样式: 排序: IF: - GO 导出 标记为已读
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Improving the combustion of scramjet engines with struts using grooves and bumps Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-13 Zhi-Qiang Sheng, Lan Zhang, Liang-Ze Lu, Jing-Yuan Liu, Xiao-An Hu
Grooves and bumps are arranged on both sides of a normal strut (NS) to fabricate vortex generators, and introduce streamwise vortices. Struts with sawtooth grooves (GS-1), rectangular bumps (BS-1), and trapezoidal and triangular bumps (BS-2) have been proposed. In this study, struts with V-shaped grooves (GS-2) and trapezoidal and triangular bumps (BS-3) were configured. The flow fields in the cold
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Aerodynamic shape optimization based on Proper Orthogonal Decomposition reparameterization under small training sets Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-12 Yuxin Yang, Youtao Xue, Wenwen Zhao, Hua Yang, Changju Wu
Complex shape aerodynamic optimization frequently encounters the problem of dimensionality curse. Extracting geometric features from the original design space proves effective in this issue by reconstructing shapes with lower-dimension. While deep learning methods possess strong capabilities in dimensionality reduction, they suffer from longer training times and higher computational resource requirements
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A Nonlocal Higher-Order Shear Deformation Approach for Nonline ar Static Analysis of Magneto-Electro-Elastic Sandwich Micro/Nano-plates with FG-CNT Core in Hygrothermal Environment Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-12 Vu Thi Thuy Anh, Ngo Dinh Dat, Pham Dinh Nguyen, Nguyen Dinh Duc
In this study, the nonlocal static analysis of Magneto-Electro-Elastic (MEE) sandwich micro/nano-plates with Functionally Graded Carbon Nanotubes (FG-CNTs) core in a hygrothermal environment is studied. The nonlocal static formulation is developed based on Reddy's High-order Shear Deformation theory (HSDT). The von Kármán nonlinear strains are used and the governing equations of the HSDT are derived
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Data-Driven Integrated Study on Operational Performance Degradation Detection and Recovery Control of VFDR Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-12 Zongyu Zhang, Qinghua Zeng, Meng Tang, Xiaoyu Ye, Jie Zhang
The Variable Flow Ducted Rocket (VFDR) serves as the preferred propulsion system for hypersonic aircraft. However, it is prone to health degradation issues due to component failures, aging, and changes in operational conditions, which significantly challenge flight safety. This study introduces a data-driven integrated control approach for modeling, diagnosing, and remedying performance deterioration
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Fast initialization of the indirect optimization problem in the solar sail circle-to-circle orbit transfer Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-12 Alessandro A. Quarta
This Short Communication presents a procedure to approximate, in an analytical form, the solution of the optimization problem that gives the minimum-time trajectory of a low-performance solar sail, in a classical circle-to-circle heliocentric transfer. More precisely, the proposed procedure gives an accurate approximation of the solution of the two-point boundary value problem associated to the optimization
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Negative-Imaginary-based Spacecraft Attitude Tracking control Using Modified Rodrigues Parameters Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-12 Xiaoyu Lang, Xiangdong Liu, Zhen Chen
This paper investigates a counter-clock-wise input-output map about spacecraft attitude dynamics and kinematics using Modified Rodrigues Parameters. A gyro-free attitude control scheme is established by constructing a negative imaginary system for spacecraft attitude stabilization. Attitude tracking control scheme is also explored where the negative-imaginary-based controller has no need on the angular
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A disturbance rejection control for urban air mobility using artificial sensor-based Gaussian process regression Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-12 Dain Yoon, Chang-Hun Lee
This paper presents a learning-based disturbance rejection control strategy for Urban Air Mobility (UAM) with vertical take-off and landing capability, which is subject to uncertainties in system parameters. The two primary sources of uncertainty during UAM operation, specifically moment of inertia uncertainty and center of gravity variation, are thoroughly analyzed as they negatively impact control
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Study of the spike-aerodisk-opposing jet on heat protection to both the spike-aerodisk and the blunt body and overall drag reduction in rarefied hypersonic flow in near space Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-11 Zi-jian Ni, Shu-zhou Fang
