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Predefined-time robust attitude tracking control of flexible spacecraft with continuous and nonsingular performance Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-30 Yan Xiao, Yunteng Wang, Dong Ye, Zhaowei Sun
To address the predefined-time robust attitude tracking control of flexible spacecraft with both external disturbances and model uncertainties, this paper proposes an adaptive terminal sliding mode controller. A modal observer is designed to estimate the unmeasured modal information of flexible attachments, and the estimation error is regarded as a part of the lumped disturbance. The term with a power
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A unified deep learning model for thermoacoustic instability detection in swirl premixed flames based on spatial-temporal features Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-30 Xuejiao Li, Chunyu Liu, Dezhi Zhou, Liang Yu, Xingcai Lu
This paper proposes a thermoacoustic Instability (TAI) detection method based on a convolutional neural network (CNN) with long short-term memory (LSTM) and attention mechanisms. First, considering the limitations of TAI control techniques, we experimentally categorize the thermoacoustic modes into five regimes: low frequency with low amplitude, low frequency with high amplitude, high frequency with
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Model predictive control of a flared folding wingtip for gust load alleviation Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-30 Mohammad Narimani, Hassan Haddadpour, Seid H. Pourtakdoust
Although a reduction in lift-induced drag by having larger wing spans potentially improves aircraft performance and fuel consumption, it could bring about structural and maneuverability challenges. Folding Wing-Tip (FWT) devices offer a solution by enabling higher aspect ratios during cruise while being folded to meet the size constraints on the ground or other flight conditions. This study investigates
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Robust optimal powered descent guidance via model predictive convex programming Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-29 Yizheng Xiao, Youmin Gong, Jie Mei, Guangfu Ma, Weiren Wu
This paper investigates the robust fuel-optimal guidance problem for powered descent landing under uncertainty. A robust optimal control problem (OCP) with stochastic dynamics and constraints is first constructed to ensure both optimality and safety. The polynomial chaos expansion (PCE)-based uncertainty quantification technique is then employed to convert the stochastic OCP into a high-dimensional
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Robust trajectory design and guidance for far-range rendezvous using reinforcement learning with safety and observability considerations Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-29 Minduli Charithma Wijayatunga, Roberto Armellin, Harry Holt
Observability, safety, and robustness are critical for successful rendezvous and proximity operation (RPO) missions. The use of angles-only navigation (AON) for these missions is often seen as limited due to its inability to determine range, though it remains appealing for its low cost. This work utilizes the proximal policy optimization algorithm in reinforcement learning for the guidance of the far-range
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Smoothing-homotopy-based sequential convex programming for trajectory optimization Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-29 Mengxin Zhao, Binfeng Pan, Xiyu Hou, Longxin Huang
This paper proposes a new smoothing-homotopy-based sequential convex programming (SCP) method for general trajectory optimization problems. The surrogates, derived from convolving the smoothing kernel with the terminal states, are firstly incorporated into the terminal constraints as replacements of the original ones. The smoothing parameter, taken as the homotopic parameter, decreases from a larger
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Flow field prediction and optimization of non-axisymmetric aero-engine nacelles based on deep learning Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-28 Guocheng Tao, Yang Liu, Jiahuan Cui
Nacelle designs are evolving toward compact configurations to tackle the aerodynamic challenges of higher bypass ratios. Traditional methods require extensive computational fluid dynamics simulations, leading to high computational and time costs. Integrating machine learning in the preliminary design stage effectively reduces costs while maintaining accuracy. This study develops a deep neural network
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Design, analysis, and test of morphing wing driven by multi-layer parallel MFC bimorphs with adjustable axial pressure Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-27 Kaiming Hu, Donghai Ruan, Hua Li, Hongzhou Song, Tianhong Yan
