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Dynamic-matching adaptive sliding mode control for hypersonic vehicles Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-23 Chaoran Qu, Lin Cheng, Shengping Gong, Xu Huang
Hypersonic vehicles exhibit significantly varied dynamic characteristics across different flight regimes. These characteristics, such as model uncertainties and actuator saturation levels, have strong time-varying properties, necessitating a control strategy capable of adaptively matching robustness and responsiveness to such variability. This paper introduces an adaptive sliding mode control strategy
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A tensor basis neural network-based turbulence model for transonic axial compressor flows Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-23 Ziqi Ji, Gang Du
Traditional turbulence models encounter limitations when simulating intricate flows within transonic axial compressors. In contrast, recent advancements in machine learning turbulence models have demonstrated enhanced potential in refining the precision of turbulence modeling. Notably, the tensor basis neural network (TBNN) methodology has successfully developed non-linear eddy viscosity turbulence
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On minimum power flight formations of lifting propellers Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-21 Dima Usov, Timotheos Chronis, Iuliu-Cezar Ardelean, Antonio Filippone
The present study delves into the problem of minimum-power formation of independent, non-articulated, lifting propellers in edgewise flight. Formation flight of free-flying fixed wings has been well addressed, demonstrating the importance of mutually induced upwash. However, there is a need to understand how this mechanism relates to the optimal flight formation of an arbitrary number of free-flying
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Collaborative target assignment problem for large-scale UAV swarm based on two-stage greedy auction algorithm Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-18 Guihao Wang, Fengmin Wang, Jiahe Wang, Mengzhen Li, Ling Gai, Dachuan Xu
This paper introduces a collaborative allocation model designed for multiple UAVs and diverse targets in maritime combat situations. The model incorporates factors such as distance, angle, interception rate, and recognition rate to comprehensively represent the UAVs' overall damage advantage against targets. Given the complexity of real-world environments and real-time demands, large-scale UAV swarm
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Freestream turbulence effects on low Reynolds number NACA 0012 airfoil laminar separation bubble and lift generation Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-17 Meilin Yu, John T. Hrynuk, David T. Booth, Naresh Poudel
Laminar separation bubbles (LSB's) over the suction surface of a wing at low Reynolds number ( based on the airfoil chord length) can significantly affect the aerodynamic performance of the wing, and pose a unique challenge for the predictive capabilities of simulation tools due to their high sensitivity to flow environments and wing surface conditions. In this work a series of two-dimensional (2D)
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Transonic buffet simulation using a partially-averaged Navier-Stokes approach Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-17 Andrea Petrocchi, George Barakos
The present article assesses the capability of the partially averaged Navier-Stokes (PANS) method to reproduce accurately the self-sustained shock oscillations, also known as transonic buffet, occurring on airfoils and wings at transonic regime under certain conditions of Mach number and angle of attack. The test case under analysis is an OAT15A unswept wing at Mach number and Reynolds number . The
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Autonomous spacecraft collision avoidance with a variable number of space debris based on safe reinforcement learning Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-17 Chaoxu Mu, Shuo Liu, Ming Lu, Zhaoyang Liu, Lei Cui, Ke Wang
The avoidance of multiple space debris collisions by autonomous spacecraft has garnered significant interests worldwide. Applying deep reinforcement learning (DRL) to autonomous spacecraft collision avoidance problems is still difficult because of limitations on constraint satisfaction and environment state perception, even if DRL is a suitable model-free and data-driven framework. In this research
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UAV trajectory tracking under wind disturbance based on novel antidisturbance sliding mode control Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-16 Qi Wang, Wei Wang, Satoshi Suzuki
With the widespread application of unmanned aerial vehicles, harsh environments require higher control performance. Numerous existing works offer solutions for handling external disturbances during flight; however, the timeliness of the disturbance compensation is rarely discussed. This study focuses on trajectory tracking under external wind disturbances, specifically under two types of interference:
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An improved energy management strategy for hybrid electric powered aircraft based on deep reinforcement learning Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-16 Liaolei He, Fang Chen, Peidong Tian, Huaxing Gou