The Direct Simulation Monte Carlo method (DSMC) is utilized in this study to investigate the flowfield surrounding the spike-aerodisk without and with an opposing jet under rarefied hypersonic conditions within near space (altitudes of 60∼90 km and Mach numbers 7∼20). As the flight altitude increases, the incoming flow gradually becomes rarefied, weakening the drag reduction effect of the spike-aerodisk
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Nonlinear aero-thermo-elastic flutter analysis of stiffened graphene platelets reinforced metal foams plates with initial geometric imperfection Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-11 Jin-Peng Song, Gui-Lin She, M.A. Eltaher
Due to its lightweight design and high load-bearing capacity, the stiffened plate structure is extensively applied in the passive control of aircraft flutter. However, the evolution mechanism of the nonlinear response of stiffened plates within the unstable region remains unclear. In particular, there is a lack of research on the nonlinear aero-thermo-elastic properties of stiffened plates with initial
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Optimization and experimental study of stationary endwall of stator labyrinth cavity in a low-speed research compressor Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-11 Biaojie Zheng, Runzhu Shao, Songan Zhang, Mingmin Zhu, Xiaoqing Qiang, Jinfang Teng
Controlling the leakage flow of the labyrinth seal cavity is very important for the efficiency and aerodynamic matching design of aero-engine high-pressure compressor. However, due to the complexity of the geometry and internal flow of the labyrinth seal cavity, the design optimization of the labyrinth seal cavity is rarely studied. In this paper, a multi-objective design optimization method was used
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Passivity-Based Fractionated Payload 6-DOF Maneuver Control using Electromagnetic Actuation Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-09 Yan Qin, Xiaoyu Lang
Employing fractionated spacecraft architecture with electromagnetic actuation into space missions can enhance resilience and flexibility since all subsystems of conventional monolithic spacecraft are separated as several modules to be easily replaced on-orbit when failure happens. Previous electromagnetic configuration used in fractionated spacecraft would render unexpected forces and torques which
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Experimental Investigation of Secondary Flow Losses in a Variable Geometry Linear Turbine Cascade with Winglet Tip Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-09 Yueqi Liu, Shaowen Chen, Chen Xu
Variable geometry turbines (VGT) hold a crucial role in gas turbines and variable cycle engines (VCE) by allowing adjustments to different operational conditions. In order to realize the adjustable function of the VGT stator blade, there will be partial gap structure at both ends of the stator blade, which will lead to partial leakage flow and serious secondary flow loss at the blade end that cannot
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Performance study of a central reentrant step pilot-flameholder in a dual-mode combustor Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-08 Liu Chen, Fan Yuxin
The augmented/ramjet combustion chambers are characterized by wide operating ranges, large flow state variations, and harsh operating conditions. The reliable ignition of these chambers urgently needs to be achieved. To improve the pilot ignition and blowout performance based on the centerbody in augmented/ramjet combustion chambers, a reentrant step flameholder is proposed on the basis of a conventional
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A novel calculation method for low-thrust transfer trajectories in the Earth-Moon restricted three-body problem Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-08 Chongrui Du, Liangjun Song, Jiye Zhang, Yi Liu
This paper introduces a novel trajectory calculation method for achieving continuous low-thrust transfers from the geostationary orbit to libration point orbits within the Earth-Moon restricted three-body framework. Low-thrust engines can offer benefits such as high specific impulse and long operating lifetimes, making them suitable for deep space exploration. However, the primary challenge lies in
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Multi-fidelity Simulation of Aeroengine across Wide Operation Range using Auxiliary Fully Coupled Method Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-07 Weimin Deng, Yibing Xu, Ming Ni, Zuojun Wei, Xiaohua Gan, Guangming Ren
Multi-fidelity simulations for the design point or equilibrium lines of aeroengines are implemented using fully coupled methods, simultaneously optimizing computational resources and speed. Fully coupled methods remove the requirement of characteristic maps by directly incorporating computational fluid dynamics models of subcomponents into the thermodynamic model of an aeroengine. However, poor convergence
