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Refined mode classification and performance analysis method of dual-mode scramjet vehicles for flight trajectory optimization Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-07-06 Jiwon Son, Hyosang Ko, Han-Lim Choi, Kwanjung Yee
Hypersonic air-breathing vehicles, utilizing ramjet and scramjet propulsion systems, are emerging as a promising option for future hypersonic transportation due to high specific impulse. The performance of hypersonic aircraft is significantly influenced by their flight trajectory, as combustion efficiency and aerodynamic forces vary markedly with altitude. Although numerous studies have focused on
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Strength analysis method of CMCs tip shroud structure considering random distribution of preform properties Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-07-04 Yue Zhou, Sheng Zhang, Huajun Zhang, Chengqian Dong, Xiguang Gao, Yingdong Song, Fang Wang
This paper considers the impact of the random distribution of yarn properties on the mechanical and failure behavior of ceramic matrix composites (CMCs) structures and proposes an integrated analysis method based on preform-structure. Tensile tests of CMCs tip shroud specimens were carried out, and the digital image correlation technique was used to record the deformation of the specimens in real-time
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Improved non-contact vibration measurement via acceleration-based blade tip timing Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-07-04 Yuda Zhu, Baijie Qiao, Yanan Wang, Zhibo Yang, Meiru Liu, Xuefeng Chen
The conventional displacement-blade tip timing (D-BTT) measurements often rely on Once-Per-Revolution (OPR) sensors to compute expected or theoretical time of arrival (TOA) based on rotational speed. However, integrating OPR sensors within the confined space of aero-engines presents challenges, and estimating theoretical TOA introduces computational errors, particularly for low-amplitude, high-frequency
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Station-keeping HAPS mission through optimal sprint and drift trajectories Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-07-03 Adrián Delgado, Diego Domínguez, Jesús Gonzalo, Alberto Escapa
Due to the latest technological breakthroughs, High-Altitude Pseudo Satellites (HAPS) have recently become a feasible solution with great potential in the aerospace industry for Earth observation and communications, among other applications. Minimizing the energy consumption of these solar powered platforms is critical and, in the case of lighter than air vehicles, leads to smaller and more manageable
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Utilizing global-local neural networks for the analysis of non-linear aerodynamics Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-07-02 Abhijith Moni, Weigang Yao, Hossein Malekmohamadi
In addressing the computational challenges pervasive in engineering where time and cost limitations are key concerns, particularly within the Computational Fluid Dynamics (CFD) domain, Reduced Order Models (ROMs) have emerged as instrumental tools. Focused on reducing computational complexity without intrusively modifying the computational model, this study centres on the strategic application of aerodynamic
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Imaging diagnostics and PIV measurements of flame propagation and flow structure during ignition process in a three-sector RQL combustor Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-07-01 Chaowei Tang, Jianzhong Li, Jianhan Feng, Qian Yao, Li Yuan, Wu Jin
The ignition of kerosene spray in an aero-engine combustor is complex due to the fuel injection, mixing, and swirl flow. To explore the influence of ignition position on the ignition characteristics of the aero-engine combustor, a three-sector rich-quench-lean (RQL) combustor experiment system was designed. The experimental study on the ignition process of different ignition positions was carried out
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Coupled nonlinear vibration characteristics of quasi-zero-stiffness Gough-Stewart isolation platform Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-07-01 Ke Sun, Jie Tang, Zhijing Wu, Yinghui Li, Dengqing Cao
The quasi-zero-stiffness (QZS) Gough-Stewart vibration isolation platform is designed for six degrees-of-freedom (DOFs) low-frequency vibration isolation. Lots of studies regarding the amplitude-frequency relationship of the platform are based on the assumption that interference with the platform in one direction only provokes a response in that direction. This assumption artificially decouples a six
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High-speed perforation of IN718 plates by spherical TC4 Ti alloy projectiles: Experiments and modeling Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-07-01 J.Y. Hua, Q. Liu, Z.Y. Liu, C.H. Mi, Y.D. Chen, J.C. Cheng, J. Wu, L. Lu, Y. Cai, S.N. Luo
