bluuebunny/crossref_metadata_2025_split huggingface dataset:
Modelling and simulation of double-pantograph catenary system of Taiwan railway
Authors: Chuang Y J , Chen L K 
Published: November 2024

Abstract
In view of the insufficient transportation capacity of Taiwan Railways in populated urban areas and intercity railways, increasing the maximum operating speed can be a solution for the problem. However, it is unknown whether the overhead contact line (OCL) system of the Taiwan Railways can tolerate such speed changes. For the unique railway system used in Taiwan, the literature does not present research on the dynamic interaction behaviour for the typical EMU trains with two pantographs, which are widely used in Taiwan railway system. Further, in response to the government policy to localize the supply chain of railway components, this research aims to establish a reliable simulation model so that domestic manufacturers may use this model for the design and development of the pantograph-catenary system. In this study, the catenary system model is established based on theoretic principles, specifications and parameters are adapted from data used by Taiwan Railway Co. The pantograph model was constructed as multi-body model, with parameters taken from the pantograph equipped on the TEMU2000 tilting train. This model is used to analyse catenary system to investigate the potential loss of contact between the double pantographs and the contact wire with increased train speed. The loss of contact and other phenomena will be analysed to explore possible solutions or optimization strategies for catenary system design.
Development and application of software for designing axial fans in high-temperature environments
Authors: Zhang Shengli , Zeng Zhichun , Zhu Qianhui , Zhang Xinli , Wang Zhao , He Long , Ge Jian 
Published: November 2024

Abstract
This paper presents the development of software specifically designed for designing axial fans operating in high-temperature environments. The software’s accuracy and reliability are validated under extreme conditions. Key features of the software include adjustments for air physical properties, calculations for blade aerodynamic performance, and geometric dimension design. Through various design examples and experimental validation, the results indicate that the airflow error of the software under high-temperature conditions is 9.1%, while the total pressure error is 4.8%, demonstrating its high accuracy and reliability. Additionally, this paper proposes improvements to models of air physical properties, blade surface roughness, multi-condition simulations, and optimization algorithms to further enhance the software’s performance and applicability. The findings suggest that this design software holds significant application value in the field of high-temperature fan design.
Modeling and analysis of creep at elevated temperature analysis on thin-walled profile structures
Authors: Liu Jiexuan , Liu Yutong , Liu Xiao , Hui Yanchuan 
Published: November 2024

Abstract
High-strength steel plays a crucial role in aerospace because of its excellent performance. The high temperatures experienced during a spacecraft’s re-entry to Earth may result in creep in the steel, potentially leading to structural failure, so the finite element software is utilized in this paper to establish a calculation model and analyze the impact of temperature and fire duration on the creep strain of high-strength I-section steel beams under elevated temperatures. Among them, the high-temperature parameter significantly affects the creep strain variation of the mid-span element of the high-strength I-section steel beam. When the temperature parameter is increased by 100%, the maximum creep strain variation of the mid-span component of the beam will increase by about 24%. Under the exact increase, the maximum creep strain variation of the high-temperature duration parameter will only increase by about 3.78%; thus, when conducting a high-strength steel structure, fire resistance analysis should mainly consider the influence of temperature on its creep at elevated temperature strain.
Geometric nonlinear analysis of smart composite laminates
Authors: Zhu Hongyun 
Published: November 2024

Abstract
In order to create an adaptable system, active piezoelectric layers are fused or inserted into a host structure to create smart composite laminates (SCLs). SCL’s prospective applications in form modification, self-health sensing, and active vibration control demonstrate how important it is. In this paper, the static deformation characteristics and dynamic properties of SCL under voltage and mechanical loads are investigated. A completely coupled field program for SCL is constructed using Matlab. It describes mechanical displacements based on the shear deformation assumption and compares two displacement-strain models: linear and von K´arman nonlinear. The coupled nonlinear electromechanical equations are reduced to a finite element form that can be solved with convenience. Based on the program written, we have done a comparative study of linear and geometric nonlinearities of the SCL plate and also compared it with the existing articles. The results of the geometric nonlinear model of the SCL plate are quite different compared to linear and the nonlinear model results are more accurate.
Research on modeling method of providing oxygen functional architecture based on model
Authors: Yang Hao , Huang Renyu , Chen Dongsheng 
Published: November 2024