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Analysis and modeling of the aerodynamic ceiling effect on small-scale propellers with tilted angles Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-07 Yiliang Liu, Zi Kan, Huadong Li, Yuzhe Gao, Daochun Li, Shiwei Zhao
Micro air vehicles with propellers have been widely used in military and civilian applications due to their high maneuverability and low cost. As the mission scenarios and requirements of rotorcrafts become more complex, proximity effects caused by confined environments, such as the ceiling effect cause significant interference to the performance and stability of rotors. Most researchers have analyzed
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Adaptively tracking hypersonic gliding vehicles Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-07 Zhao Li, Yidi Wang, Wei Zheng
The motion model plays a key role in tracking hypersonic gliding vehicles (HGVs). The process noise covariance matrix is used to scale the errors of the motion model, and its design has significant influence on the tracking accuracy. In this paper, a dynamics model with an adaptive process noise covariance matrix is proposed for tracking HGVs. The dynamics model is described by a nonlinear stochastic
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Distributed time-varying optimization with coupled constraints: Application in UAV swarm predefined-time cooperative consensus Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-06 Aiwu Yang, Xiaolong Liang, Jiaqiang Zhang, Yueqi Hou, Ning Wang
This paper addresses the global optimal consensus problem with time-varying objective functions and state-coupled inequality constraints. By integrating the predefined-time consensus and prediction-correction schemes, a distributed optimization protocol is proposed for the cooperative interception scenarios involving the unmanned aerial vehicle (UAV) swarm. Specifically, the -exact penalty method is
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Numerical Research on the Resonance Frequency Characteristics of the SparkJet Actuator using Modal Analysis Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-05 Jin Young Shin, Kyu Hong Kim
In this study, the resonance frequency characteristics of the SparkJet actuator are examined through numerical investigation using modal analysis. First, an eigenvalue problem is established to compute the resonance frequencies of the SparkJet actuator, considering its configuration, boundary conditions and internal physical phenomena. To validate the eigenvalue problem, computational fluid dynamics
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Design considerations for efficient spanwise-inclined air-jet vortex generators for separation control in supersonic and hypersonic flows Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-05 Robin Sebastian, Anne-Marie Schreyer
Shock-wave/boundary-layer interactions and associated flow separation are frequently occurring phenomena in many high-speed flow applications. Injection of spanwise-inclined air-jets is an efficient means to control shock-induced flow separation in supersonic and transonic flows. Separation-control studies in hypersonic flow are scarce and so far mostly restricted to microramp control. The objectives
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Flight dynamics of aircraft incorporating the semi-aeroelastic hinge Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-04 Huaiyuan Gu, Fintan Healy, Sanuja Jayatilake, Djamel Rezgui, Mark Lowenberg, Jonathan Cooper, Thomas Wilson, Andrea Castrichini
Aircraft like the Boeing 777-X use on-ground folding wingtips to meet the airport gate size restriction while increasing the aspect ratio during flight to reduce induced drag. A recent concept of aircraft design is to utilise in-flight floating wingtips as a means of load alleviation, which is known as semi-aeroelastic hinge (SAH). This device allows wingtips to be released during manoeuvre and severe
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Combined discrete Fourier transform method for azimuthal acoustic mode analysis Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-04 Siyin Liao, Min Zhu
Modal analysis is an effective and prevalent method for analysing and diagnosing oscillatory systems. In this study, a combined discrete Fourier transform (cDFT) method was developed in addition to the discrete Fourier transform (DFT) method and solving equation (SE) method for azimuthal acoustic mode analysis to utilize the advantages of both methods. cDFT transforms the original sampling matrix equation
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Development of maximum conical shock angle limit for osculating cone waveriders Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-04 Agnivo Ghosh, Srisha M.V. Rao
