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A numerical method for predicting bursting strength of composite rocket motor case considering filament winding process-induced stress

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Chinese Journal of Aeronautics 2025年第2期38卷 505-518页

作者： Jiqiu LIANG Fei ZHAO Dan WU Anxin DING Hubei Key Laboratory of Advanced Aerospace Propulsion Technology Wuhan 430040China System Design Institute of Hubei Aerospace Technology Academy Wuhan 430040China School of Materials Science and Engineering Wuhan University of TechnologyWuhan 430070China State Key Laboratory of Advanced Technology for Materials Synthesis and Processing Wuhan University of TechnologyWuhan 430070China

A numerical method to predict the bursting strength of filament wound composite rocket motor case is proposed *** method can evaluate the longitudinal stress evolution of each composite layer as impregnated filaments with fiber tension are wound layer by layer,and consider the effects of accumulated stress and deformation during filament winding on the bursting strength of composite ***∅520 mm composite cases as a case study,the filament-winding-process-induced stress and deformation as well as progressive damage behavior are numerically predicted,followed by a comparison with experimental *** numerical results show that the predicted bursting pressures for composite cases manufactured on the mandrels with and without a flexible component are 14.20 MPa and 21.40 MPa,*** values exhibit slight deviation from the measured pressures of 13.50 MPa and 21.57 ***,the predicted damage locations,situated respectively in the dome and cylinder,agree well with the experimental *** observations indicate that use of flexible component reduces the load-bearing capacity of the ***,it validates the reliability and accuracy of the proposed numerical method in predicting the bursting strength of composite cases.

关键词： Composite case Fiber tension Bursting strengt hProgressive damage analysis Filament winding

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Experimental Study on Geometry Characteristics of Turbulent Premixed Flames for Natural Gas/Air Mixtures

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Journal of Thermal Science 2025年第1期34卷 268-282页

作者： ZHENG Weilin WANG Qijiao XIAO Huahua CHEN Xiaoxiao XIE Fan ZENG Wen Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System Shenyang Aerospace UniversityShenyang 110136China State Key Laboratory of Fire Science University of science and Technology of ChinaHefei 230027China AVIC Shenyang Aircraft Design and Research Institute Shenyang 110035China

In this study,focusing on the geometry characteristics of spherical expanding flame,the turbulent premixed flames of natural gas/air mixtures were investigated in a fan-stirred turbulent *** effects of initial temperature(T=300-400 K),initial pressure(P=0.1-0.3 MPa),turbulence intensity(u'=1.0-2.7 m/s),oxygen volumetric percentage(φ(O_(2))=15%-21%)and carbon dioxide volumetric percentage(φ(CO_(2))=0-20%)were delved *** flame profile under the Cartesian coordinate system was derived from the schlieren images taken by the high-speed ***,from both macroscopic and microscopic perspectives,the influence of experimental conditions on the flame geometry characteristics was explored through flame front extraction,wavelet decomposition and network *** results demonstrate that for significant flame wrinkling,changes in species concentrations and turbulence intensity have more pronounced effects on the flame wrinkling *** wrinkling of the flame front maintains a certain degree of similarity,as evidenced by the locally concentrated distribution of the angles of the maximum fluctuation *** disturbance energy under large-scale(D6-D8)disturbances exhibits relatively high values with a similar trend,exerting a significant impact on the geometry characteristics of the flame *** peaks of correlation degree are scattered either with the decomposition scale or the development of flame radius,indicating no linear correlation between different detail ***,the probability distribution of node degrees in key wrinkled regions exhibits different trends with that of large-scale wrinkling and disturbance energy,especially with changes in initial *** occurs because the number of key wrinkles varies based on the perturbation's strength or the region's ***,an increase in the fluctuation frequency of the flame's local radius may not necessarily lead to an increase in the number of key folded regions.

关键词： geometry characteristics large-scale wrinkling wavelet decomposition network topology fan-stirred turbulent combustor

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Mechanical performance of stiffened CFRP panel cured via magnetic particle-induced in-situ heating

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Fuhe Cailiao Xuebao/Acta Materiae Compositae Sinica 2025年第5期42卷 2528-2536页

作者： Xu, Yurong Hu, Xiafen Sun, Ao Liang, Jiqiu Wu, Dan Hao, Lei Wei, Junjie Li, Yichao School of Aerospace Engineering Huazhong University of Science and Technology Wuhan430074 China Hubei Key Laboratory of Advanced Aerospace Propulsion Technology System Design Institute of Hubei Aerospace Technology Academy Wuhan430040 China