Electric airplanes have attracted a great deal of attentions because of their strategic commercial values and low emissions. One of the essentials for efficient control and management of hybrid electric propulsion aircraft is a well-designed energy management strategy (EMS). A new EMS approach based on deep learning is introduced in this study to realize thrust distribution and power distribution,
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Thrust vector V/STOL aircraft control based on angular acceleration estimation Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-16 Qi Zhu, Yongxi Lyu, Shan Huang, Jingping Shi, Xiaobo Qu, Zhunga Liu, Zehao Wang
In this paper, an adaptive-estimate-incremental nonlinear dynamic inverse (AE-INDI) flight control method is proposed to address the issue of inaccurate angular acceleration signals in the thrust vector control of vertical/short takeoff and landing (V/STOL) aircraft. First, considering the change of center of gravity (CG) caused by aircraft structure transformation, a model for the deflection of a
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Off-design characteristics of a scoop-type streamline-tracing scramjet inlet Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-14 Haechang Jung, Seong-kyun Im
This study investigates the off-design characteristics of a scoop-type streamline-tracing inlet, focusing on identifying its operable envelope using numerical and experimental methods, with experiments primarily conducted for validation purposes. The fixed geometry of streamline-tracing inlets necessitates this research, and a scoop-type inlet is targeted because it has the minimum viscous drag owing
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Sufficient active control of uncertain low-frequency space micro-vibrations near measurement limit of acceleration sensors Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-12 Qian Jia, Qing Li, Lei Liu
High-precision payloads such as ultra-stable optical clocks for next-generation space missions are greatly sensitive to the low-frequency micro-vibrations induced by various flexible appendages equipped on the spacecraft. The frequencies of such micro-vibrations are uncertain and near the measurement limit of acceleration sensors, leading to insufficient vibration control performance of classical feedback
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A three-stage sequential convex programming approach for trajectory optimization Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-12 Tengfei Zhang, Hua Su, Chunlin Gong
Recently, sequential convex programming (SCP) has become a potential approach in trajectory optimization because of its high efficiency. To improve stability and discretization accuracy, a three-stage SCP approach based on the -adaptive Radau pseudospectral discretization is proposed in this paper. In most instances, the initial subproblem may risk infeasibility due to the undesignated initial guess
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A ML strategy for the identification of optimal LPT design region and related blade shape Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-10 Daniele Petronio, Pietro Paliotta, Davide Lengani, Daniele Simoni
This work presents a machine-learning (ML) strategy for the identification of the design region that guarantees minimum losses for Low Pressure Turbine (LPT) blades, allowing the definition of the optimal blade shape. The data-driven procedure is twofold. Firstly, an advanced loss-correlation model (M1) that describes the LPT efficiency as a function of the main flow and geometrical parameters, also
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Flight dynamic modeling and stability of a small-scale side-by-side helicopter for Urban Air Mobility Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-09 Francesco Mazzeo, Marilena D. Pavel, Daniele Fattizzo, Giulia Bertolani, Emanuele L. de Angelis, Fabrizio Giulietti
This paper aims to explore the development of a flight dynamics model for a small-scale side-by-side helicopter and describe its trim and stability characteristics. The helicopter is considered a suitable candidate for Urban Air Mobility (UAM) solutions, because of its reliable design and low noise characteristics, but still very small knowledge is present on the mathematical modeling approaches and
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Predictor-based constrained fixed-time sliding mode control of multi-UAV formation flight Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-08 Maria Khodaverdian, Shahram Hajshirmohamadi, Aleksandr Hakobyan, Salman Ijaz
In this work, a predictor-based fixed-time sliding mode control is designed to tackle the problem of achieving precise trajectory tracking control of multiple unmanned aerial vehicle formation flight. The proposed approach simultaneously addresses various practical requirements, such as optimality, constraints, fixed-time convergence, external interferences, and computational burden. Initially, using
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Learning-based spacecraft multi-constraint rapid trajectory planning for emergency collision avoidance Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-07 Jianfa Wu, Chunling Wei, Haibo Zhang, Yiheng Liu, Kehang Li
Aim at the emergency collision avoidance scenarios caused by the close-range space debris, a learning-based spacecraft rapid trajectory planning method, which can adapt to complex constraints and satisfy the requirements of the business service and real-time replanning, is proposed in this paper. First, the emergency collision avoidance scenarios are initialized and the optimal multi-constraint avoidance