Hypersonic waveriders are special shapes with leading edges coincident with the body's shock wave, yielding high lift-to-drag ratios. The waverider geometry results from streamline tracing using the solutions of a basic flow field such as the wedge or the cone for specified shock and base curves. The base and shock curves can be independently prescribed in the osculating cone method enabling a larger
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Numerical investigation and experimental validation of aluminized propellant combustion under high pressures: Critical effects of heat feedback Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-03 Lu Liu, Gangchui Zhang, Zhan Wen, Shipo Li, Peijin Liu, Guoqiang He, Wen Ao
Aluminum is a common metal fuel in propellants, but its effects on the burning rate and the underlying mechanism are still unclear. Numerical calculations and temperature measurement experiments were carried out within the pressure range of 0.1–9 MPa, and the effects of the pressure and the ammonium perchlorate (AP) particle size on the combustion characteristics of aluminized propellants were studied
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Enhancing gust load alleviation performance in an optimized composite wing using passive wingtip devices: Folding and Twist approaches Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-03 Majid Ahmadi, Touraj Farsadi, Hamed Haddad Khodaparast
This paper introduces an innovative numerical method for the design and optimization of high-aspect-ratio composite wings equipped with passive control systems, specifically, Folding WingTip (FWT) and Twist WingTip (TWT) devices. The aim is to enhance Gust Load Alleviation (GLA) performance in the baseline wing. Recent numerical studies have indicated that the inclusion of spring devices and wingtip
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Experimental study on the influence of the wall cavity on stability of kerosene two-phase rotating detonation combustion Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-03 Yongbo Zhang, Yingchen Shi, Haocheng Wen, Bing Wang
The combustion characteristics in annular rotating detonation combustors are experimentally investigated using 40% oxygen-enriched air and liquid aviation kerosene (RP-3) as reactants. Two types of wall cavity structures, embedded in the outer and the inner wall of the annular combustors, respectively, are employed to study their effects on detonation stability. The characteristics of typical combustion
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Adaptive prescribed performance based on recursive nonsingular terminal sliding mode control for quad-rotor systems under uncertainty and disturbance: Real-time validation Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-02 Gao Han, Omid Mofid, Saleh Mobayen, Mohammad Hassan Khooban
In this paper, at the aim of the fast trajectory-following control of the Unmanned Aerial Vehicle (UAV) systems subject to uncertainty and disturbance, the adaptive prescribed performance control based recursive nonsingular terminal sliding mode control is suggested. Afterward, for the fast trajectory-following control of the uncertain and perturbed quad-rotor system, a recursive nonsingular terminal
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Isolated propeller aeroacoustics at positive and negative thrust Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-01 Jatinder Goyal, Francesco Avallone, Tomas Sinnige
Using propellers in negative thrust conditions can potentially result in many benefits, such as a steeper descent, a reduced landing run, reduced community noise, energy regeneration, etc. However, the aerodynamics and aeroacoustics of propellers in this regime are not well understood. This paper presents an aeroacoustic analysis of an isolated propeller operating in both positive and negative thrust
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Aerodynamic interaction between tandem propellers in eVTOL transition flight configurations Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-01 Alex Zanotti, Alessandro Velo, Chiara Pepe, Alberto Savino, Donato Grassi, Luca Riccobene
The present study investigates the aerodynamic interactions in a tandem propellers configuration typical of a tilt-wing eVTOL aircraft during the transition manoeuvre. Particular focus is on how the relative position and the propeller's tilting angle influence the aerodynamic performance. A systematic series of wind tunnel tests, including thrust and torque measurements with Particle Image Velocimetry
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Multi-objective aerodynamic optimization of expansion–deflection nozzle based on B-spline curves Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-01 Yong Wang, Qitai Eri, Jifeng Huang, Bo Kong
An expansion–deflection nozzle (EDN) is an altitude-compensated nozzle that can accommodate a wide range of nozzle pressure ratio (NPR) variations. An EDN design with good thrust performance under both high- and low-NPR conditions can effectively improve the launch capability of the vehicle. In this study, a multi-objective aerodynamic optimization design is developed considering the performance of