Data and knowledge on ballistic performance of Inconel-718 (IN718) alloy is critical for evaluating the resistance of turbine blades against foreign object impacts in aeronautical and astronautical industries. Ballistic perforation experiments (impact velocity 480 ms to 1340 ms) with TC4 spherical projectiles (5-mm-diameter) are conducted on IN718 target plates (2-mm-thick) in this work, along with
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An experimental parametric study assessing the effect of a certain initial geometric imperfection on cylinder buckling Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-07-01 C. Cervi, L.N. Virgin
Given the sensitivity of axially-loaded cylinder buckling to geometric imperfections, the advent of additive manufacturing provides a compelling platform to assess subtle changes in initial configuration from an experimental perspective. The cylindrical form is ubiquitous in many load-bearing contexts, from soda cans to submarines to rocket fuel tanks. Despite the relative simplicity of the shape,
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Numerical study of hydrogen ratio effect on detonation initiation characteristics of aviation kerosene with hydrogen addition Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-29 Zhiwu Wang, Yuxiang Hui, Yang Zhang, Jingtao Xiao, Weifeng Qin, Yuxuan Yang
Detonation initiation is one of the most important problems in the research of pulse detonation engine (PDE). It is difficult for aviation kerosene to meet the performance requirement of short-distance detonation initiation in PDE. Hydrogen can improve the detonability of fuels. Aviation kerosene with hydrogen addition provides a new method to shorten the detonation initiation distance in PDE. Therefore
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Noise control for nose landing gear by longitudinal wavy strut Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-29 Binnian Chen, Jia Yan, Xiaoquan Yang, Jue Ding, Peifen Weng
The noise of landing gears is a major contributor to the overall airframe noise of an aircraft during approach and landing. In this paper, a novel strut treatment method, termed the Longitudinal Wavy Strut (LWS), is proposed to improve the aeroacoustics performances of nose landing gear. The simplified and complete landing gear model with wavy strut are respectively investigated by a hybrid approach
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Comprehensive crashworthiness simulation analysis of a large aircraft fuselage barrel section in various crash scenarios Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-29 Haolei Mou, Zilong Wang, Jiang Xie, Zhenyu Feng, Fei Gao
To utilize computational techniques in investigate and evaluate the crashworthiness of typical fuselage section of a large transport aircraft in various crash scenarios, the finite element model of fuselage section was modeled and validated based on the vertical drop test of fuselage section at 6.02 m/s. The crash simulation analysis in various crash scenarios (such as concrete ground, soft soil grounds
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Vibration characteristics of dual-rotor system with staggered-type double elastic ring squeeze film dampers under maneuvering flight Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-28 Yuwei Zhang, Siji Wang, Kai Zhao, Lei Xu, Fengyu Yang, Quankun Li
The vibration of the rotor system is significantly intensified during maneuvering flight, rendering traditional elastic ring squeeze film dampers (ERSFDs) insufficient or unstable. To improve the applicability of dampers, a novel structure of staggered-type double elastic ring squeeze film dampers (SDERSFD) is proposed in this paper. Through the synergistic effect of double elastic rings, the damping
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Improved sequential convex programming based on pseudospectral discretization for entry trajectory optimization Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-28 Shoudong Ma, Yuxin Yang, Zheyu Tong, Hua Yang, Changju Wu, Weifang Chen
Sequential convex programming (SCP) is widely used to solve entry trajectory optimization problems. However, challenges persist in scenarios with strict constraints, such as unsolvable convex subproblems, iterative solution oscillations, and slow convergence rates. This study introduces an enhanced SCP algorithm designed to address these limitations. First, Radau pseudospectral discretization is used
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Flow stability analysis on low-speed compressor with swept rotor blades under radial inlet distortions Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-28 Dakun Sun, Hengyi Zhu, Dengke Xu, Haoyu Ni, Xiaofeng Sun