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A fast prediction model of blade flutter in turbomachinery based on graph convolutional neural network Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-06 Yupeng Liu, Yunzhu Li, Liangliang Li, Yonghui Xie, Di Zhang
With the development of gas turbine towards higher load capacity and improved efficiency, blade flutter has emerged as a significant obstacle in the further development of turbomachinery due to fluid-structure coupling phenomenon. However, the traditional numerical simulation methods lengthen the design cycle and reduce the optimization efficiency due to the expensive time and resource cost. To solve
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Evaluation of the mechanical properties and energy absorption in a novel hybrid cellular structure Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-06 Fatemeh Ghorbani, Hussain Gharehbaghi, Amin Farrokhabadi, Amir Bolouri
The present study proposes a novel hybrid cellular structure consisting of unit cells with different geometrical designs to tailor Young's modulus and improve the energy absorption capability. An analytical model was developed to predict the mechanical properties of the baseline cellular structure. Using the particle swarm optimization (PSO) algorithm, the geometry of two unit cells is designed with
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An integrated optimization method of multi-hierarchy variables for rudder structures with radial force transfer paths Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-05 Jian-Jun Gou, Shu-Zhen Jia, Hai-Tao Tian, Jia-Xin Hu, Chun-Lin Gong
The optimization of structures with beam-like force transfer paths for flight vehicles is closely dependent on the hierarchy decomposition and interaction effects of variables. In this work, the variable of a rudder structure with radial beams is decomposed into conventional hierarchies of topology and size and a new unconventional hierarchy of angle, which is a representational variable with implicit
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Data-driven controller and multi-gradient search algorithm for morphing airfoils in high Reynolds number flows Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-05 José M. Magalhães Júnior, Gustavo L.O. Halila, Kyriakos G. Vamvoudakis
In this paper, we propose a data-driven framework to control morphing airfoils in the subsonic flight regime, considering high Reynolds numbers with an efficient and safe way to reach a shape with improved values of the aerodynamic coefficients. The online solution is based on a data-driven controller combined with a surrogate model and a multi-gradient descent algorithm. Without full knowledge of
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Free vibration analysis of hybrid CNT/GPL-reinforced Porous composite plates under fluid-loading Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-04 Zhiqiang Feng, Xiaoli Yang, Hemad Keshavarzpour, Ali Ghasemi
The present study aims to explore free vibration analysis of hybrid reinforced porous composite plates subjected to fluid loading. The hybrid composite comprises a porous core layer covered by two reinforced porous face sheets. Graphene Platelets (GPLs) and Carbon Nanotubes (CNTs) are considered as reinforcement materials. The linear three-dimensional piezo-elasticity theory is employed to model the
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Flutter analysis of a rigid-flexible coupled composite space structure with momentum wheels under thermal load Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-04 Yi-Bo Wang, Ying-Jing Qian, Yue-Wu Wang, Xiao-Dong Yang, Lei Xu
The communication and observation spacecraft generally consists of the spacecraft body, the composite connecting beams, the working payload and the CMG/momentum wheel for integrated attitude-vibration control. When such complex space structure operates in near-Earth orbit, the sudden change in thermal load may cause a solar flux shock to the structure, which is likely to excite the flutter motion of
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Surrogate-based pneumatic and aerodynamic allocation design optimization for flapping-wing micro air vehicles Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-04 Hao Zheng, Zhonglai Wang, Wei Zhang, Haiyang Yu, Cui Wu
Determining the mapping relationships between the bionic structures and aerodynamic characteristics of flapping-wing micro air vehicles (FWMAVs), therefore optimizing their comprehensive performances of pneumatic functions and maneuvering capabilities, poses a formidable challenge. In this work, a surrogate-based approach is proposed to tackle the pivotal challenges. Firstly, an experimental surrogate
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Suboptimal guidance law against maneuvering target with time and angle constraints Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-03 Jiliang Xie, Kemao Ma
The impact time and angle constrained terminal guidance laws against a maneuvering target are usually designed under the assumption that the magnitude of the missile's velocity can be controlled, rather than a missile with uncontrollable speed because it is difficult to adjust the time-to-go due to the maneuver of the target. The main objective of this work is to propose a new guidance law to access