Abstract
The provision of oxygen is an important function of commercial aircraft, which is defined as providing the necessary oxygen for the safety of everyone on board, including crew oxygen, passenger oxygen, and portable oxygen. This article adopts SysML modelling language and proposes a model-based architecture modelling method for providing oxygen function for commercial aircraft. It transforms traditional experience and document-based system engineering work into functional architecture system engineering work, and utilises the correlation and traceability relationships of models to achieve state machine modelling for providing oxygen functional architecture. Through simulation verification, the functional architecture modelling method that provides oxygen can be effectively applied to the architecture of other systems.
Research on the ultra-high acceleration method based on dual-mass shock amplifier
Authors: Ren Zhiqiang , Li Xinming , Shen Zhiqiang , Yan Tingfei , Zhu Jianbin , Jin Zijian 
Published: November 2024

Abstract
Spacecraft are exposed to rigorous mechanical conditions throughout the launch, explosive decoupling, and landing stages. Electronic devices intended for space deployment are required to endure shock-induced reliability assessments. This study delves into the composition and operational principles of a high-g shock testing system. Furthermore, the paper derives a collision kinematics model from established classical collision dynamics and constructs analytical frameworks for both a single-degree-of-freedom and a two-degree-of-freedom spring-mass systems. Additionally, it investigates the principles of acceleration amplification. The finite element analysis model was computed, and its simulation outcomes were compared and contrasted with the data from shock experiments. The findings indicate that the finite element model is capable of accurately capturing the peak acceleration for both the drop table and DMSA table, with a discrepancy of no more than 5%. The acceleration of the amplifier is enhanced by approximately 40 times following the momentum exchange during the second collision. Moreover, the shock system, equipped with a dual mass shock amplifier (DMSA), is capable of producing accelerations exceeding 30,000G.
Fuselage panel structural-acoustic optimization design of civil aircraft based on numerical analysis
Authors: Zhou Hangwei 
Published: November 2024

Abstract
During the design process of civil aircraft, it is necessary to achieve a high level of cabin noise control to improve cabin comfort. In addition to controlling the intensity of the main noise sources that affect the acoustic environment in the cabin, the acoustic optimization design of the fuselage wall panel structure is also required. In this paper, acoustic analysis software ACTRAN is applied to study the acoustic characteristics of typical structures of civil aircraft cabins. Boundary conditions, material density, and material damping are analyzed from the following main aspects: fuselage panels, thickness, density, reinforced frame design, etc., to study the acoustic barrier performance of typical fuselage panel structures, put forward design suggestions for fuselage panels, and guide the acoustic optimization design of civil aircraft structures.
Thermal design of a frequency hopping processor
Authors: Liang Dapeng , Wang Sheng , Wang Siqi , Zhang Li , Li Dan , Hu Fengjiao 
Published: November 2024

Abstract
To solve the difficult problems in the thermal design of a new frequency-hopping processor, such as high heat consumption, concentrated local heat flux of the device, and large thermal resistance, a thermal design scheme was proposed to optimize the structure design and enhance the thermal conductivity of PCB board. At the same time, a combined scheme of copper water heat pipe-thermal expansion plate was used. Flotherm was used for thermal simulation and a thermal balance experiment under vacuum conditions was designed. Then the temperature of the frequency-hopping processor was measured experimentally to further verify the rationality of the design scheme. The combined scheme of copper water heat pipe-thermal expansion plate will guide the thermal design of this type of frequency hopping processor.
Experimental study of polyurethane rubber with half-sine waveform generator
Authors: Jin Zijian , Shen Zhiqiang , Yan Tingfei , Li Xinming , Liu Chuang , Ren Zhiqiang 
Published: November 2024

Abstract
Impact mechanics environmental testing technology is booming. Polyurethane rubber, as a typical semi-sinusoidal waveform generator, is particularly important to understand its stiffness performance. This paper presents an experimental investigation utilizing a pneumatic impact testing machine to evaluate the performance of polyurethane rubber waveform generators, varying in both hardness and height. By recording their compression under varying impact pressures, as well as the rebound height of the table and the corresponding velocity changes, we observed that the data generated by the 60mm thick waveform generator exhibited greater regularity. Notably, these data adhered to the principle that increased hardness correlates with decreased compression and reduced rebound height of the table. Additionally, we successfully designed an initial prototype of a rebound collision acceleration amplifier, which, under an impact pressure of merely 0.038MPa, achieved an impressive impact acceleration of nearly 2700g, accompanied by a smoother half-sine waveform curve.
Fuze vibration reduction design based on high-speed rocket sled vibration effect
Authors: Yan Lide , Cao Lifei , Duan Xiaochang , Wu Qi , Hou Lei , Xue Yubo 
Published: November 2024