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FTDO-based adaptive fuzzy fixed-time tracking control for uncertain unmanned helicopter with output constraints Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-01 Haoxiang Ma, Ruonan Ren, Fazhan Tao, Zhumu Fu, Nan Wang
During the actual flight of unmanned helicopters, there are widespread output constraints, system uncertainties and external disturbances, which bring significant threats to their safe flight. To keep the output constraints from violating predefined boundaries, the barrier Lyapunov function (BLF) is utilized in this paper. The system uncertainties are estimated by the fuzzy logic system (FLS). The
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Optimal design of composite grid/skin structures based on deep learning and Double-Double layup strategy Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-03-01 Zhenyu Wang, Chuanxiang Zheng, Liang Wang, Jiaying Gu, Lei Jing, Xiaoliang Lai
This study introduces a novel two-stage optimization framework combining deep learning and genetic algorithms for the design of composite grid/skin structures. Firstly, an image dataset of 131,022 potential design configurations based on the Double-Double (DD) layup strategy is created. Subsequently, a deep-learning based Auto-encoder model is employed to extract the structural genes from this dataset
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Polynomial shaping based three-dimensional impact angle and field-of-view constrained guidance Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-29 Prajakta Surve, Arnab Maity, Shashi Ranjan Kumar
This paper proposes a polynomial-based three-dimensional (3D) impact angle-constrained guidance law considering the seeker's field-of-view (FOV) bound. The guidance laws are derived using nonlinear coupled dynamics of the interceptor-target engagement against stationary as well as constant velocity targets. Line-of-sight (LOS) orientations between the interceptor and the target in both pitch and yaw
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Simulation of supersonic axisymmetric base flow with a data-driven turbulence model Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-29 Seoyeon Heo, Yeji Yun, Minjae Jeong, Solkeun Jee
Axisymmetric base flow involves massive flow separation which is challenging for a typical Reynolds-averaged Navier-Stokes (RANS) turbulence model. Furthermore, a supersonic condition imposes additional difficulties to a turbulence model in predicting strong compressibility effects associated with the flow separation phenomena. A data-driven approach is pursued here to improve a turbulence model. The
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Flapping trajectory characteristics and attitude control approach of a flapping-wing robot with 2-DOF parallel mechanism Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-29 Liang Wang, Bifeng Song, Zhongchao Sun, Xiaojun Yang
This article investigates the flapping trajectory characteristics and attitude control methods of a flapping robot with the 2-degree-of-freedom (2-DOF) flapping mechanism. Inspired by the flying insects in nature, a 2-DOF parallel mechanism is utilized to realize the complex wingtip trajectories such as the elliptical and figure-of-eight shapes. Firstly, the kinematics of the mechanism are analyzed
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Simulation of wave mode switching in a rotating detonation engine with gaseous and liquid fuel Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-29 Marc Salvadori, Achyut Panchal, Suresh Menon
Three-dimensional simulations of a realistic two-phase rotating detonation engine are conducted to understand the effects of gaseous and liquid fuel on mechanisms of wave mode switching. A fully compressible solver coupled with an Eulerian-Lagrangian approach is used for this numerical study. Hydrogen and kerosene are used as gaseous and liquid fuels, respectively, with air as an oxidizer. Starting
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Physics-informed springback prediction of 3D aircraft tubes with six-axis free-bending manufacturing Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-28 Zili Wang, Yongzhe Xiang, Shuyou Zhang, Xiaojian Liu, Jun Ma, Jianrong Tan, Le Wang
As critical components of fluid transport and cooling systems, spatial tubes have broad applications in the aerospace industry. Six-axis free-bending (FB) technology provides a high level of processing flexibility, making it suitable for manufacturing complex spatial tubes. However, springback remains a critical problem affecting the tube dimensional accuracy in the FB forming process. This paper addresses
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Three-dimensional terminal angle constraint guidance law with class K∞ function-based adaptive sliding mode control Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-28 Zewei Zheng, Jiazhe Li, Mir Feroskhan