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Breaking the limitation of thermodynamic cycle efficiency of the plasma synthetic jet actuator: Noble gases Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-03 Jinfeng Li, Xiaobing Zhang
The low thermodynamic cycle efficiency of the plasma synthetic jet actuator (PSJA) limits its application in flow control of supersonic aircraft. To improve the thermodynamic cycle efficiency of the PSJA, the energy conversion process of the PSJA under single discharge has been investigated by thermodynamic theory analysis and numerical simulation. The relations between thermodynamic cycle efficiency
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Novel design method for inward-turning inlets with non-uniform inflow Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-03 Changkai Hao, Wenguo Luo, Zonghan Yu, Jianfeng Zhu, Yancheng You
For the integrated design of the forebody and hypersonic inlet, the non-uniform inflows generated by the forebody have significant impacts on the inlet performance. Traditional inlet designed by the Internal Conical Flow C (ICFC) flowfield or Method of Characteristics (MOC) flowfield, is difficult to match non-uniform inflows, which can easily lead to reduced captured flow and total pressure recovery
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Nonlinear resonant responses and chaotic dynamics of three-dimensional braided composite cylindrical shell Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-02 Wei Zhang, Huiying Zheng, Tao Liu, Yan Zheng, Yingjing Qian
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Influence of primary jets on the combustion performance of a rich quench lean combustor: A numerical and experimental investigation Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-02 Chaowei Tang, Jianhan Feng, Haibo Liu, Qian Yao, Wu Jin, Jianzhong Li, Li Yuan
The effect of primary hole jet on the Rich-burn/Quick-mix/Lean-burn (RQL) combustor was studied here by both experimental and numerical analysis approaches, where with a standard k-ε model was applied. To understand the influence of primary hole on the performance of RQL combustor, three primary hole jets configurations with different dimensions of layout were tested. Results from both experimental
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Multifunctional design of hierarchical corrugated metamaterial absorber realized by carbon fiber stitching Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-01 Linhao Cheng, Zhiheng He, Jiachen Dong, Leilei Yan, Xitao Zheng
Carbon fiber (CF) which has both mechanical and electromagnetic (EM) characteristics can achieve multiple functions by special designing, such as load bearing and EM wave absorption. In this work, based on the excellent mechanical properties of hierarchical corrugated sandwich structure (HCSS), a novel CF interlaminar reinforced hierarchical corrugated metamaterial absorber (HCMMA) is constructed.
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Large eddy simulation of pulsating film cooling on turbine vane Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-01 Yunan Wang, Zhenbing Luo, Yan Zhou, Wenqiang Peng
In this study, the large eddy simulation (LES) was employed to investigate the interaction mechanism between pulse jet and mainstream flow in turbine vanes, with a focus on assessing the impact of pulse frequency and amplitude on film cooling heat transfer. The results indicate that on the pressure surface, introducing pulsating coolant under high blowing ratio can effectively reduce the wall temperature
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Cascade ensemble learning for multi-level reliability evaluation Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-01 Lu-Kai Song, Xue-Qin Li, Shun-Peng Zhu, Yat-Sze Choy
For complex systems involving multiple operating conditions and multiple failure modes, its reliability analysis usually presents the cascade failure correlation between multiple levels (i.e., operating condition level, failure mode level) and the strong coupling analysis between multiple physical fields (i.e., fluid, thermal, structure), leading to the traditional integral or separate reliability
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Experimental and numerical investigations on non-synchronous vibration and frequency lock-in of transonic compressor rotor blades Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-01 Songbai Wang, Yong Chen, Yadong Wu
Non-synchronous vibration (NSV) problems in axial compressors are challenging and frequently result in high vibration stress or structural failure within the frequency lock-in region. A deeper understanding of the lock-in phenomenon in NSV is necessary to improve blade reliability and safety. In this study, an experiment was conducted on a multistage transonic axial compressor to obtain frequency lock-in
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Influence of backward-facing step (BFS) on three-dimensional flow behavior in transonic compressor cascade Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-30 Junbing Liu, Xiaoqiang Fan
High-performance compressor cascades are crucial components of aero-engine compressor stages and require wide operational ranges for optimal efficiency. This study examines the aerodynamic effects of implementing 0.5 mm high backward-facing steps (BFS) on the suction side of transonic compressor cascades. Numerical analyses were conducted to assess the influence of step position under specific operating