Flow stability enhancement for axial flow compressors under radially distorted inlet conditions through rotor sweep design is an important issue for designers. To investigate the couped effect of rotor swept and radial inlet distortion on flow stability, steady numerical simulations, theoretical model predictions, and experimental validations were conducted for a low-speed, single-stage axial compressor
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Surrogate-based shape optimization and sensitivity analysis on the aerodynamic performance of HCW configuration Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-27 Xi Xiaozhe, Li Guangli, Zhang Kaikai, Xiao Yao, Chang Siyuan, Cui Kai
With an additional wing upon the fuselage, the novel high-pressure capturing wing (HCW) configuration exhibits remarkable aerodynamic characteristics at hypersonic speeds under beneficial aerodynamic interference. This bi-wing structure can also enhance the lift at subsonic speeds, positioning HCW configuration as an excellent aerodynamic layout under wide-speed range conditions. In this paper, a single-wing
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Multi-level and multi-objective structural optimization for hypersonic vehicle design Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-27 Miguel Rodríguez-Segade, Santiago Hernández, Jacobo Díaz
This research introduces a novel methodology for optimizing the structural design of a full-scale hypersonic aircraft, integrating a multifaceted approach across different levels of modelling detail to enhance a variety of performance metrics. The proposed approach is capable of reduce the vehicle mass, while meeting the necessary operational requirements and maintaining an acceptable computational
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Experimental investigation of wing-propeller aerodynamic interaction in eVTOL configurations Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-27 Alex Zanotti, Luca Menini, Alberto Savino, Donato Grassi, Luca Riccobene
The present study is aimed at the experimental investigation of the effects of wing-propeller aerodynamic interaction in a boom-mounted configuration typically used in eVTOL aircraft. The investigation was focused on the repercussions on wing and propeller performance coming from the variation of angle of attack, advance ratio and blades sense of rotation. Moreover, particular attention was devoted
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Numerical analysis of aeroacoustic characteristics for coaxial counter rotating propellers considering the self-interference effect Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-26 Hang Xu, Weiqi Wang, Xi Chen, Qijun Zhao
Based on the FW-H equation and the CFD method, the coaxial counter rotating propellers aeroacoustic characteristics in hover are calculated and analyzed. First, a set of analysis method for aperiodic coaxial propellers aeroacoustic characteristics is developed. The aerodynamic and aeroacoustic characteristics of the Harrington coaxial rotor 1 (HC1) in hover and the AH-1G rotor in forward flight are
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A deep neural network reduced order model for unsteady aerodynamics of pitching airfoils Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-26 Giacomo Baldan, Alberto Guardone
A machine learning framework is developed to compute the aerodynamic forces and moment coefficients for a pitching NACA0012 airfoil incurring in light and deep dynamic stall. Four deep neural network frameworks of increasing complexity are investigated: two multilayer perceptrons and two convolutional neural networks. The convolutional framework, in addition to the standard mean squared error loss
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On the determination of the standing oblique detonation wave in an engine combustor using laser absorption spectroscopy of hydroxyl radical Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-25 Wenshuo Zhang, Zijian Zhang, Xin Han, Chaokai Yuan, Yunfeng Liu, Liuhao Ma, Wei Ren
Freejet experiments were conducted in the hypersonic flight-duplicated shock tunnel (JF-12) to understand the detonation combustion mode in the combustor of a standing oblique detonation ramjet (Sodramjet) engine prototype. Besides the traditional schlieren imaging to capture the oblique shock positions in the combustor, we implemented laser absorption spectroscopy of hydroxyl (OH) radical with three
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Thermo-chemical nonequilibrium effects on combustion characteristics of a transverse jet in the scramjet Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-25 Jincheng Zhang, Zhenguo Wang, Chaoyang Liu, Mingbo Sun, Hongbo Wang, Junding Ai, Zihao Zhang
As the Mach number increases, the local static temperature gradually approaches the characteristic gas vibration/dissociation temperature, and significant thermo-chemical relaxation processes occur. The thermo-chemical nonequilibrium phenomenona could affect the mixing and combustion process and become a factor that must be considered for scramjet design. In this paper, a large eddy simulation solver