This paper investigates the three-dimensional (3-D) interception guidance problem, where the missile is required to intercept the maneuvering target with the desired terminal angles. For the nonlinear relative kinematic model, a class function-based adaptive sliding mode guidance law is proposed, which ensures that the errors of terminal Line-of-Sight (LOS) angles converge to the small neighborhoods
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Trajectory tracking of a quadrotor via full-state feedback control Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-28 João Madeiras, Carlos Cardeira, Paulo Oliveira
This paper introduces a novel control approach for underactuated aerial vehicles that eschews conventional control paradigms like the inner-outer loop or backstepping techniques. Rather, the proposed control strategy merges the position and attitude control systems cohesively, resulting in a more integrated and efficient control scheme. The proposed control strategy is designed to facilitate an exponential
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The influence of supersonic spatial-temporal coupling disturbance on detonation in an expanded chamber Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-28 Jindian Liu, Wei Xiao, Jian Dai
At present, the most researches on perturbed detonation only considers single factor effects, and there are few studies on the impact of multi-factor coupled perturbations on detonation. In order to match the complex inflow conditions in real situation, the initiation and propagation process of detonation disturbed by spatial-temporal coupling have been studied. This study adopts an adaptive mesh refinement
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Numerical simulation of distributed propulsion systems using CFD Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-28 Geng Qiao, Tao Zhang, George N. Barakos
This paper examines a Distributed Propulsion (DP) concept and involves CFD verification, optimisation and evaluation. The first part of the study validates the employed simulation methods using experimental data from the NASA Workshop for Integrated Propeller Prediction (WIPP) and the Folding Conformal High Lift Propeller (HLP) project, for isolated and installed cases under various conditions. Additionally
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Experimental investigation on the aerodynamic performance of a transonic turbine rotor with non-axisymmetric endwall Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-28 Jie Wang, Yifei Yan, Zhi Tao, Zhendong Guo, Liming Song, Jun Li
To demonstrate the effectiveness of non-axisymmetric endwall (NAE) and elucidate its underlying flow fundamentals, a transonic aerodynamic test platform was designed and constructed for an annular cascade. The loss characteristics and flow field structures were measured for a meticulously-designed NAE model and a baseline axisymmetric endwall at various exit Mach numbers (0.6 to 0.95). The static pressure
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A minimum objective function trim procedure for VTOLs noise reduction Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-27 Caterina Poggi, Giovanni Bernardini, Massimo Gennaretti
The present paper proposes a novel approach for multi-rotor acoustic nuisance mitigation based on the identification of optimal control settings. This strategy is possible thanks to the peculiarity of multi-rotor systems (like, for instance, those involved in urban air mobility applications) to have redundant controls. The idea is to take full advantage of the control redundancy by defining the control
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Analytical investigation of in-plane and out-of-plane elastic properties of bone-inspired cellular structures Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-24 Nguyen Van Thuong, Nguyen Dinh Khoa, Tuan Ngo, Nguyen Dinh Duc
Determining the elastic moduli of materials plays an important role in solving many structural problems, such as vibration and buckling analyses of advanced laminate plates and shells. Bone-inspired cellular structure material (BCS) is a new cellular structure material that has recently attracted the attention of scientists and engineers. However, till now, none of the works in the literature can fully
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Numerical study on the flow characteristics and stability in the isolator of rotating detonation ramjet engine by different combustion modes and structure parameters Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-23 Minghao Zhao, Hua Qiu, Xinlu He, Zhiyuan Feng, Zhan Yang, Xitao Chen
In this paper, numerical simulations are conducted to investigate the effects of the combustion modes and structure parameters of the combustion chamber of a rotating detonation ramjet engine(RDRE) generated within the isolator. The stability of the isolator in the combustion mode as a single or dual wave mode is evaluated. The influence of parameters such as the combustion chamber expansion angle
