Chengyang Li ,&nbsp;Wei Wang ,&nbsp;Zhijie Liu ,&nbsp;Yuchen Wang ,&nbsp;Zhongjiao Shi","doi":"10.1016/j.ast.2024.109746","DOIUrl":"10.1016/j.ast.2024.109746","url":null,"abstract":"<div><div>Aiming at the issues of actuator saturation, inertia uncertainties, and external unknown disturbances in the attitude tracking control process of spacecraft, an adaptive fixed-time attitude control method is proposed, which is based on a radial basis function neural network (RBFNN). Firstly, a spacecraft attitude kinematics and dynamics model is established based on the quaternion method and a Gaussian error function is introduced to constrain the controller amplitude. Secondly, the external unknown disturbances are addressed by a fixed-time disturbance observer, and the controller is designed utilizing the backstepping method. To eliminate the adverse effects caused by actuator saturation, we design an enhanced auxiliary system to improve the stability of the system. Aiming at inertia uncertainties, RBFNN is used to approximate it, and an innovative fixed-time convergence adaptive law with RBFNN weights is devised. Subsequently, based on Lyapunov theory, the fixed time stability of the closed loop system is proven, and an expression for the settling time is given. Finally, simulation analysis validates the effectiveness of the designed controller.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109746"},"PeriodicalIF":5.0,"publicationDate":"2024-11-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142696825","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":"Self-adaptive turbulence eddy simulation of a supersonic cavity-ramp flow","authors":"Pengfei Xie ,&nbsp;Gaofeng Wang ,&nbsp;Wenchang Wu ,&nbsp;Xingsi Han","doi":"10.1016/j.ast.2024.109758","DOIUrl":"10.1016/j.ast.2024.109758","url":null,"abstract":"<div><div>High Reynolds number supersonic wall-bounded turbulent flow is common in the aviation industry. However, accurately predicting this flow remains a long-standing challenge for turbulence modeling, particularly in separation cases. This study presents a numerical investigation of a Mach 2.92 turbulent cavity-ramp flow employing a new hybrid turbulence modeling approach, denoted as the self-adaptive turbulence eddy simulation (SATES) method. The results are compared with experimental data, as well as with outcomes from the conventional Reynolds-averaged Navier–Stokes (RANS) method and the previous delayed detached eddy simulation (DDES). The SATES model demonstrates a satisfactory prediction of time-averaged and fluctuating quantities in the free shear layer, redeveloping boundary layer, and ramp, showing better accuracy than the RANS results. Notably, the SATES results from the medium grid exhibit similarities to the DDES results from the extremely fine grid which is about 26 times compared with the SATES mesh. Furthermore, the significant features of the supersonic reattached flow, including turbulent properties, vortex structures, and unsteadiness characteristics, are analysed in detail, including the Reynolds stresses anisotropy invariant maps, transport process of vorticity, and frequency spectra. This work confirms that accurate numerical predictions of high Reynolds number supersonic separated and reattached flows are achievable using the SATES method with a relatively coarse mesh maintaining an affordable computational cost.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"156 ","pages":"Article 109758"},"PeriodicalIF":5.0,"publicationDate":"2024-11-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702006","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":"Multi-physical fields prediction model for turbine cascades based on physical information neural networks","authors":"Lele Li ,&nbsp;Weihao Zhang ,&nbsp;Ya Li ,&nbsp;Chiju Jiang ,&nbsp;Yufan Wang","doi":"10.1016/j.ast.2024.109709","DOIUrl":"10.1016/j.ast.2024.109709","url":null,"abstract":"<div><div>The flow field information within the cascade is crucial for turbine design. Currently, the physical field data in the cascade is mostly obtained through numerical simulation, which is accurate but time-consuming. To enable fast and accurate prediction of the physical fields within the cascade, this study proposes a Physics-Informed Fourier Neural Operator (PIFNO) model. Compared to pure data-driven surrogate models, PIFNO incorporates partial physical information into the modeling process through a physics-head correction approach during training, which not only improves prediction accuracy but also enhances model interpretability to some extent. To expand the applicability of PIFNO, this paper proposes a Transfer Learning-based multi-physics fields prediction model (TL-PIFNO) that can predict the physical fields within the cascade under different operating conditions using limited training data. Experiments show that PIFNO has relative errors within 2% for pressure and temperature field prediction, and maximum relative errors within 5% for velocity field prediction. TL-PIFNO can achieve similar accuracy to PIFNO using only 3/10 of the data volume and 1/10 of the training time, showing great potential for engineering applications.