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Aeroacoustics computation for propellers based on harmonic balance solution Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-25 Luca Abergo, Luigi Vigevano, Alberto Guardone
In this paper, a novel open-source framework is presented for the evaluation of noise emissions produced by aerodynamic bodies exhibiting dominant motion at specific frequencies. This behavior is frequently encountered in propellers used for urban air mobility applications. The reduced order model called harmonic balance is employed to compute the unsteady flow solution, reducing the computational
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Nonlinear bending and buckling analysis of 3D-printed meta-sandwich curved beam with auxetic honeycomb core Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-25 Mohammad Reza Nasri, Erfan Salari, Arshia Salari, Seyed Ali Sadough Vanini
The present study investigates the static responses of a 3D-printed polymeric meta-sandwich curved beam with an auxetic honeycomb core, including buckling and nonlinear bending behavior. After extracting the mechanical properties of the core material, the nonlinear governing equations for the curved beam under two types of loading, namely uniform transverse and axial mechanical loads, are derived based
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Micro-flow properties of NEPE propellant in a rotating depressurization combustion environment of solid rocket motor Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-24 Kaixuan Chen, Xiaochun Xue, Zhenwei Ye, Yonggang Yu
A profound understanding of microflow processes within the combustion chamber is paramount for optimizing engine performance and ensuring safe operation in the realm of solid rocket propulsion. Specifically, the scrutiny of Nitrate Ester Plasticized Polyether (NEPE) propellant under rotating depressurization combustion conditions has garnered substantial scholarly interest. The non-uniform distribution
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Function observer based on model compensation control for a fixed-wing UAV Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-23 Lin Xu, Guoyuan Qi
Fixed-wing unmanned aerial vehicle (UAV) is a nonlinear system characterized by strong coupling, high complexity, and sensitivity to external interference and model uncertainty. For the fixed-wing UAV having eight degrees of freedom, the uncertainty and wind disturbance parts of the model are clarified, and a model with lump disturbance is established through the mechanic analysis. To get the high
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Vibration localization and reduction of double-plate structures Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-22 Jian Xue, Hong-Wei Ma, Li-Qun Chen
A thin plate-type resonator is attached to a host-stepped plate to achieve vibration localization and reduction in initial low-order global vibration modes. A semi-analytical method is proposed to analyze the free and forced vibrations of the double-plate structure, considering the geometric configuration's heterogeneity and discontinuity. The double plate structure is divided into several sub-plates
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Neural network observer-based predefined-time attitude control for morphing hypersonic vehicles Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-22 Xinyue Lu, Jianying Wang, Yonghai Wang, Jun Chen
Considering the fast-time varying external disturbance and model uncertainties caused by large-scale morphing and cross-domain flights, this study proposes a novel predefined-time sliding mode control method for the attitude control of morphing vehicles during the large-scale morphing phase. Firstly, a predefined-time neural network disturbance observer is established for approximating system error
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A hybrid optimization method based on extreme learning machine aided factor graph for INS/GPS information fusion during GPS outages Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-22 Xiaokai Wei, Ping Lang, Jie Li, Kaiqiang Feng, Ying Zhan
To enhance the navigation capability of the microelectromechanical system (MEMS)-based inertial navigation system (INS)/global positioning system (GPS) integrated system under satellite denied, a hybrid optimization navigation method using minimal learning parameter (MLP) to improve extreme learning machine (ELM) aided adaptive factor graph (AFG) is proposed. The proposed method mainly contains two
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Interaction between lateral jet and hypersonic rarefied flow Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-22 Guang Zhao, Chengwen Zhong, Sha Liu, Jianfeng Chen, Congshan Zhuo