With the development trend of large and complexity of carbon fiber reinforced polymer (CFRP) structures, the conventional oven or autoclave molding method exposes problems such as size limitation, long fabrication time, low energy utilization, uneven curing, etc., and there is an urgent need to explore new composite molding method. In this paper, a new fabrication method to cure CFRP based on electromagnetic induction in-situ heating was investigated by using Mn-Zn ferrite as a heating carrier. The heating characteristics, mechanical properties and porosity of stiffened CFRP panels with two kinds of complex layups, T-shape and I-shape, were investigated, and comparative analyses were carried out with the counterpart specimens cured by an oven. The results show that the induction method can achieve in-situ, uniform, temperature-controlled and lay-up angle independent heating and curing for both two types panels. Under the condition of 13wt% Mn-Zn ferrite addition and 5.5 h induction heating, the flexural stiffness of the T-shaped panel is increased by 5.2% and the maximum load is increased by 11.2% compared to the oven-formed specimen under the same curing time. The buckling load of the I-beam reinforced panel increases by 3.3% compared to the oven-molded specimen. However, the porosity of the two types of panels increase slightly by 0.4% and 0.3%. The results obtained in this paper provide important guidance for the engineering application of electromagnetic induction curing process in the fabrication of CFRP composite structures. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Machinability

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Bending Characteristics of Folded Multi-celled Tubes with Square and Circular Section Geometries

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Acta Mechanica Solida Sinica 2025年第1期38卷 125-141页

作者： Rui Liang Fengxiang Xu Zhen Zou Xiaoqiang Niu Xuebang Tang Tingpeng Li School of Automobile Engineering Guilin University of Aerospace TechnologyGuilin541004China Hubei Key Laboratory of Advanced Technology of Automotive Components Wuhan University of TechnologyWuhan430070China Hubei Collaborative Innovation Center for Automotive Components Technology Wuhan University of TechnologyWuhan430070China Academic Affairs Office Guilin University of Aerospace TechnologyGuilin541004China

This research investigates the bending response of folded multi-celled tubes(FMTs)fabricated by folded metal sheets.A three-point bending test for FMTs with circular and square sections is designed and *** base numerical models are correlated with physical experiments and a static crashworthiness analysis of six FMT configurations to assess their energy absorption *** influences of thickness,sectional shape,and load direction on the bending response are *** indicate that increasing the thickness of the tube and radian of the inner tube enhances the crashworthiness performance of FMT,yielding a 20.50%increase in mean crushing force,a 55.53%increase in specific energy absorption,and an 18.05%decrease in peak crushing force compared to traditional multi-celled tubes(TMTs).A theoretical analysis of the specific energy absorption indicates that FMTs outperform TMTs,particularly when the peak crushing force is *** study highlights the innovative and practical potential of FMTs to improve the crashworthiness of thin-walled structures.

关键词： Bending Folded Multi-celled tube Energy absorption Numerical

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HfC–HfO_(2) modified high/superhigh temperature thermal protection coating for superior hot corrosion resistance and antioxidation performance

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Journal of advanced Ceramics 2025年第1期14卷 177-191页

作者： Zhiyun Ye Shuqi Wang Shuang Yu Xinrui Zhao Yongchun Zou Guoliang Chen Lei Wen Lina Zhao Guangxi Zhang Yaming Wang Jiahu Ouyang Dechang Jia Yu Zhou State Key Laboratory of Precision Welding&Joining of Materials and Structures Harbin Institute of TechnologyHarbin 150001China Institute for Advanced Ceramics Harbin Institute of TechnologyHarbin 150001China Key Laboratory of Advanced Structure-Function Integrated Materials and Green Manufacturing Technology Harbin Institute of TechnologyHarbin 150001China National Center for Materials Service Safety University of Science and Technology BeijingBeijing 100083China Xi’an Aerospace Composites Research Institute Academy of Aerospace Propulsion TechnologyXi’an 710025China

With advances in the thrust-weight ratio,the service temperature of gas turbine engines even exceeds 1500℃,which is urgent for the development of high/superhigh-temperature thermal protection systems(TPSs)for long-term *** alloys are increasingly viewed as promising structural materials for high-temperature applications because of their superior high-temperature mechanical strength,but the“pest”catastrophic oxidation greatly restricts their further *** this study,a HfC–HfO_(2)-modified silicide coating was prepared via an innovative method of halide-activated pack cementation(HAPC)combined with liquid-plasma-assisted particle deposition and sintering of niobium alloys,resulting in a composite coating with excellent hot corrosion resistance and high-temperature oxidation *** modified multilayer coating is characterized by the synergistic combination of a dense NbSi_(2) inner layer and a HfC–HfO_(2) porous outer layer,resulting in a significant improvement in high-temperature performance compared with that of the single NbSi_(2) *** corrosion gain of the composite coating is only 13.94 mg·cm^(−2) after a corrosion time of 200 h at 900℃,and an intact oxide scale surface is observed after oxidation at 1500℃for 500 *** improvement is attributed to the formation of a robust Hf-rich skeleton provided by the deposited HfC–HfO_(2) layer,which can accelerate the formation of a highly stable corroded layer/oxide *** addition,multiple stress release mechanisms of the composite coating at high temperatures also provide substantial contributions to long-term *** these merits make HfC–HfO_(2)-modified composite coatings on niobium alloys competitive for the development of high/superhigh-temperature thermal protection systems for long-term service.