To further improve the deformation ability of morphing wing driven by MFC pre-compressed bimorph actuators (MFC-PBAs) to achieve the actuation capability of the existing micro electric servoactuator, and make its deformation ability controllable, a scheme of a chordwise variable camber wing driven by the three-layer compact parallel and axial pressure controllable MFC-PBAs is presented in this paper
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Flow3DNet: A deep learning framework for efficient simulation of three-dimensional wing flow fields Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-27 Kuijun Zuo, Zhengyin Ye, Xianxu Yuan, Weiwei Zhang
Artificial intelligence is considered an effective means to accelerate the simulation of wing flow fields. However, rapid simulation of three-dimensional wing flow fields remains a challenging task. In particular, with the gradual accumulation of datasets, current deep learning models struggle to achieve adaptability to flow fields of arbitrary resolutions, both in the training and prediction phases
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Experimental study on the detonation propagation behavior in a thin cylindrical chamber Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-27 Chenyang Wang, Bo Zhang
For the propagation of the cylindrical detonation, which evolves from planar detonation within a pre-detonator, previous experimental research predominantly has employed continuous recording methods such as smoke foils and open-shutter photography. However, these techniques pose challenges in directly observing the instantaneous flame propagation state within the chamber. To address this, the current
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Propulsion system integration on truss-braced aircraft: structural performance sensitivity to architectural design parameters Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-27 Damian Quinn, Stephen Colbert, Declan C. Nolan, Rob Fox, Jill Gaskell
Strut-, or Truss-Braced Wing configurations, compatible with traditional or more novel propulsion technology, have been proposed to meet future sustainable aviation goals. However, an understanding of how propulsion system performance and/or design is impacted by such novel architectural changes is required to develop an optimal integrated propulsion system solution. With a focus on the structural
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Ablation behavior of carbon-carbon composite nozzles produced by different carbon fibers in a small solid rocket motor Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-27 Sha Li, Bin Zhang, Siyi Meng, Jinlv Zuo, Bo Yang, Meigui Qi
PAN-based carbon fibers produced by dry-jet wet-spun method and wet-spun method were used to produce carbon-carbon composite nozzles C-1 and C-2, the ablation properties were tested by a small solid rocket motor, then ablation morphologies were observed by scanning electron microscope (SEM), and ablation behaviors were studied. The results show that dry-jet wet-spun fibers have higher tensile strength
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An investigation on UAV vibration control based on negative Poisson's ratio metastructures Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-27 Weibo Li, Sidong Zhang, Zhenbo Lu
Vibration control is critical to the unmanned aerial vehicle (UAV) flight system and directly affects the stability and safety of the airframe during flight. The vibration reduction of the UAV arm can effectively isolate the vibration effects between the power source and core components. Based on this, this paper proposes two types of three-dimensional mechanical metastructures with negative Poisson's
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Optimizing energy capacity, and vibration control performance of multi-layer smart silicon solar cells using mathematical simulation and deep neural networks Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-27 Mengxia Wang, Junda He, Liwei Zheng, Tamim Alkhalifah, Riadh Marzouki
This study focuses on optimizing the energy capacity and vibration control performance of a multi-layer silicon solar cell reinforced with graphene oxide powder (GOP) and equipped with sensor and actuator layers. Mechanical properties such as Young's modulus, Poisson's ratio, and density are determined using the Halpin-Tsai method and the law of mixing, ensuring accurate modeling of material behavior
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A fish evasion behavior-based vector field histogram method for obstacle avoidance of multi-UAVs Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-27 Minghao Li, Zhanjun Huang, Wenhao Bi, Tianle Hou, Pan Yang, An Zhang
Focusing on the obstacle avoidance problem of multiple unmanned aerial vehicles (multi-UAVs) in three-dimensional dynamic environment, a fish evasion behavior-based vector field histogram (FEB-VFH) method is proposed in this paper. First, an obstacle avoidance decision function inspired by fish evasion behavior is designed, which considers the size and movement of the obstacle. Second, the threat of