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Experimental and numerical investigation on thermochemical erosion and mechanical erosion of carbon-based nozzles in hybrid rocket motors Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-30 Xiangyu Meng, Hui Tian, Xianzhu Jiang, Tianfang Wei, Guobiao Cai
In order to enhance energy characteristics of propellants in hybrid rocket motors, aluminum particles are added into the solid fuel. However, these particles may lead to nozzle mechanical erosion, which significantly affects the motor performance. This paper intends to study thermochemical and mechanical erosion mechanism of carbon-based nozzles in hybrid rocket motors with aluminum metallized fuel
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Aeroacoustic characteristics of a strut-braced high-lift device Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-29 Luke Bowen, Hasan Kamliya Jawahar Jr., Mahdi Azarpeyvand
The aerodynamic and aeroacoustic performance of a strut-based high-lift device were evaluated and demonstrated for six different strut models. The primary objective of the study was to investigate the impact of strut modifications on reducing noise levels. The aerodynamic characteristics are presented with the aid of surface pressure distribution on the airfoil that remained consistent across all the
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Experimental study on the synergy of sweeping jets on the afterbody flows of a slanted-base cylinder Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-29 Xiaodong Chen, Shan Zhong, Tanghong Liu, Jie Zhang, Ozgun Ozer, Guangjun Gao
The synergistic effects of sweeping jets (SWJs) hold significant potential in controlling afterbody vortex flows of a cargo fuselage. A combination of SWJ pairs, located at various streamwise positions, are employed to investigate the efficiency of their synergy in influencing the afterbody flows of a slanted-base cylinder with a 30° angle at a Reynolds number of 200,000. The total mass flow rate is
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Low-velocity impact simulation of carbon fiber reinforced composite laminate using IFF-criterion based on BP-ANN Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-29 Zhuo Zhang, Kai Zhang, Gang Zhang, Bailin Zheng
Damage characteristics of composite materials after low-velocity impacts are hard to predict and numerical simulation is time-consuming. This paper explores a study in carbon fiber reinforced composite (CFRP) laminates low-velocity impact (LVI) simulation with Puck inter-fiber failure (IFF) criterion based on the back-propagation neural network (BP-ANN) model. LVI numerical simulations under three
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Hypersonic boost-glide systems: Flight mechanics and plasma parameters evaluation through aero-thermo-chemical computational fluid dynamics Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-29 Ragnoli Giona, Savino Raffaele, Cecere Anselmo, Rigamonti Marco
Currently, the conception, design, and development of hypersonic space-borne systems is a central topic of discussion among researchers and industrial stakeholders. In the design phase of a hypersonic manoeuvrable vehicle, it is essential to characterise the thermal heating and manage the problem of the communication blackout, in addition to other challenges concerning guidance, navigation and control
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Hierarchical temporal sequence convergence in prescribed-time control for quadrotor UAVs under unknown dynamic disturbances Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-28 Hua Bai, Sen Mei, Jiuxiang Dong
This paper studies the trajectory tracking control problem for quadrotor unmanned aerial vehicles (UAVs) under unknown disturbances and model uncertainties. A priori information about disturbances is required for most existing prescribed time-extended state observer (PTESO) methods. For unknown disturbances, a barrier function-based adaptive prescribed-time extended state observer (BFAPTESO) is designed
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Robust attitude control of a flexible satellite assembled with a partially expanded coilable mast Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-28 Liming Fan, Yanjun Xing, Zongbo He, Qiang Zhang, Zeming Chen
This paper investigates the attitude control system of a flexible satellite consisting of a rigid main-satellite, a partially expanded coilable mast and a rigid sub-satellite. Multiple critical information such as the length of deployed coilable mast, system damping and stiffness matrices are uncertain. The satellite also suffers from parameter perturbation, external disturbance, flexible vibration
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Autonomous morphing strategy for a long-range aircraft using reinforcement learning Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-27 Baochao Zhang, Jie Guo, Haoning Wang, Shengjing Tang
A novel morphing strategy based on reinforcement learning (RL) is developed to solve the morphing decision-making problem with minimum flight time for a long-range variable-sweep morphing aircraft. The proposed morphing strategy focuses on the sparse-reward no-reference decision-making problem caused by terminal performance objectives and long-range missions. A double-layer morphing-flight control