Abstract
Rocket sled is one of the important methods to realize the performance test in fields such as aerospace and weapon equipment. In response to the extremely high overload phenomenon of the tested fuze system in rocket sled impact tests, this paper proposes a new method of fuze vibration reduction. By optimizing the layout and multi-layer potting of fuze shell and internal components, the influence of vibration effects on electronic components is effectively reduced. Comparative analysis of results is based on epoxy resin sealant potting, silicone rubber potting, or without additional protection, to further improve the safety and service life of internal key components and provide necessary structural reference for vibration reduction treatment in rocket sled tests.
Performance analysis of air-cooled turbine based on source terms method
Authors: Hao Ning , Yi Weilin 
Published: November 2024

Abstract
Investigating turbine blade cooling and blade tip clearance leakage is crucial for reducing turbine losses and enhancing overall engine performance. Therefore, this paper uses the E3 two-stage high-pressure turbine as a case and employs the source term method to model the film cooling configuration, validating its efficacy and examining the performance parameters and flow field characteristics of air-cooled turbines under varying blade tip clearances. The outcomes demonstrate that the source term approach accurately forecasts the comprehensive performance parameters of air-cooled turbines, with blade tip clearance height predominantly impacting turbine performance in high-velocity regions. For small blade tip clearance, air-cooled turbines exhibit diminished efficiency with a decreasing expansion ratio in high-velocity regions, but they demonstrate an inverse behavior in low-velocity regions. Conversely, under conditions of larger blade tip clearances, the cooling effectiveness of air-cooled turbines is more pronounced in regions characterized by low expansion ratios and low speeds.
Research on the influence of out-of-plane loads on the fatigue life of metal structures
Authors: Wang Qianqian , Huang Fu 
Published: November 2024

Abstract
For civil aircraft structures, in-plane tensile, compressive, shear, and their combined forms of loads are the usual loads on plate and shell structures, while bending moments, torsion, and other forms of loads are mainly borne by assemblies consisting of multiple parts. However, some plate and shell structures are subjected to in-plane loads while also being affected by out-of-plane loads. In order to study the difference between the fatigue performance of plate and shell structures under the influence of out-of-plane load and the fatigue performance under the effect of pure in-plane load, the axial tensile fatigue test considering the out-of-plane load is carried out, which demonstrates the negative effect of the out-of-plane load on the axial tensile fatigue strength of the structure. At the same time, a new structural fatigue life prediction method considering out-of-plane loads is established by combining finite element analysis, which can more accurately predict the structural fatigue life under the influence of out-of-plane loads and provide support for metal structure fatigue analysis.
Study of three-dimensional crack extension in turbine discs of short-life turbojet engines
Authors: Huang Yang , Huang Hui , Xiong Jie 
Published: November 2024

Abstract
A simulation study on the 3D crack extension of short-lived turbojet engine turbine discs was carried out using FRANC3D 3D fracture mechanics software combined with ABAQUS finite element software. By establishing a 3D geometric model of the turbine disc, the crack extension process is simulated by using the sub-model method, and the crack extension behavior and failure mode are analyzed to predict the remaining life of the cracked wheel disc. The results show that the crack expansion path matches well with the crack failure phenomenon of the turbine disc under the actual working conditions; the turbine disc crack is dominated by Type I (open Type) crack expansion, and the stress intensity factors of Type II and Type III are negligible; the crack expansion rate increases slowly with the increase of crack depth, and it rises steeply at the critical value of the fracture failure; and the residual life of the turbine disc is 32 cycles. This study provides empirical analyses for crack monitoring and life prediction of turbine discs and is of great significance for engine maintenance and reduction of end-of-life costs of turbine components.
Prediction of aircraft fuel consumption based on machine learning algorithm
Authors: Fang Shengyou , Qu Cheng , Liu Tao 
Published: November 2024

Abstract
The shortcomings of traditional aircraft fuel consumption calculation methods include insufficient theoretical analysis, complex input parameters, and poor calculation accuracy. Through the analysis of aircraft motion equations and engine working characteristics, this paper screens out the key parameters affecting aircraft fuel consumption. Based on the real flight data, three machine learning methods, BP neural network, RBF neural network, and Support Vector Machine(SVM), are used for training, and a fuel consumption prediction model is established with key parameters as inputs. The prediction accuracy and characteristics of the three models are analyzed and compared. The aircraft fuel consumption prediction model achieves the operational requirements, and the accuracy in the flight profile reaches 5%. The trained model was applied to the planning of the transport aircraft mission profile, achieving a fuel consumption error of only 1.1% across the entire mission profile, resulting in a relatively accurate outcome.
Analysis of factors affecting the stability of aircraft engine test
Authors: Shen Yifan , Luo Tingfang 
Published: November 2024