Reaction control systems (RCS) are commonly utilized in a variety of air vehicles, and they give rise to complex flow phenomena. For flows dominated by shock waves and expansion, such as lateral jets, a significant gradient is formed in the local region of the flow field, resulting in a high local Knudsen number, and the continuum hypothesis is no longer applicable, even if the freestream belongs to
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Event-triggered fixed-time fault-tolerant attitude control for the flying-wing UAV using a Nussbaum-type function Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-21 Wenda Yang, Xiangxi Wen, Li Mo, Maolong Lv, Zhilong Yu, Minggong Wu
This paper introduces an innovative adaptive event-triggered fault-tolerant attitude control framework designed for a flying-wing unmanned aerial vehicle (UAV) operating under constraints such as limited embedded resources, unknown actuator failures, system uncertainties, and external disturbances. The proposed scheme incorporates several noteworthy features: (i) Implementation of a relative threshold
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Adaptive sliding mode attitude control of two-wheeled robots for planetary auxiliary: From theory to applications Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-21 Shuangxi Liu, Zehuai Lin, Wei Huang, Binbin Yan
The value of two-wheeled robots in planetary auxiliary is significant, but their attitude control presents challenges due to their inherent characteristics and external environment conditions. To address this issue, this paper presents an adaptive sliding mode (SMC) control scheme of two-wheeled robots for planetary auxiliary. Firstly, a motion model specifically for two-wheeled robots that focuses
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An integrated cable-driven parallel robot for space station servicing: Self-calibration and pose estimation Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-20 Dongxing Li, Zhengqing Li, Guotong Li, Xiaoqiang Tang
This paper presents an integrated cable-driven parallel robot designed for space station servicing. All components, including winches, sensors, controllers, and others, are integrated within its envelope, greatly simplifying the installation process of the robot. However, practical application of this integrated robot necessitates a rapid self-calibration method that relies solely on internal sensors
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Aeroelastic effects in PIO occurrences: A dual approach on flight simulator tests Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-20 André L.A. Paladini, Daniel Drewiacki, Jorge H. Bidinotto
This article presents the PIO identification for a conceptual aircraft subjected to aeroelastic effects. The flight data was obtained in an extensive flight simulator campaign, using the DLR AVES full-motion simulator, performed by four test pilots, as part of Embraer's/DLR's DinAFlex project. The aircraft model inserted in the simulator considered three cases, varying in structural flexibility and
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Fuel consumption and trailing-edge noise tradeoff studies via mission-based airfoil shape optimization Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-20 Yuan Lyu, Arjit Seth, Rhea P. Liem
Aerodynamic drag is often used as a proxy for fuel consumption in aircraft design. However, the aeroacoustic byproduct of airfoil design, such as trailing-edge noise (TEN), is yet to be considered in aircraft applications, despite its inclusion in wind turbine designs. To explore the impact of TEN in airfoil design for aircraft, we establish a mission-based aerodynamic shape optimization framework
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Event-triggered finite-time fuzzy tracking control for a time-varying state constrained quadrotor system based on disturbance observer Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-20 Changhui Wang, Nan Yang, Wencheng Li, Mei Liang
In contrast with most existing results concerning quadrotor unmanned aerial vehicle (UAV) wherein time-triggered controllers or only symmetric state constraints are considered, this paper deals with the event-triggered finite-time trajectory tracking control problem for quadrotor UAV with asymmetric time-varying state constraints and unknown external disturbances. Firstly, the fuzzy logic system is
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Incremental fully actuated system approach-based prescribed-time fault-tolerant formation control of helicopters under multiple faults Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-20 Qiyang Miao, Ke Zhang, Bin Jiang
Helicopter formation is characterized by intricate dynamics, complex mechanics, and challenging scenarios, raising the necessity for agile, robust, and convenient controller design. This paper explores the prescribed-time fault-tolerant formation control of multiple helicopters through the incremental fully actuated system approach, which addresses multiple faults in sensors and swash plate struts