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Traveling wave vibration and critical rotating speed of rotating porous metal conical shell with elastic boundary conditions Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-26 L. Sun, Y.X. Hao, W. Zhang, H. Li
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Aerodynamic performance of a flyable flapping wing rotor with dragonfly-like flexible wings Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-26 Y. Pan, S. Guo, J. Whidborne, X. Huang
Drawing inspiration from insect flapping wings, a Flapping Wing Rotor (FWR) has been developed for Micro Aerial Vehicle (MAV) applications. The FWR features unique active flapping and passive rotary kinematics of motion to achieve a high lift coefficient and flight efficiency. This study thoroughly investigates the aerodynamic performance and design of a bio-inspired flexible wing for FWR-MAVs, emphasizing
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Unified path planning for composite UAVs via Fermat point-based grouping particle swarm optimization Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-26 Yunpeng Li, Lixian Zhang, Bo Cai, Ye Liang
This paper is concerned with the problem of path planning for a class of composite unmanned aerial vehicles (UAVs). The composite UAV in the paper refers to an aerial vehicle consisting of a carrier UAV and several parasite UAVs to be launched, which combines the advantages of long flight range and high flexibility. A Fermat point-based grouping particle swarm optimization (FP-GPSO) algorithm is proposed
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Learning Chebyshev neural network-based spacecraft attitude tracking control ensuring finite-time prescribed performance Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-25 Qingxian Jia, Genghuan Li, Dan Yu, Choon Ki Ahn, Chengxi Zhang
This article presents a finite-time prescribed performance (FTPP) control approach based on a learning Chebyshev neural network (LCNN) for spacecraft attitude tracking with modeling uncertainties, actuator faults, and external disturbances. An FTPP function is designed to specify the desired accuracy boundary and finite-time convergence. Further, an FTPP-based learning sliding mode controller (LSMC)
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Natural frequencies and modal shapes of folded sandwich plates made of porous core and FG-CNTRC coating layers resting on two parameters elastic foundation Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-25 Hamzeh Salehipour, Mohammad Amin Shahmohammadi, Ömer Civalek
Folded structures hold significant importance in aerospace technology due to their distinct design, effectively reconciling strength with a lightweight framework. Within aerospace applications, these structures fulfill diverse roles, serving as pivotal elements in aircraft wings, fuselage sections, and essential components of spacecraft and satellites. This study delves into the free vibration behavior
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Optimization of high-speed fixed-wing UAV penetration strategy based on deep reinforcement learning Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-24 Xing Zhuang, Dongguang Li, Yue Wang, Xinyu Liu, Hanyu Li
The penetration decision of unmanned aerial vehicles (UAVs) is one of the key components for UAVs to detect or strike crucial targets in adversarial environments. Presently, most methods lack research on penetration decisions under unknown interception information. The executing UAV for decision-making is generally a simplified three-degree-of-freedom model. The decision format is often simplified
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Operational mechanism of valved-pulsejet engines Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-24 Mohamad M. Ghulam, Shyam S. Muralidharan, Vijay Anand, Erik Prisell, Ephraim J. Gutmark
The study investigates twelve configurations of the self-aspirated valved pulsejet, focusing on its operational mechanism. It begins by characterizing the engine's acoustic field with varied boundary conditions, revealing an extended effective acoustic length beyond the combustion chamber and tailpipe sections when the valve is open. Radial and lateral velocity fluctuations are hypothesized as causes
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Scale effect on wave planing performance of amphibious aircraft at constant speed Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-24 Jichang Chen, Le Li, Xiaoqin Fu, Tianhang Xiao, Bin Wu, Mingbo Tong
Scaled model testing is commonly recognized as a valuable approach for predicting aircraft performance in the aeronautical applications. However, challenges arise in the case of wave planing events for amphibious aircraft due to difficulties in satisfying the scaling laws of Reynolds number and Froude number simultaneously in a water tank. Therefore, it is important to evaluate the scale effect of
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Multiobjective aerostructural optimization for efficient transport wing conceptual design Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-21 Spyridon G. Kontogiannis, A. Mark Savill, Vasileios Mazis, Vangelis Skaperdas
The advantages of Multidisciplinary wing development are only gradually being exploited in an industrial level, largely halted by the inevitable design space complexity arising from the interacting disciplines and objective constraints. An industrial tool has to provide design space exploration early in the design process and be reliable enough to guide subsequent fine-tuning optimization studies.