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Adaptive attitude control of rigid-elastic coupling launch vehicle based on rate gyro weighting Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-25 Xingyu Jiang, Peng Shi, Shengping Gong
In this paper, the problem of adaptive attitude control is studied for a rigid-elastic coupling launch vehicle based on rate gyro weighting. Firstly, an attitude tracking error dynamics model is established, which contains multiple rate gyros that are arranged at different positions of the rocket body. Subsequently, a rate gyro adaptive weighting method is proposed to reduce the elastic vibration signals
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Effect of dome spacing on flow field and flame dynamics in a three-sector rich-quench-lean combustor Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-24 Qian Yao, Erlong Li, Chaowei Tang, Wu Jin, Jianhan Feng, Jianzhong Li, Li Yuan
To optimize the performance of rich-quench-lean (RQL) combustors, a numerical and experimental investigation into the impact of dome spacing was conducted using a three-sector model combustor with adjustable dome spacing. The study specifically focused the flow field, flame dynamics, and outlet temperature distribution under various dome spacings. The results shown that dome spacing has a great influence
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Dual-channel event-triggered practical predefined-time formation controller for multi space transport robot system Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-24 Ran Tao, Yibo Ding, Hanyu Li, Ziyu Yang, Xiaokui Yue
This paper proposes a dual-channel event-triggered practical predefined-time formation controller (PPFC) for multi space transport robot system (MSRS) by combining sliding mode control theory with dual-channel event-triggering mechanism (ETM). Firstly, a novel practical predefined-time stability criterion is proposed in the form of composite Lyapunov function, which can simplify the determination of
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Integrated guidance and control for underactuated space manipulator whole-body transfer operations Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-23 Mingchao Wang, Lijun Zong, Jianping Yuan
This paper proposes an integrated guidance and control method for an underactuated dual-arm space manipulator to transfer to the target position near the Space Station (SS) and subsequently unfold its robotic arms for operations. Considering the dynamic coupling between the position and attitude of the underactuated base spacecraft, the integrated method comprises two layers: a model predictive controller
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Optimal design of regenerative cooling channels for a ram/scramjet dual-mode aircraft using conjugate heat transfer analysis Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-23 Jae Seung Kim, Song Hyun Seo, Minsul Lee, Hyoungjin Kim, Kyu Hong Kim
This study presents an optimal design of a regenerative cooling system for a ram/scramjet dual-mode aircraft, similar to the design of an X-51A Waverider, using conjugate heat transfer (CHT) analysis. The analysis accounted for the aerodynamic heating, thermal structures, and cooling systems. A sensitivity analysis was conducted on the physical parameters (fuel flow rate and fuel inlet velocity) and
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Research on intelligent orbit life prediction model of low Earth orbit vehicle Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-23 Yu-Ming Guan, Zhi-Hui Li, Xing-Long Gao
Spacecraft in low Earth orbit are significantly affected by atmospheric effects. Previous orbit prediction models only considered atmospheric drag, assuming that it was the only significant factor causing orbital decay. This article supplements the effects of aerodynamic lift and lateral force on the orbit. To address the inaccuracy encountered by the Simplified Perturbation Model (SGP4) during orbit
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Hierarchical pigeon inspired optimization based Multi-UAV obstacle avoidance control Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-23 Hao Wu, Haibin Duan
UAV formation collision avoidance control plays an important role in UAV (unmanned aerial vehicle) flight missions, and is a crucial technology in complex environments such as mountainous areas. Aiming at the collision avoidance control problem of UAV formation, a UAV formation control protocol is designed, which includes formation direction control component, flocking speed consistent control component
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Investigation on H2/O2 rocket rotating detonation engine with annular and hollow combustors Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-22 Hongfei Xu, Fang Wang, Chunsheng Weng