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Feasible model-order reduction approach for analysis of composite rotor blades based on geometrically exact beam formulation Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-19 Inho Jeong, Haeseong Cho, Seung-Hoon Kang, Haedong Kim
This paper presents a novel and practical reduced-order model (ROM) approach designed specifically for analyzing composite rotor blades, leveraging the geometrically exact beam formulation. The slender nature of rotor blades necessitates aero-structure coupled analysis to precisely predict their response, which involved numerous iterative computations. By capturing large displacements and rotations
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A generative adversarial network for enhancing over-expansion flow field perception of nozzles with large expansion ratio Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-19 Yunfei Li, Wanlin Guo
Over-expansion flow and separation phenomena exist inside the nozzle during the startup and shutdown of the rocket engine, and the transition between the separation modes is prone to cause significant side loads and jeopardize the safety of the engine. Accurate, comprehensive and prompt nozzle flow field state perception is of great significance to the stable operation of the engine. Here, a generative
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Aeroelastic fluid dynamics assessment of performance and vibration on active twisting rotors Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-19 Rinaldo Steininger, George N. Barakos
The effects of passive, and higher-harmonic rotor blade twist on helicopter main rotors are investigated. High-fidelity CFD is used for calculations due to the demanding flow conditions considered, including high blade loading, and high-speed cases. A strong structural coupling scheme is employed for enhanced performance and vibration predictions. Quantitative predictions are made for the effects of
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Design and characterization of a pyroshock reduction structure based on local resonance mechanisms Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-19 Yuxi Wang, Xiao Kang, Lina Feng, Ying Li
In the spacecraft Pyrotechnic shock process, the explosion generated by the strong shock wave and preload force release of the vehicle structure produces a transient, high-frequency, and high-amplitude shock response, resulting in a harsh shock environment prone to failure or damage to many precision equipment or components on the spacecraft, a fatal impact on the launch mission. This paper designed
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Explosion behaviors of aviation kerosene in a 20-L spherical vessel Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-18 Cheng Wang, Shixiang Song, Boyang Qiao, Xiaoli Li
Aviation kerosene is the main fuel in aerospace industry. In order to investigate the explosion behaviors of aviation kerosene, the explosion experiments were conducted using the 20-L liquid explosion testing system. The influence factors, including mist concentration , ignition delay time , liquid injection pressure , and ignition energy were discussed, and the explosion mechanism of aviation kerosene
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Helicopter rotor in a propeller slipstream: Aerodynamic and rotor blade flapping responses Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-18 Berend G. van der Wall
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Aeroelastic analysis using confocal sensors: experimental study and numerical validation with application to a future particle detector Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-18 Aitor Amatriain, Massimo Angeletti, Corrado Gargiulo, Gonzalo Rubio
This study investigates the structural displacements induced by aerodynamic loads in a future particle detector at the Large Hadron Collider (LHC): the Inner Tracking System 3 (ITS3) of the ALICE experiment. The development of an ultralight structure and use of air cooling lead to an unprecedentedly low material budget, resulting in improved accuracy compared to the current detector (ITS2). The airflow
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Longitudinal dynamic envelope solution and transition path optimization based on reachability analysis for fixed-wing VTOL UAVs Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-18 Keran Cong, Dongli Ma, Liang Zhang, Xinglu Xia, Yucan Cheng, Hao Guan
Flight velocity and tilt angle are commonly employed to define the safe region for fixed-wing vertical take-off and landing (FW-VTOL) UAVs as they undergo tilting, referred to as the transition corridor. Nevertheless, the transition corridor only considers the aircraft's limitations in a quasi-stationary condition and ignores the additional constraints introduced by the aircraft's kinematic behavior