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Nonlinear dynamic modelling and analysis of a rotating composite thin-walled beam considering ice coating Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-20 Xiao Li, Ji'an Li, Yinghui Li, Ming Li
For rotating structures operating in severe weather conditions, ice coating phenomenon is an established issue that impairs the reliability and effectiveness of the structures by changing the dynamic behaviors. To explore the influence mechanisms of ice coating on the dynamic behaviors of rotating structures, this work presents an analytical dynamic model for nonlinear forced vibration of a composite
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Coordinated transportation of tethered multi-rotor UAVs based on differential graphical games Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-20 Ya Liu, Zhuochen Ma, Fan Zhang, Panfeng Huang, Yingbo Lu, Haitao Chang
This paper investigates the stability control of the tethered multi-rotor unmanned aerial vehicles (T-MRUAVs) system in cargo delivery, where precise payload trajectory control is deemed unnecessary, with a focus on enhancing controller simplicity and robustness. To achieve this objective, it is imperative to employ an optimal formation tracking control, ensuring not only the symmetrical positioning
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Failure mechanisms and process defects of 3D-printed continuous carbon fiber-reinforced composite circular honeycomb structures with different stacking directions Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-20 Xin Zhang, Xitao Zheng, Yagang Han, Yuanyuan Tian, Di Zhang, Leilei Yan
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Optimal microphone selection for aero-engine acoustic measurement Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-20 Zepeng Li, Baijie Qiao, Bi Wen, Xuefeng Chen, Andreas Jakobsson
Acoustic testing is crucial in the aero-engine design process, providing valuable information about the sound field in terms of acoustic modes. The conventional use of a uniform sampling array limits the achievable resolution for a given number of sensors, necessitating the use of a large number of sensors to achieve high-resolution estimates. This limitation may be overcome using a non-uniform sensing
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Scaling laws of Space Solar Power Satellite concentrator unit distortion model obtained by performance-driven separate similitude analysis method Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-19 Yingchun Du, Guanheng Fan, Guangda Chen, Yiqun Zhang, Dongxu Wang, Xintong Li
The distortion model may arise due to the inability to isometrically scale the thickness dimensions when utilizing similitude theory to develop scaling laws for large-scale concentrator units in the Space Solar Power Satellite. Previous works to address the distortion model neglect its negative impacts and persistent limits, resulting in insufficient prediction accuracy for prototype. To obtain scaling
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Improvement of labyrinth seal performance using the partial honeycomb lands Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-18 Hyeok Je Kim, Young Jun Kang, Woojun Kim, Won Seok Lim, Suhyeon Park, Jae Su Kwak
In this study, a partial honeycomb land was proposed for improving the sealing performance of a labyrinth seal which has been widely applied to the low-pressure section of a gas turbine. The partial honeycomb land in this experiment is distinguished by a solid strip under the fin of the honeycomb land labyrinth seal. The tested fin front angle of the labyrinth seal was 60°, and the clearance size ranged
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Effect of upstream injection on local flame intensity in a scramjet combustor fueled with liquid kerosene at Mach 4 flight condition Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-18 Heng Bao, Daoning Yang, Wanshen Nie, Zongyang Wang, Chuanjin Jiang
The intensity of the local flame generated by spark ignition was investigated in a scramjet combustor fueled with liquid kerosene under Ma 4 flight conditions. The study utilized wall pressure evolution and high-speed imaging during experiments to assess the local flame intensity. The rise in wall pressure near the aft edge of the cavity was found to be an indicator of local flame intensity, and the
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Accelerated formulation of optimal control law for adaptive cycle engines: A novel design methodology Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-17 Man Zhen, Xuezhi Dong, Xiyang Liu, Chunqing Tan
Adaptive cycle engines (ACEs) represent a sophisticated class of power units, embodying numerous variable geometry components, marking them as pivotal for the advancement of next-generation high-speed civil and military engines. Nonetheless, this variability introduces substantial complexity into the engineering of control laws. Contemporary research predominantly relies on either manual methodologies
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Bending information of nanocomposites-reinforced microplate subjected to transient loading: Introducing physics-informed machine learning algorithm for solving the transient problem Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-16 Yuan Fang, Rizwana Irfan, Ahmad Almadhor, Mohamed Abbas
Due to the importance of microplate structure in some related industries especially in microchips, transient dynamics analysis of microplate has got a lot of attention, recently. For this issue, in the current work, for the first time, transient dynamics analysis of microplate reinforced by graphene nanoplatelets composites (GPCs) using both mathematical modeling and physics-informed machine learning