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Knowledge transfer accelerated turbine blade optimization via an sample-weighted variational autoencoder Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-23 Zhendong Guo, Cunxi Li, Yun Chen, Liming Song, Jun Li, Zhenping Feng
The aerodynamic shape optimization (ASO) of turbine blades is a typical black-box expensive problem. With the ever increasingly strict design requirements, high-fidelity simulations are demanded, and the related simulation cost increases sharply, which means fewer simulation calls are allowed within a design optimization cycle. Then, the problem as “how to achieve better solution with fewer simulations”
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Sound radiation characteristics of a beam under supersonic airflow and non-uniform temperature field Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-23 Huchhanagouda H Patil, Jeyaraj Pitchaimani
This paper investigates vibro-acoustic behaviour of an isotropic beam subjected to in-plane varying temperature field and supersonic flow. For a given elevated temperature and non-uniform temperature (NUFT) field, the aerodynamic pressure (ADP) is varied in fraction of its critical value, and the consequent effect on sound radiation characteristics is investigated. Shear and normal deformable beam
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Experimental investigation on the effects of transverse injection distribution scheme on dual flame dynamics subjected to flow disturbances Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-23 Tengyu Liu, Pengcheng Wang, Jingxuan Li, Lijun Yang, Zhuyin Ren
Combustion instability has become a major problem in low-emission annular gas turbine combustors. It is of practical importance to investigate the effects of transverse nozzle distribution scheme on multi-flame dynamics subjected to external acoustic perturbations. In this study, the responses of heat release rate perturbations from dual propane/air laminar premixed flames to axial acoustic perturbations
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Nonlinear elastic wave dispersions of solar cells strengthened by advanced functionally graded materials via both mathematical modeling and deep neural networks technique Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-22 Lei Chang, Hao Wu, YangLin Hu, Ahmed M. El-Sherbeeny
From claims of roughly 3% efficiency in 2009 to over 25% efficiency now, perovskite solar cells have made amazing developments in recent years. Perovskite solar cells have quickly increased their efficiency, but there are still a number of obstacles to overcome before they can be considered a viable commercial technology. So, improving the stability of the perovskite solar cells and obtaining the mechanical
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Uncertainty quantification of geometric variations in transonic high-pressure turbine with different trailing edge and throat area distribution Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-22 Yongchao Chen, Zhengping Zou, Lichao Yao, Yifan Wang
The transonic high-pressure turbine is a critical component in modern aviation engines which is susceptible to geometric variations throughout its entire lifecycle. However, the specific impact and underlying mechanism of geometric deviations on the performance are not yet fully understood. This article presents a framework for modeling, quantifying, and analyzing geometric variations in typical transonic
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Novel hierarchical bioinspired cellular structures with enhanced energy absorption under uniaxial compression Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-22 Nguyen Dinh Khoa, Rajendra Prasad Bohara, Abdallah Ghazlan, Huu-Tai Thai, Tuan Ngo
Biological thin-walled cellular structures, such as hierarchical structures of bone, exhibit unique internal structures that offer lightweight characteristics and high energy absorption capabilities. The compact bone shell can protect against local damage during high-impact events, while the porous cancellous bone is essential in absorbing energy. This research proposed five novel bioinspired cellular
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Effects of Re on blade load temporal-spatial distribution and correlation with flow stability of transonic compressor under inlet distortion Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-22 Zhiping Li, Xingyu Zhu, Zhaoqi Yan, Tianyu Pan
Compressor blade operating conditions and aerodynamic load change periodically owing to inlet distortion. The effects of low Re are often unavoidable when the inlet distortion is encountered in real compressor operation. Blade load distribution and internal flow field are both affected by variations in Re. In this paper, the effects of Re on the blade load distribution patterns under 60 degrees of