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UAV autonomous source seeking with cumulative exposure minimization in complex hazardous environments Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-17 Menghua Zhang, Honglun Wang, Hongxia Ji, Jianfa Wu, Yiheng Liu, Yu Huang
Considering autonomous searching for an unknown source in complex hazardous environments while balancing search efficiency and flight safety, this paper proposes a framework called source seeking with cumulative exposure minimization (SSCEM) for an unmanned aerial vehicle (UAV) equipped with gas sensors. First, the hazardous substance dispersion is formulated by using an isotropic plume model, and
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An experimental study on the combustion characteristics of the cavity-stabilized supersonic premixed flame Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-17 Suyi Dou, Jiaqi Yu, Qingchun Yang, Xu Xu
With the overwhelming trend of fast and economic aviation, it is becoming increasingly difficult for fuel to burn stably and efficiently in a constrained space and time period in the combustor of a hypersonic air-breathing vehicle. Conventional supersonic diffusion flame runs the risk of blowing out in the incoming flow at such high velocity. Upstream fuel injection of the flame holder is gaining popularity
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Numerical study on the internal/external flow and thrust-drag characteristics of oblique detonation engine-based aircraft Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-15 Wenhui Ling, Chengxiang Ren, Lin Zhou, Yining Zhang
The oblique detonation engine (ODE)-based aircraft employs the fast oblique detonation wave (ODW) combustion for airbreathing propulsion, delivering significant technical advantages in structure and efficiency under hypersonic flight conditions. However, achieving overall optimization by harmoniously integrating the ODE internal flows with the aircraft external flows remains a crucial yet unexplored
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Influence of a novel leading-edge winglet on the aerodynamic characteristics of a highly loaded turbine Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-15 Yue Li, Weipeng Xue, Lei Luo, Han Yan, Wei Du, Qiao Luo, Shaoyun Yang
In order to decrease the flow loss of the region close to the endwall, a novel leading-edge modification strategy is proposed in this paper. Specifically, the winglet is installed at the leading edge of the first-stage blade of the highly loaded PW-E (Energy Efficient Engine designed by Pratt & Whitney Aircraft Group) turbine. The numerical methods used in this study are validated with the experimental
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Transient experimental study on cooling performance of a radial turbine with impingement cooling in rotating state Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-15 Chao Ma, Han Zhang, Jianjian Zhang, Xiaoli Wang
Increasing the inflow temperature of a turbine is an effective approach for enhancing the thermal efficiency of devices operating in the Brayton cycle, such as micro-gas-turbines and waste heat recovery systems. However, elevated temperatures also pose a significant risk of thermal fatigue failure. This paper presents an experimental investigation of impingement cooling for radial turbines, aiming
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Distributed adaptive disturbance observer-based multi-channel event-triggered finite-time coordinated control for multi-UAVs with actuator failures Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-15 Lihao Wang, Aijun Li, Chao Xiao, Changqing Wang, Yuriy Zabolotnov
A finite-time coordination controller based on an adaptive disturbance observer and a multi-channel event-triggered strategy is proposed for the multi-UAVs control problem with actuator faults, external disturbances, and communication constraints. First, an adaptive finite-time disturbance observer based on a hyperbolic tangent function is established to compensate for actuator faults and external
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Experimental and numerical investigation on turbine flow control through integrating endwall contouring with section profiling at different Mach numbers Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-15 Zhengshuai Du, Le Cai, Jun Zeng, Yingjie Chen, Xun Zhou, Songtao Wang
The efficiency of turbomachinery is notably impacted by losses occurring within the turbine cascade, which are intricately linked to the configuration and intensity of secondary flows. Non-axisymmetric endwall contouring, as well as three-dimensional blade designs, are effective methodologies for regulating secondary flows within the cascade passage. These passive control strategies are garnering increased
