样式: 排序: IF: - GO 导出 标记为已读
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Unified framework for multi-sensor distributed fusion with memory configuration Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-05-06 Lingjiao Fu, Yifang Shi, Dongliang Peng, Ihsan Ullah
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Sensitivity analysis for knowledge discovery in scramjet intake design optimization using deep-learning flowfield prediction Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-05-06 Chihiro Fujio, Hideaki Ogawa
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Path planning of stratospheric airship in dynamic wind field based on deep reinforcement learning Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-05-03 Baojin Zheng, Ming Zhu, Xiao Guo, Jiajun Ou, Jiace Yuan
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Development of a low-cost flutter test bed with an EPS foam model for preliminary wing design Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-05-03 Varakini Sanmugadas, Jitish Miglani, Wei Zhao, Siddhant Desai, Joseph A. Schetz, Rakesh K. Kapania
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A3-DOF frog-inspired quasi-zero stiffness isolator and its vibration control performance Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-05-02 Jingxuan Wang, Guo Yao
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Autonomous assembly of multiple spacecraft by tether-aided rendezvous and docking: From theory to experiment Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-30 Zhengtao Wei, Ti Chen, Hao Wen, Dongping Jin, Haiyan Hu
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Dynamic-mode-decomposition-based gradient prediction for adjoint-based aerodynamic shape optimization Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-30 Wengang Chen, Jiaqing Kou, Wenkai Yang, Shugang Pan
Accurate and efficient gradient computation is the key to aerodynamic shape optimization. In this paper, dynamic mode decomposition (DMD) is employed to analyze the dynamic characteristics of the early pseudo-time marching of adjoint equations and to predict the gradient. Besides the first-order zero-frequency mode, other zero-frequency modes also contribute to the pseudo iterations of the adjoint
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Skin-friction measurements using oil-film interferometry in hypersonic transitional boundary layer flows Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-29 Chuanhong Zhang, Huibin Ni, Zhiwei Shi, Puyuan Wu
Skin-friction measurements in hypersonic transitional boundary layer (HTBL) flows on a flared cone at Mach 6 at zero angle of attack are obtained using oil-film interferometry (OFI). In addition, the amplitude evolution of instability waves is investigated using fast-response pressure sensors and Rayleigh-scattering flow visualization (RSFV). The connection between the skin-friction coefficient and
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Numerical analysis of novel wavy wall based control of turbulent boundary layer separation Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-29 Piotr Kamiński, Paweł Niegodajew, Artur Dróżdż, Vasyl Sokolenko, Artur Tyliszczak, Witold Elsner
In this work, a comprehensive insight into the new passive flow control method, i.e. a two-dimensional streamwise waviness (recently proposed by Dróżdż et al. ) is provided using Large Eddy Simulations. This approach was demonstrated to be effective in postponing turbulent boundary layer separation at high , which is out of reach for other commonly known passive flow control strategies. Although the
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Test and numerical analysis for water entry of elastic cabin from amphibious aircraft Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-28 Bo Cui, Yongjie Zhang, Hao Dong, Tao Jin, Chuzhe Zhang, Qiang Zhu
Water-entry performance of amphibious aircraft is one of the main factors affecting the structural design. However, it is analyzed by rigid models in general, which is difficult to reflect the elastic characteristics of the structure. And it is difficult to obtain sufficient guidance for structural design from rigid-body analysis. In this study, water-entry model of an elastic cabin from amphibious
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Integrated elastic identification and LOS angular rate extraction for slender rockets: A continuous-discrete maximum correntropy Kalman filter approach Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-27 Duo Zhang, Jianmei Song, Yeqing Zhu, Tianfeng Jiao, Liangyu Zhao
Slender rockets experience significant elastic deformation during flight due to aeroelastic forces, impacting their dynamic behavior and posing challenges for traditional line-of-sight (LOS) angular rate estimation methods. This paper addresses this challenge by proposing a novel and highly accurate line-of-sight angular rate extraction model. This model integrates elastic identification with line-of-sight
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Graph-based multi-agent reinforcement learning for large-scale UAVs swarm system control Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-26 Bocheng Zhao, Mingying Huo, Zheng Li, Ze Yu, Naiming Qi
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Large eddy simulation for jet noise characteristics of liquid rocket engine with guide groove Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-26 Ping Jin, Danqi Yang, Yongzhao Yang, Qibo Peng, Guobiao Cai
The study of jet noise characteristics of liquid rocket engines is a prerequisite for evaluating the noise level of rockets and effectively controlling the noise. To obtain the effect of engine operating and structural parameters on jet noise, the Large Eddy Simulation combined with the FW-H integration method is applied for the scaled engine with guide groove under different chamber pressures and
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Numerical investigations of different liner lengths of axial film cooling for a rotating detonation engine Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-26 Haiyin Lv, Jinglei Xu, Rui Li, Junfei Zhou, Kaikai Yu
This study numerically investigates the axial slot film cooling of a stochiometric hydron/air rotating detonation engine. The essential flow characteristics are analyzed, and application prospects are explored. An annular liner is positioned at the inlet of the engine, partitioning the combustion chamber into a cooling passage and a combustion channel. Air is injected through the cooling channel to