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Investigation on uncertainty quantification of transonic airfoil using compressive sensing greedy reconstruction algorithms Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-22 Hu Handuo, Song Yanping, Yu Jianyang, Liu Yao, Gao Wenxiu, Chen Fu
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Mechanism of single-mode panel flutter in low supersonic flow Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-22 Liu-qing Ye, Kun Ye, Ke Jin, Yi-fan Zhang, Zheng-yin Ye
Supersonic panel flutter can be of two possible types: single-mode flutter and coupled-mode flutter. Compared to coupled-mode flutter, the physical mechanism of single-mode flutter is less studied at present. In order to reveal the inducing mechanism of single-mode flutter, the present paper constructed a reduced-order fluid model by using the system identification and the Auto Regressive with eXogenous
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Effect of aircraft tire wear on water spray and water displacement drag Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-21 Chenhui Ge, Peiqing Liu, Qiulin Qu, Tianxiang Hu, Jin Zhang
During an aircraft taxiing on a water-contaminated runway, the worn tires with shallower grooves will significantly deteriorate the safety of take-off and landing. The hydrodynamics generated by the tire-water-pavement interaction is numerically studied using the coupling method of Smoothed Particle Hydrodynamics and Finite Element Method. By comparing a completely worn tire with a new tire, the effects
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A fast formation obstacle avoidance algorithm for clustered UAVs based on artificial potential field Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-16 Yunping Liu, Cheng Chen, Yan Wang, Tingting Zhang, Yiguang Gong
The aim of this paper is to improve the rapid obstacle avoidance control of UAVs cluster in a complex obstacle environment, primarily utilizing the finite-time consistent formation control algorithm and the improved artificial potential field algorithm to design the fast obstacle avoidance control strategy. Firstly, a finite-time consistent formation control algorithm is adopted to address the problems
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Large eddy simulation of hydrogen/air co-flow jet flame in the strut-based supersonic combustor Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-16 Xin Li, Yu Pan, Chaoyang Liu, Ni He, Junbo Zou
The exploration of efficient combustion organization schemes is crucial as the expansion of scramjet to higher Mach number becomes a cutting-edge trend. This paper evaluates the combination of strut flameholder and co-flow jet injection scheme through Large Eddy Simulation. The study primarily investigates the combustion stabilization and flame blowout characteristics in various internal circular airflow
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Active control of thermally induced vibrations of temperature-dependent FGM circular plate with piezoelectric sensor/actuator layers Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-16 Mehran Javani, Mohammad Reza Eslami, Yaser Kiani
This study investigates the novel application of active control methods in mitigating thermally induced vibrations of functionally graded material (FGM) circular plates subjected to thermal shock. The top surface of the FGM circular plate is exposed to rapid surface heating, resulting in thermally induced vibrations. To counteract these deflections, two piezoelectric layers, one functioning as a sensor
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Design concepts and control algorithm to minimize the control effort for earth-orbit-raising solar sails Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-15 Jungju Bae, Jaeyoung Kang
This paper presents novel design concepts and a robust sliding mode control (RSMC) algorithm for a solar sail optimized for an Earth-orbit-raising demonstration mission. The design of the solar sail is focused on minimizing mission difficulty and control effort during the Earth-orbit-rising mission. To this end, a gravity-stabilized long boom and one-sided black-coating film are introduced in the solar
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Experimental investigation of hypersonic boundary layer instability with wavy wall located downstream of synchronization point Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-02-15 Xuehao Sima, Ziyan Fang, Guoliang Xu, Jie Wu
The wavy wall surface has been reported to be effective in suppressing the growth of second mode instability waves in hypersonic boundary layer, while the allocation of wavy wall relative to the synchronization point requires further study. Upon this work experimental investigation of hypersonic boundary layer instability with wavy wall located downstream of synchronization point based on 7° half-angle