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Control on SWBLI by vortex generator in a supersonic cascade Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-14 Zhongyi Wang, Tianchu Song, Xiaohu Chen, Meng Wang
In order to control the SWBLI separation in supersonic cascade and widen its working range, VG array is set on the suction surface and numerically explored. VG can redistribute the passage flow to suppress the separation near the blade wall. Through the analysis on the effects of typical geometry parameters, the chord position of VG trailing edge should be set at the middle position between the blade
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Nonlocal strain gradient-based geometrically nonlinear vibration analysis of double curved shallow nanoshell containing functionally graded layers Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-14 Pham Hong Cong, Nguyen Van Huong, Truong Tich Thien, Nguyen Dinh Duc
It is a fact that while examining the mechanical behavior of nano/microscopic materials, size effects become apparent. This study aims at presenting a new approach to geometrically nonlinear vibration analysis of double curved shallow nanoshell on Kerr foundation containing functionally graded layers under the impacts of harmonic loading in the framework of nonlocal strain gradient theory and the classical
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Improvements for the DDES model with consideration of grid aspect ratio and coherent vortex structures Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-13 Jian Liu, Jianqiang Chen, Zhixiang Xiao
The delayed detached eddy simulation (DDES) model has achieved great success in simulations of massive separations, but has been found to significantly delay the Kelvin-Helmholtz (K-H) instability in weak separations due to the “grey area” problem. A new DDES model was proposed by considering the grid aspect ratio and local coherent vortex structures, named the DDES with an adaptive grid-scale and
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Programmable thick-panel Miura-ori for ultra-large planar antennas with one-degree-of-freedom Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-13 Xiaozhao Zhang, Wujun Chen
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6-DOF UAV Path planning and tracking control for obstacle avoidance: a deep learning-based integrated approach Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-13 Yanxiang Wang, Honglun Wang, Yiheng Liu, Jianfa Wu, Yuebin Lun
Path planning is crucial for achieving autonomous and safe flight of fixed-wing unmanned aerial vehicles (UAVs). The existing methods generally cannot simultaneously balance real-time performance, near optimality, and feasibility in three-dimensional obstacle environments. To this end, this paper proposes a deep learning-based integrated path planning and tracking control framework for obstacle avoidance
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Conceptual design methodology and performance evaluation of turbine-based combined cycle inward-turning inlet with twin-design points Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-12 Zhancang Hu, Zhonglong Li, Yiqi Tang, Yaokun Yu, Yuchao Zhang, Xiaogang Zheng, Chengxiang Zhu, Yancheng You
Turbine-based combined cycle (TBCC) engines attract intensive attention due to adequate high working efficiency within the full speed range of air-breathing vehicles. Challenges of TBCC engines lie mostly in common-used components in particular the inlet system, which needs to satisfy the mass flow distribution of different sub-engines and to reconcile the performance requirement in the full speed
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Adaptive track approach for multiple sources scenarios during radar survey for space surveillance applications Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-12 M.F. Montaruli, P. Di Lizia, S. Tebaldini, G. Bianchi
The increasing population of resident space objects is currently fostering many space surveillance initiatives, which rely on the use of on-ground sensors. In particular, survey radars allow to first characterise the target orbit from a single transit, through measurements which are Doppler shift, slant range and angular profile. In this framework, the Music Approach for Track Estimate and Refinement
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High-fidelity simulation of the interaction between a blade cascade and an ingested vortex Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2024-06-12 Dimitri Magand, Sébastien Deck, Nicolas Renard, Alain Dugeai, Béatrice Bois, Tony Spriet
The aim of this research is to analyze the flow generated by the interaction between a simplified linear blade cascade adapted from an industrial aircraft engine demonstrator and an ingested vortex with the aerodynamic characteristics of a ground vortex observed in experiments. Due to the lack of availability of experimental and high-fidelity numerical studies of this phenomenon in the literature,