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Investigation of aluminum particle ignition dynamics in various propellant environments Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-25 Wenchao Zhang, Zhimin Fan, Yao Shu, Ping Ren, Peijin Liu, Larry K.B. Li, Wen Ao
The ignition delay of aluminum particles can be profoundly influenced by the agglomeration and combustion characteristics of solid propellants. In this experimental study, the ignition of individual aluminum particles in nitrate ester plasticized polyether (NEPE) and hydroxyl‑terminated polybutadiene (HTPB) propellant atmospheres was examined using laser ignition tests and high-speed photography. Focus
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Variational mode decomposition–based nonstationary coherent structure analysis for spatiotemporal data Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-25 Yuya Ohmichi
The conventional modal analysis techniques face difficulties in handling nonstationary phenomena, such as transient, nonperiodic, or intermittent phenomena. This paper presents a variational mode decomposition–based nonstationary coherent structure (VMD-NCS) analysis that enables the extraction and analysis of coherent structures in the case of nonstationary phenomena from high-dimensional spatiotemporal
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Experimental and numerical investigation of transpiration cooling with gradient porosity layout for the thermal protection of nose cone Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-25 Yifei Liu, Taolue Liu, Rui Ding, Fei He, Jianhua Wang
Transpiration cooling with liquid phase change has been widely regarded as one of the most promising thermal protection technology for aerospace vehicles. However, when applied to the nose cone with small curvature radius, cooling failure may occur due to the extreme high heat flux and pressure at the stagnation point. In order to deal with this issue, a wedged-shaped nose cone structures with a gradient
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Decoupled incremental nonlinear dynamic inversion control for aircraft autonomous landing with ground-effect Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-24 Salahudden Salahudden, Henil Agrawal, Aditya Karnam, Anirban Roy
Due to motion coupling and increased model dependence, the use of nonlinear controllers in real-time applications for aircraft is extremely constrained. This explains why proportional, derivative, and integral (PID) controls are frequently used in practice. However, fast changes in the commanded path and the requirement for high accuracy and tracking performance limit use of PID in landing. This paper
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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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Inflatable aerodynamic decelerators for CubeSat reentry and recovery: Surface properties Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-22 Nicolas Caqueo, Rodrigo Cassineli Palharini, Rayana Santos Araujo Palharini, Emanuela Gaglio, Raffaele Savino
In this investigation, Direct Simulation Monte Carlo Method is used to compute the surface properties of inflatable aerodynamic decelerators (IAD) applied for the reentry, recovery, and reuse of cubeSats. Surface properties calculation is of fundamental importance for flexible thermal protection system materials selection that withstand the harsh reentry environment. Furthermore, simulations are extremely
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Influence of structural elasticity on the aerodynamic characteristics of the common research model with deflected control surfaces Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-21 Christopher Reinbold, Konstantin Bantscheff, Kaare Sørensen, Christian Breitsamter
Numerical aerodynamic and aeroelastic investigations are conducted for the Common Research Model (CRM) configuration with deployable aileron control surfaces and a trimmable horizontal stabilizer at cruise and off-cruise conditions. The numerical methodology which is implemented in the multi-disciplinary simulation environment SimServer is based on CFD and coupled CFD-CSM simulations. The DLR Tau Code
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Numerical investigation of aerodynamic interactions for the coaxial rotor system in low-speed forward flight Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-21 Xin Yuan, Wei Bian, Qijun Zhao, Guoqing Zhao
This study is conducted to investigate the aerodynamic characteristics of a coaxial rotor in low-speed forward flight using a high-fidelity computational fluid dynamics (CFD) solver. Numerical simulations are performed on the coaxial rotor and its isolated upper and lower rotors at two small advance ratios, 0.12 and 0.24. Interaction events in the flowfield, especially blade-vortex-interaction (BVI)
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Flight analysis and optimization design of vectored thrust eVTOL based on cooperative flight/propulsion control Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-21 Ming Liu, Zhezhe Su, Jianfeng Zhu, Feng Guo, Yancheng You
The rise of electric vertical take-off and landing (eVTOL) aircraft has sparked research interest, but attention to modeling and evaluation methods, particularly for vectored thrust eVTOL, lags behind. The intricate flight/propulsion coupling and structure/control complexity contribute to the gap. Moreover, integrated modeling and evaluation processes for vectored thrust eVTOL should fully account
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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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Effects of structural geometric nonlinearities on the transonic aeroelastic characteristics of wing Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-20 Kun Ye, Mengbing Yang, Liuzhen Qin, Rongrong Xue, Zhengyin Ye
The structural geometric nonlinearity has a great influence on the transonic aeroelastic characteristics of aircraft wings, which is an important problem for the aerodynamic and structural design of wing. In this paper, a CFD/CSD coupling method based on the high precision in-house solver is first established, and the reliability of the CFD and the CFD/CSD coupling method is then verified. Subsequently