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109709"},"PeriodicalIF":5.0,"publicationDate":"2024-11-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142696826","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":"Design approach for tilt propellers of UAM/eVTOLs for cruise and hover considering aerodynamic and aeroacoustic characteristics via a multi-fidelity model","authors":"Yingzhe Ye ,&nbsp;Yu Liang ,&nbsp;Xiaowen Shan ,&nbsp;Kefu Huang","doi":"10.1016/j.ast.2024.109739","DOIUrl":"10.1016/j.ast.2024.109739","url":null,"abstract":"<div><div>The design of quiet and efficient propellers/rotors is driven by the rapid development of Vertical Takeoff and Landing (VTOL) vehicles in urban areas. However, this task is challenging due to the expensive computational cost of propeller aerodynamic and aeroacoustic optimization based on accurate high-fidelity (HF) models. In contrast, many low-fidelity (LF) methods are less costly but also less accurate for complex propeller blade geometries, such as those involving sweep. This work aims to use a multi-fidelity (MF) surrogate model (SM) that combines a small HF data set for accuracy and a larger LF data set to speed up modeling. The MF approach inherits the accuracy of the HF method while retaining the computational efficiency of the LF model. The HF and LF aerodynamic data sets for training the MF model are obtained from a RANS solver and a meshless Large Eddy Simulation (LES) method, respectively. The obtained surface pressure of the blade is then used to calculate the noise signals radiating from the propeller using a Farassat's Formulation 1A (F1A) code. For practical design, we developed an optimization framework that combines these aerodynamic and aeroacoustic solvers, the MF model, design of experiment (DoE), and a multi-objective optimizer. The framework aims to optimize the blade aerodynamic shape in terms of chord, twist, and sweep distributions along the span from a baseline propeller, with objectives of efficiency and noise reduction under thrust constraints for both cruise and hover operating conditions. The obtained optimal designs, in the form of three-dimensional Pareto fronts, increased the aerodynamic efficiency by approximately 2% for cruise and 5% for hover and decreased the overall sound pressure level (OASPL) for hover by about 4 dB from the baseline propeller. The MF surrogate model, which utilizes both HF and LF data, doubled the optimization efficiency compared to the surrogate model based solely on HF data. Furthermore, the model based only on LF data fails to capture the three-dimensional flow effects induced by propeller sweep, which is crucial for reducing propeller noise. The aerodynamic benefits include reduced flow separation near the blade root during hover and more ideal loading distribution during cruise, while the aeroacoustic improvements are demonstrated through the “dephase” effect on noise signals emitted from different parts of the swept blade.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"156 ","pages":"Article 109739"},"PeriodicalIF":5.0,"publicationDate":"2024-11-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142696827","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":"Static and structural dynamic analysis of thick panel kirigami deployable structures","authors":"Junlan Li ,&nbsp;Cheng Wang ,&nbsp;Yucheng Yan ,&nbsp;Peng Wang ,&nbsp;Jieliang Zhao ,&nbsp;Dawei Zhang","doi":"10.1016/j.ast.2024.109753","DOIUrl":"10.1016/j.ast.2024.109753","url":null,"abstract":"<div><div>Thick panel origami and kirigami concepts have been wildly used to design novel deployable structures in various engineering applications. However, these novel folding methods usually involve complex connected topologies, which may lead to unclear and intricate characterized relationships between system properties and structural parameters, e.g., the position of cutting creases, design parameters and hinge stiffness arrangement, etc. In this paper, we propose theoretical models to describe the static and dynamic properties of thick panel kirigami structure in the fully deployed configuration. Firstly, the connected topology of the origami and kirigami structure is analysed, and the internal coupling topology of the structure is obtained. Based on the compliant matrix method, the static model of the structure is presented, and the different crease cutting modes of origami and kirigami arrays are discussed. Then, the motion modes of slight oscillation of structure are discussed and the structural dynamic model is obtained based on the Lagrange equation and validated by simulation. On this basis, the sensitivity analysis of the parameters is carried out, and the optimization model is given based on the comprehensive performance evaluation function. A physical prototype is optimized and tested, which indicates that our model is valid. This paper provides models for the structural static and dynamic properties of thick panel kirigami structures with complex connected topology, and the findings have a potential to be developed in other thick panel structures with origami and kirigami folding concepts.