In this paper, a three-dimensional numerical investigation is conducted to reveal the propagation characteristics and operation performance of the H2/O2 rocket rotating detonation engine (RDE) with annular and hollow combustors. A detailed chemical mechanism is adopted and a complex slit-hole non-premixed injection configuration is simulated. The effects of engine configurations and sizes on flow field
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Distributed average consensus attitude synchronization of multi rigid spacecrafts with predefined time event-triggered sliding mode control Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-22 Jie Wang, Ming Yang, Dinghua Wang, Ting Wang
In this paper, a predefined time event-triggered sliding mode attitude synchronization strategy is proposed for the distributed multi-spacecrafts system, where the communication topology is directed. Firstly, the design of the controller is simplified by introducing an auxiliary average attitude. Secondly, based on the predefined time non-singularity terminal sliding mode protocol and event-triggered
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Optimization of supersonic combustor configuration based on Gaussian process regression and genetic algorithm Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-22 Hao Zhang, Jiahang Li, Mi Yan, Yuanyang Miao
The present study employs a genetic algorithm to conduct an optimization research on the geometric configuration of the combustor of a supersonic combustor with forward fuel injection at the bottom of the cavity, based on a surrogate model established using numerical simulation and Gaussian process regression. A numerical simulation model for supersonic flow combustion is established, which includes
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Assessing prominent eVTOLs based on vertiport throughput, noise, and speed using multi-dimensional pareto fronts Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-21 Lukas Preis, Mark T. Kotwicz Herniczek, Brian J. German
Advanced air mobility with eVTOL aircraft is an emerging mode of transportation within cities. The novelty of this new mode is a desired combination of high volume, acceptable noise and fast travel. eVTOL aircraft design requires significant tradeoffs, and different aircraft configurations will excel in different specific AAM missions and market segments. This article examines the tradeoffs between
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An amphibious propeller design optimization framework based on deep neural network surrogate model Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-21 Zihan Dang, Mingyu Wu, Xianjun He, Zhengui Huang, Zhanfeng Ying, Zhihua Chen, Chun Zheng
The propeller of hybrid aquatic-aerial vehicles (HAAVs) adopting a water-air integrated drive system is required to achieve high thrust and efficiency in both mediums. However, current HAAVs directly employ aerial propellers, which exhibit low aquatic efficiency. Therefore, a surrogate-based propeller design optimization framework for designing amphibious propellers is proposed in this work for engineering
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High-efficiency unscented Kalman filter for multi-target trajectory estimation Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-21 Changtao Wang, Honghua Dai, Wenchuan Yang, Xiaokui Yue
High-efficiency trajectory estimation for massive resident space objects plays an important role in space situational awareness to protect space assets. The unscented Kalman filter (UKF) has been widely utilized in trajectory estimation for decades due to its high level of accuracy. However, its efficiency suffers from the time-consuming propagation of Sigma points in the unscented transformation for
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Research on multi-hierarchical multi-objective optimization design of scramjet nozzle under geometric constraints Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-20 Shuhong Tong, Maotao Yang, Ye Tian, Yue Ma, Jialing Le, Heng Wang
The traditional nozzle design method needs more time and economic cost, and it is difficult to obtain good performance under strong geometric constraints. In contrast, the nozzle optimization design process assisted by artificial intelligence technology is shorter in time, but requires a large dataset. In this paper, the multi-layered optimization framework design method is innovatively proposed to
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The effects of adverse pressure gradient and streamline curvature on oblique-wave transition and turbulence Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-20 Ying Wang, Qing Shen, Teng Zhou, Chao Yan
Direct numerical simulations have been performed to study the evolution of oblique waves in flat plate boundary layers and concave wall boundary layers under adverse pressure gradient and zero pressure gradient conditions, at a freestream Mach number of M∞=3. The investigation aims to understand the effects of adverse pressure gradient and streamline curvature on the development of oblique waves and