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High-dimensional aerodynamic shape optimization framework using geometric domain decomposition and data-driven support strategy for wing design Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-19 Xiaojing Wu, Long Ma, Zijun Zuo
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Control of a dual-mode scramjet flow path utilizing optical emission spectroscopy Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-18 Max Y. Chern, Andrew J. Wanchek, Laurie Elkowitz, Robert D. Rockwell, Chloe E. Dedic, Christopher P. Goyne
Shock train leading edge (STLE) location control within a Dual-Mode Scramjet (DMSJ) flow path was demonstrated using an optical emission spectroscopy (OES) sensor for control feedback. Emission from electronically excited chemical species, OH and C, was observed within the combustor and used for feedback to control the STLE within the DMSJ isolator. An optical emission sensor was used to experimentally
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Reentry trajectory planning for hypersonic vehicles via an improved sequential convex programming method Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-18 Yunhao Luo, Jianying Wang, Jie Jiang, Haizhao Liang
The reentry trajectory planning problem of hypersonic vehicles is generally a continuous and nonconvex optimization problem. The solution efficiency and convergence properties of the planning algorithm become an essential point when considering the practical application scenarios. In this paper, an augmented-Lagrange-based improved sequential convex programming algorithm is proposed to solve it and
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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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Optimal attitude control for landing on asteroid with a flexible lander Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-16 Pingyuan Cui, Chengyu Zhang, Zixuan Liang
The recently developed flexible lander offers a potential option for future asteroid landing missions due to its advantages in suppression of rebound and overturning. The strong nonlinear dynamics and control constraints of the flexible lander hinder the online implementation of optimal attitude feedback control. To generate the optimal attitude control rapidly, a constrained inhomogeneous approximating
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Study on the method of transfer alignment based on the distributed inertial network of guided submunition Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-16 Hui Kang, Chunlan Jiang, Ming Li, Liang Mao
Aiming at the problem of poor transfer alignment accuracy between missiles with a high length-to-diameter ratio as a carrier missile and the internally carried guided submunition, this study proposes a transfer alignment method based on the distributed inertial network of the guided submunition. Initially, considering the influence of the deflection deformation of the carrier missile body and the dynamic
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Numerical investigation on the use of various blade tips for the helicopter's main rotor blade in forward flight regarding aerodynamic performance and HSI noise considerations Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-16 Reza Afshari, S.M.H. Karimian
The goal of this research is to investigate aerodynamic performance and high-speed impulsive (HSI) noise of various blade tips for the helicopter's main rotor in forward flight. For this purpose, three-dimensional compressible flow field around the rotor blades is numerically simulated by the solution of the unsteady Reynolds averaged Navier-Stokes (URANS) equations with the "SST k-ω" turbulence model
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A novel impact angle control guidance law design via predefined time convergence theory Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-16 Zhongtao Cheng, Cong Zhu, ChengJun Shan, Chao Ou, Yaosong Long
A predefined time guidance law with impact angle control is proposed for intercepting the stationary target. With such a guidance law, the convergence time of the impact angle error for the missile is independent of the initial conditions, and it can be selected at the will of the designer. First, a heading error shaping method based on the Lyapunov asymptotic stability theory will be introduced, which
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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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Experimental study on multi-angle pulsed jet actuators for controlling corner separation flow in a compressor cascade Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-14 Huawei Lu, Chengze Wang, Xiaozhi Kong, Shiqi Wang, Jianchi Xin, Shuang Guo
Three-dimensional corner separation caused by the aerodynamic design of high-load compressor cascades is the main factor that limits their performance enhancement. Because of the unsteady characteristics of large-scale flow separation, injecting unsteady jets into the flow field has become a new flow control method. In this study, the essential flow characteristics of a compressor cascade were obtained
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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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An efficient sparse surrogate model for aerodynamic characteristics of a supersonic compressor cascade with uncertain geometric deformations Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-09 Zhengtao Guo, Wuli Chu, Haoguang Zhang, Kaiye Liu
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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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Transient plasma enhanced combustion of solid rocket propellants Aerosp. Sci. Technol. (IF 5.6) Pub Date : 2024-04-04 Caleb Medchill, Armando A. Perezselsky, Andrew Cortopassi, Alejandro L Briseno, Chris Brophy, Stephen B. Cronin
We demonstrate the use of nanosecond pulse transient plasma (NPTP) to improve the control (and acceleration) of the combustion of solid rocket propellants. Here, we fabricate end-burning propellant samples (i.e., grains) with a co-axial center wire electrode using hydroxyl terminated polybutadiene (HTPB), isodecyl pelargonate (IDP), modified diphenyl diisocyanate (MDI), and ammonium perchlorate (AP)
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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