Abstract
Although the aircraft is in a braking and shutdown state during engine testing, there may still be situations where the aircraft slides or deviates during the development process, which affects the safety of the aircraft. This article establishes a force analysis model for an aircraft engine test and proposes a single-engine testing force analysis method based on dual-engine testing force analysis. Factors such as the friction coefficient of pavement, wind speed, and aircraft parking slope are taken into account in the calculation. The relationship between different influencing factors and ground stability is studied in the article. The article provides a reference for the weight center of gravity limitation of aircraft under engine ground testing conditions.
Experimental study on fireproof of aviation lubrication oil tank
Authors: Wu Bin , Zeng Tai , Li Songyang , Su Zhengliang , Xie Fei 
Published: November 2024

Abstract
This paper presents an experimental study on the fireproof performance of aeroengine lubrication oil tanks. By constructing a simplified lubrication oil tank model and simulating the harsh operating conditions of engine fires, the oil tank was exposed to flames generated by a standard burner for testing. The study monitored and recorded key parameters such as temperature, pressure, flow rate, and phase changes within the tank. The results indicate significant differences in the temperature distribution characteristics of the tank walls under different inlet temperatures and flow conditions. In the rigorous 15-minute flame test, all tests successfully completed the fire verification process.
Modeling of the leader-follower satellite formation for long baseline
Authors: Wu Jun , Wang Wenyan , Wan Bei 
Published: November 2024

Abstract
Interferometric Synthetic Aperture Radar (InSAR) represents a crucial component of synthetic aperture radar technologies, with the accuracy of measurements significantly improving as the baseline length increases. In comparison with the traditional Hill-Clohessy-Wiltshire (HCW) equations, the application of curvilinear coordinate systems for modeling satellite formations in circular orbits has demonstrated enhanced precision, especially when the formations span larger distances. However, these improvements were initially limited to circular orbits. Addressing this limitation, this study introduces a novel approach by incorporating elliptical orbits into the model, thereby refining the state transition matrix through the incorporation of eccentricity factors and maintaining the direct correlation with the temporal dynamics of satellite motion in three dimensions. Through rigorous numerical simulations, it has been established that this refined model substantially improves accuracy in leader-follower satellite formations.
Insight HXMT and GECAM joint observation of time domain astronomy from cosmic outbursts
Authors: Huang Xinyue 
Published: November 2024

Abstract
The field of time-domain astronomy focuses on the observation of temporal variations in celestial phenomena, in particular gamma-ray bursts (GRBs). It emphasized the importance of monitoring transient events and phenomena, which occurred on different time scales, ranging from milliseconds to years. This paper also explained the properties of X-rays and Gamma-rays, their sources and the significance of studying them for understanding the dynamic nature of the universe. The collaboration between the Insight HXMT and GECAM missions was designed to detect and study high-energy astronomical events, such as those associated with black holes and neutron stars, and to provide for rapid data transmission and dissemination of astronomical alerts. By combining observations from the two instruments, researchers can gain a more comprehensive understanding of cosmic phenomena and explore the fundamental physics of the universe.
Experimental study on thermally induced vibration of flexible solar cell wing simulator
Authors: Bi Yanqiang , Gao Wen , Fan Chao , Xiang Zhihai , Du Chunlin 
Published: November 2024

Abstract
With the development of large spacecraft and satellite payloads, the power supply required is increasing, especially in space solar power stations, and the large flexible solar wing is an inevitable trend in the future. Due to their light weight and large area, flexible solar wings may face thermally induced vibration during orbit operation, which will lead to the degradation of spacecraft performance and even structural damage. In this paper, the test method of a flexible solar wing simulator is established, and the thermally induced vibration test of a flexible solar cell wing simulator is carried out. And vibration amplitude value is 25 and 9 microns with a frequency 0.56Hz.The characteristic of thermally induced vibration of flexible solar cell wing is given, which provides a basis for its thermally induced vibration suppression.
Trajectory reconstruction method for spacecraft formation considering collision probability constraints
Authors: Wang Bochuan , Wang Xiaohui , Liu Jiancen , Jin Xiangyu , Tang Yinglong 
Published: November 2024

Abstract
This paper introduces a trajectory reconstruction algorithm for spacecraft formation, combining collision probability and sequential convex programming algorithms. When reconstructing the trajectory of spacecraft formation, external collision avoidance constraint is added to avoid collision threats from space objects. The constraint accuracy of the external collision avoidance constraints of the BOX method and the collision probability method is analyzed. The simulation results indicate that the collision probability method has higher accuracy compared to the BOX method. It addresses the issue of inaccurate division of collision avoidance zones in the BOX method, which tends to be aggressive in the velocity direction and conservative in other directions. A reference is provided for trajectory reconstruction when formation satellites encounter non-cooperative targets.