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Feedback from gas-phase chemical reactions to surface reactions in high-temperature hypersonic airflow coupled with carbon ablation Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-20 Leibao Han, Yufeng Han, Wei Cao
This work numerically investigates the feedback mechanisms from the gas-phase chemical reactions to the surface reactions using a multi-component thermochemical nonequilibrium flow solver. The in-house solver is based on the finite-difference method and utilizes the AUSMPW+ and central difference schemes to discretize the convective and viscous fluxes, respectively. Research shows that ablation products
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Particle image velocimetry measurement of supersonic turbulent boundary layers mixed with seeping gas film Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-18 Q. Mi, S.H. Yi, D.D. Gang, Y.X. Zhao, S.K. Chen
Porous-wall seeping gas film is an effective method to realize drag reduction and heat reduction for high-speed vehicles. However, quantitative research on the mixing flow structure between seeping gas film and boundary layer is lacking. By improving the seeding method of tracer particles within the boundary layer, the Near-wall Particle Image Velocimetry (PIV) technique was achieved to measure the
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Flow simulation of propeller-airframe interaction using a modified blade camber surface loading model Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-18 Hyeonwook Lim, Kwanjung Yee, Hyoungjin Kim
In the present study, the blade camber surface loading (BCSL) model, which is a kind of the body force method was modified and extended for efficient propeller simulations in CFD. The BCSL model was originally proposed for turbomachinery fan analysis. To apply the BCSL model to propeller simulations, modifications were made by incorporating tip loss and zero-lift angle to the model. The modified BCSL
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Design and aerodynamic analysis of a morphing joined-wing aircraft with transonic flight capability Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-17 Xiangying Guo, Zhen Wang, Kuan Lu, Dongxing Cao
A broad-speed-range operational capability coupled with both subsonic and supersonic flight performances is a key factor for new aircraft design. The joined-wing configuration has higher bending torsional strength, lower induced resistance, larger lift coefficient, and better stability in comparison to traditional wing configuration. A new morphing joined-wing aircraft that featured a retractable wing
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The inverse design and three-dimensional analysis of double design points basic flow field based on wide range capture ability Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-17 Zejun Cai, Waner Hu, Zhancang Hu, Chongguang Shi, Xiaogang Zheng, Chengxiang Zhu, Yancheng You
The hypersonic inward-turning inlet plays an essential role in ensuring optimal inflow to the engine throughout a broad range of speeds. However, traditional single design point methodologies frequently overlook performance variations across different velocity regimes. To address this oversight, a Double Design Point (DDP) basic flowfield and its inverse design methodology are proposed. This DDP method
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A novel ROM-based FSI model of composite blisk with blades-disk coupling for flutter analysis Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-17 Qian Xu, Lei Hou, Lixian Hou, Zhonggang Li, Shuangxing Ren, Faisal Z. Duraihem, Emad Mahrous Awwad, Nasser A. Saeed
With the trend of blisk becoming lightweight, compact, and material-composite, fluid-structure interaction (FSI) in blisk flutter analysis becomes increasingly unignorable. Direct numerical simulation of FSI consumes a large amount of computing resources, and there has been very little research on the mechanism of influence of blades-disk coupling on the flutter characteristics of blisk. This paper
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Reentry glide vehicle trajectory prediction method via multidimensional intention fusion Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-17 Jiong Li, Yangchao He, Lei Shao, Xianhai Feng
To address the problems of difficulty in identifying the attack intention of reentry glide vehicle under the influence of no-fly zones and low accuracy of long-term trajectory prediction, a reentry glide vehicle trajectory prediction method via multidimensional intention fusion is proposed. Firstly, a time-varying parameter model set is constructed by estimating and predicting the aerodynamic parameters
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Preliminary trajectory design of implementing the asteroid rendezvous and impact in a single launch Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-17 Nan Zhang, Di Wu, Zhong Zhang, Haiyang Li, Hexi Baoyin