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109753"},"PeriodicalIF":5.0,"publicationDate":"2024-11-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142696829","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":"Free vibration characteristics of honeycomb sandwich cylindrical shells reinforced with graphene nanoplatelets/polymer coatings","authors":"Pham Toan Thang,&nbsp;Changsoo Kim,&nbsp;Hyounseung Jang,&nbsp;Taehoon Kim,&nbsp;Jimin Kim","doi":"10.1016/j.ast.2024.109744","DOIUrl":"10.1016/j.ast.2024.109744","url":null,"abstract":"<div><div>This study conducts a comprehensive analysis of the free vibration characteristics of honeycomb sandwich cylindrical shells reinforced with graphene nanoplatelets (GNPs). The shells are modeled with a hexagonal honeycomb core, which not only provides a lightweight structure but also enhances the stiffness and dynamic stability. This core design is ideal for high-performance applications such as aerospace and light transport equipment. In addition, the incorporation of graphene nanoplatelet/polymer coatings further improves the structural stiffness, making these shells suitable for demanding environments where both strength and lightweight properties are critical. In the theoretical model, the refined trigonometric shear deformation theory (RTSDT) is applied to accurately represent both bending and shear deformations, capturing the complex behavior of honeycomb sandwich cylindrical shells without requiring shear correction factors. Various parameters, including axial and circumferential wave numbers, as well as geometry and material properties, are examined to assess their impact on natural frequencies. Comparisons with existing literature validate the theoretical models, demonstrating strong agreement with previous results. The analysis reveals that the fundamental natural frequency and other natural frequencies are significantly affected by the inclusion of GNPs and variations in sandwich cylindrical shell geometry. The findings underscore the effectiveness of the RTSDT in modeling these complex sandwich structures.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"156 ","pages":"Article 109744"},"PeriodicalIF":5.0,"publicationDate":"2024-11-19","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142748138","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":"Aerodynamics coupling study on the tail cone electrical ducted fan integrated with fuselage","authors":"Hanru Liu ,&nbsp;Jiahui Li ,&nbsp;Yuyao Feng ,&nbsp;Yangang Wang ,&nbsp;Xuewei Sun","doi":"10.1016/j.ast.2024.109749","DOIUrl":"10.1016/j.ast.2024.109749","url":null,"abstract":"<div><div>The tail cone thruster configuration is an important layout to realize the hybrid electric propulsion technology. This study carries out numerical simulation on the scaling tail-cone electrical ducted fan integrated with fuselage. The performance change of the ducted fan under the boundary layer ingestion and the overall benefit in the tail cone thruster layout are investigated. The results show that compared with the isolated fan, the thrust of the tail cone thruster layout increases by 2%. The fan isentropic efficiency is decreased by 1.03%, but the fan propulsive efficiency is increased by 15.48%. The influence of the axial installation position of the fan on the aerodynamic performance is analyzed. The results show that as the axial installation position increases, the propulsive efficiency first increases and then decreases. When the axial installation position increases to 1.71D, the propulsive efficiency is increased by 0.26% compared with 1.58D. The investigation of angle of attack shows that the aerodynamic performance of the tail cone thruster layout has no obvious change in the range of 0° to 5° angle of attack. However, when the angle of attack increases from 10° to 15°, the overall thrust is decreased significantly by 42.60%.</div></div>","PeriodicalId":50955,"journal":{"name":"Aerospace Science and Technology","volume":"155 ","pages":"Article 109749"},"PeriodicalIF":5.0,"publicationDate":"2024-11-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"142702116","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}