This paper presents the preliminary design of single-launch rendezvous and impact trajectories targeting asteroid 2015 XF261, one of the potential candidates for China's first Near-Earth Asteroid Defense Mission. The mission is planning to involve launching an observer for long-term escort operations and an impactor for high-velocity collision with the target asteroid using one rocket. First, based
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High-efficiency reduced space sequential convex programming using low-complexity matrix inversion Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-17 Yangyang Ma, Binfeng Pan, Longxin Huang, Qi Chen, Zihui Xu
In response to the increasing demand for real-time optimization in aerospace systems, reduced space sequential convex programming (rSCP) has been developed to improve the computational efficiency of conventional sequential convex programming by explicitly eliminating state variables and state equations from the optimization formulation. However, as the number of discretization nodes increases, this
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Efficient reduced order modeling for nonlinear dynamic analysis of beamlike truss structures Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-15 Tengfei Yuan, Wei Fan, Hui Ren, Yipeng Liu
Dynamic analysis of large flexible truss structures is a challenging task due to their complexity and huge computational cost. In this paper, a low-dimensional, high-accuracy model of the beamlike truss with geometric nonlinearity is developed using the reduced order modeling technique. The obtained reduced model only involves the low-frequency transverse modes, but the contribution of the high-frequency
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Autonomous helicopter shipboard recovery flight control design based on tau theory Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-15 Qingyu Kang, Honglei Ji, Ye Yuan, Yi Ye
This paper develops an autonomous flight control system to alleviate the heavy workload involved in managing multiple emergencies during manned helicopter shipboard recovery operations. It can operate either partially or fully autonomously preserving the pilot's familiar guidance strategies while allowing pilot intervention when necessary. First, a simulation model of helicopter recovery flight is
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Physics-based and data-driven prediction method for features and type boundaries of oblique detonation wave systems in hydrogen-air mixtures Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-15 Junhan Ma, Zhiyuan Lyu, Bin Zhang
Predicting the wave systems in the initiation region of oblique detonation wave (ODW) is critical to the development of oblique detonation engine. Despite the extensive studies on ODW initiation characteristics, this remains a challenging task. In this study, a physics-based and data-driven prediction method is proposed to predict the features and type boundaries of oblique detonation wave systems
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The ignition and self-sustaining combustion of the rotating detonation fueled by solid propellant Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-14 Bo Zhang, Yixiao Song, Quan Wen, Yuanyang Miao, Meng Huang, Zhiyi Wang, Xiaotao Tian, Bing Wang, Haocheng Wen, Yingchen Shi, Kegang Cai
In this study, self-sustained rotating detonation combustion is successfully achieved using solid propellant as fuel. A stable single wave rotating detonation is observed in the experiment, lasting for over 6 s, with a detonation propagation velocity of 1675 m/s. A comparison between the high-energy spark and the solid propellant ignitor demonstrates that the high-pressure hot jet generated by the
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Fault tolerant control of vibration isolation platform based on fuzzy active disturbance rejection controller Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-14 Chao Ma, Wei Li, Qing Li, Lei Liu
The vibration isolation platform, operating in the harsh space environment, faces the potential risk of actuator failure. Consequently, fault-tolerant capability becomes paramount for the platform to successfully accomplish on-orbit tasks. Considering the nonlinear characteristics of the vibration isolation platform in large angle motion, multiple degrees of freedom (multi-DOF) coupling nonlinear dynamic
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Numerical investigation of effects of blade-tip and number of blades in a cyclorotor system using large-eddy simulation Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-13 Manabu Saito, Ryoichi Kurose
The complexity of the geometry and generated flow field of a cyclorotor poses significant challenges for a detailed experimental flow field analysis, conducted to understand the phenomena involved in generating thrust. In this study, large-eddy simulations (LES) are conducted to investigate the effect of interactions between the blades and the blade-tip vortex on the aerodynamic performance of a cyclorotor
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Investigation of aeroelastic instability in a transonic compressor with low engine order distortion Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-11 Huayin Chen, Kailong Xia, Hefang Deng, Mingmin Zhu, Jinfang Teng
Aeroelastic instability has been a critical challenge in the design of modern compressors for decades. It arises from the interaction between aerodynamic forces and the structural dynamics of the blades, potentially leading to harmful vibrations and reduced performance. The compressor blades may experience unsteady aerodynamic forces arising from various disturbances in low engine order (LEO) patterns
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An efficient thermal optimization model with integrated force paths, fully-decomposed hierarchies and hybrid genetic operations for a flight wing Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-11 Jian-Jun Gou, Hao-Dong Niu, Shu-Zhen Jia, Jia-Xin Hu, Xiao-Wei Wang, Chun-Lin Gong
Lightweighting of the thermal system is the key issue for high-speed vehicles, and the integrated optimization of heat-force transfer path is one of the most promising techniques. However, the inconsistent transfer paths and multi-hierarchy variables lead to a complex and time-consuming optimization problem. In this work, the integrated path with I-type force path and rectangular heat transport path
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Design and aerodynamic analysis of the morphing waverider with rotating telescopic wing for wide-speed-range flight Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-11 Nanxuan Qiao, Tielin Ma, Biao Jing, Jingcheng Fu, Ligang Zhang
Wide-speed-range vehicles represent a burgeoning research area in aerospace, challenged by the conflicting aerodynamic demands of different flight regimes. This study proposes a novel "waverider with rotating telescopic wing" configuration for clustered launch deployments, capable of morphing to meet both hypersonic and subsonic flight requirements. The research focuses on two key aspects: firstly
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Determination of the dynamic temperature field of a disturbed laminar conical premixed flame based on the background-oriented schlieren technique Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-11 Yue Zhang, Xuanye Liang, Yu Tian, Zixuan Wang, Lijun Yang, Jingxuan Li, Wei Hu
In this paper, the Background-Oriented Schlieren (BOS) technique is used to measure the temperature field of a laminar conical premixed propane-air flame. Thermocouples and OH* chemiluminiscence are used to verify the measurement accuracy of BOS. The results indicate that BOS demonstrates higher measurement accuracy under low equivalence ratio conditions with good flame symmetry, and it effectively
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Research on 3D layered visibility graph route network model and multi-objective path planning for UAVs in complex urban environments Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-10 Xiao-Bing Hu, Chang-Shu Yang, Jun Zhou, Ying-Fei Zhang, Yi-Ming Ma
Over the past decade, unmanned aerial vehicles (UAVs) have seen increased use in urban transportation, including applications such as package delivery and emergency rescue. However, the complex nature of urban environments poses significant challenges to the safe and efficient operation of UAVs. Path planning offers an effective solution for improving both flight efficiency and safety. This paper develops
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A cost-efficient method to determine the dynamic stability of a missile/rocket configuration with grid fins Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-10 K. Salehi Paniagua, P. García-Fogeda Núñez, F. Arévalo Lozano
In this work a useful tool for analyzing the static and dynamic stability of missiles and rockets equipped with grid fins is presented. The proposed method, applicable to subsonic flows, is based on the use of the Doublet-Lattice Method combined with the “Unit Grid Fin” concept. This approach demonstrates high computational efficiency compared to other CFD-based numerical procedures. Comparisons with
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Optimal planning and tracking for E-sail transition between steady-states Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-10 Guillermo Pacheco-Ramos, Rafael Vazquez, Daniel Garcia-Vallejo
The E-sail technology employs the repulsive force of solar wind protons on positively charged tethers for continuous propulsion. Mission research highlights the necessity to modulate thrust, while dynamics studies reveal a tendency for oscillation. This study explores achieving stable transitions between different E-sail steady-states, each associated to varying voltages and thrust levels. By creating
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Analytical pursuit-evasion game strategy in arbitrary Keplerian reference orbits Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-10 Shuyue Fu, Shengping Gong, Peng Shi
This paper develops an analytical strategy for solving the linear quadratic pursuit-evasion game in arbitrary Keplerian reference orbits. The motion of the pursuer and evader is described using the controlled Tschauner-Hempel equations, and the feedback saddle-point solution of the LQ pursuit-evasion game is presented by the solution of the differential Riccati equation. The analytical solution of
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Exact interception probability-based assignment for multiple pursuers against multiple evaders Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-10 Hong Tao, Tao Song, Hongyan Li, Defu Lin, Ruonan Zhai
This paper aims to address the assignment issue associated with multiple aerial pursuers against multiple evaders by proposing a guidance performance-based algorithm. An evaluation function for assignment is first established based on the interception probability of evaders, which is exactly derived by reconstructing augmented ideal proportional navigation (AIPN) guidance law as a time-varying close
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Low-communication collaborative navigation with state estimation for large-scale agent systems meeting minimum performance requirements Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-10 Songtan Yang, Xingqun Zhan, Hanyu Wang
Consensus-based event-triggered distributed schemes effectively address the communication congestion and excessive power consumption of traditional time-driven collaborative navigation schemes. However, existing methods rely on fixed fusion topologies, leading to performance redundancy under dynamic navigation requirements. In contrast, we consider the “minimum performance requirement” for each task
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Weight-adaptive parameter estimation assisted event-triggered model predictive guidance for reentry Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-10 Tengfei Zhang, Licong Zhang, Chunlin Gong, Songyu Liu, Hua Su
This paper proposes an event-triggered model predictive guidance (ET-NM PG) method assisted by weight-adaptive parameter estimation (WAPE) and applies it to reentry guidance. Guidance methods based on online trajectory optimization (TO) often face a trade-off between guidance accuracy and the efficiency of guidance command computation when dealing with complex problems. By using state deviation exceeding
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Multiple UAVs cooperatively circumnavigating a group of non-cooperative targets in a GPS-free environment via a range-only distributed controller Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-10 Shan Huang, Jingping Shi, Qi Zhu, Zhihui Du, Yongxi Lyu, Zhunga Liu
This article proposes a distributed controller for multiple unmanned aerial vehicles (UAVs) cooperatively circumnavigating a group of non-cooperative targets only using range measurements. Unlike most existing methods that either only consider a single target or know the global locations of the UAV and target beforehand, this article investigates a more general situation to circumnavigate multiple
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Second-order cone programming based covariance control and applications in terminal flight guidance Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-09 Peng Zhang, Wenbo Li, Junfeng Li, Shengping Gong
Terminal flight guidance problems are full of uncertainties. The deterministic trajectory optimization methods typically disregard uncertainties, which renders achieving precise target arrival impractical. Conventional covariance control approaches add directly uncertain terms to the right hand of the dynamic equations. The uncertainties' meaning is unclear. In addition, current approaches convert
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On the use of Mahalanobis distance in particle image velocimetry post-processing Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-09 Colin M. Stutz, John T. Hrynuk
Particle Image Velocimetry (PIV) is a method of flow measurement that has become increasingly popular as an experimental tool. New technology has made high-speed and higher-dimension (stereoscopic, tomographic, etc) methods available to an ever-growing population of researchers. These advanced methods can provide significantly more data than traditional low-speed planar PIV, but these larger data sets
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Acoustic characteristics improve of doubly curved aerospace systems considering an optimum control strategy Aerosp. Sci. Technol. (IF 5.0) Pub Date : 2025-01-08 Nader Moustafa, Roohollah Talebitooti, Kamran Daneshjou, Mehrdad Motavasselolhagh
This study aims to improve sound transmission loss of a simply supported doubly curved shell that duplicates many aircraft structure parts. This is performed using piezoelectric controller to counteract the effect of an incident acoustic disturbance wave. The shell is modeled using first order shear deformation theory considering piezoelectric constitutive equations and Hamilton's principle. Then,