关键词： thermal protection coating niobium alloys hot corrosion resistance high-temperature oxidation resistance stress release mechanism

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Solving model of friction and wear characteristics of brush seal considering time-varying wear of brush wire

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Hangkong Dongli Xuebao/Journal of aerospace Power 2025年第4期40卷

作者： Lan, Kexin Zhao, Huan Sun, Dan Yang, Zemin Xu, Wenfeng Sun, Jisheng Liaoning Key Lab of Advanced Test Technology for Aerospace Propulsion System School of Aero-engine Shenyang Aerospace University Shenyang110136 China Key Laboratory of Turbomachinery Advanced Seal Technology Shenyang Aerospace University Shenyang110136 China

Based on Euler-Bernoulli beam theory and Archard wear theory coupling method， a solution model of brush seal friction and wear characteristics considering time-varying wear of brush wire was proposed. The normal contact force，wear rate and wear loss between the free end of brush wire and the rotor surface were analyzed. The experimental device of brush seal friction and wear characteristics based on cylindrical circumferential friction was designed and built. On the basis of experimental verification of the accuracy of the solution model，the influences of working condition parameters and structural parameters of brush seal on the friction and wear characteristics of brush seal were studied. The results showed that the normal contact force and wear rate between the free end of the brush wire and the rotor surface decreased logarithmically with the increase of the friction time，and finally approached 0. The wear loss increased logarithmically with the increase of friction time，and finally became stable. When the rotation speed was 2 000 r/min and the interference amount was 0.4 mm，the wear of the brush wire mainly occurred in the first 20 h，and the wear of the brush wire became stable at the 50 h. The normal contact force，wear rate and wear amount of the brush wire increased with the increase of the interference amount and the thickness of the brush wire，and the wear amount also increased linearly. With the increase of rotational speed，radial length and diameter of the brush wire and the decrease of the inclination angle of the brush wire，the decrease rate of the normal contact force and wear rate curve of the brush wire was faster，and the time for the brush wire to reach the maximum wear amount was shorter. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Wear of materials

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Effect of suction leading edge vortex generator on characteristics of compressor cascade

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Hangkong Dongli Xuebao/Journal of aerospace Power 2025年第5期40卷

作者： Xu, Wenfeng Zou, Shilong Sun, Dan Lu, Wenxin Ren, Guozhe Zhao, Huan Liaoning Key Laboratory of Advanced Measurement and Test Technology for Aviation Propulsion System School of Aero-engine Shenyang Aerospace University Shenyang110136 China

A compressor linear cascade was studied，and vortex generators were arranged near the suction leading edge of the end wall to improve the stator aerodynamic characteristic and control the corner separation. The effects of the vortex generators with different heights，lengths，and pitch positions on the corner separation flow and aerodynamic characteristics were studied by numerical simulation. The results showed that the suction leading edge vortex generator can generate the induced vortex near the end wall of the passage inlet， which inhibited the accumulation of low-energy fluids in the corner region，shifted the separation starting point backward，and narrowed the corner region along the pitch direction，thereby reducing the flow loss. The vortex generator should be arranged at the starting position of the corner separation. The control effect of the corner separation first increased and then decreased with the increase of the height of the vortex generator. With the increase of the chord of the vortex generator，it gradually decreased. As the arrangement position was far away from the suction，it first increased and then decreased. When the vortex generator was arranged at the boundary between the end wall recirculation region and the mainstream region，the chord was equal to 25% of the blade chord，and the height was equal to 2% of the blade height，the flow loss can be reduced by 10.3%. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Airships

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Suppression of microcracks in femtosecond laser grooving of aluminum using a flame environment

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Optics Letters 2025年第9期50卷 2836-2839页

作者： Guo, Sijia Jiang, Yuanfei Han, Jianhui Chen, Anmin Jin, Mingxing Institute of Atomic and Molecular Physics Jilin University Changchun130012 China Jilin Provincial Key Laboratory of Applied Atomic and Molecular Spectroscopy Jilin University Changchun130012 China State Key Laboratory of Advanced Space Propulsion Department of Aerospace Science and Technology Space Engineering University Beijing101416 China

Femtosecond laser machining of aluminum often suffers from microcrack formation and edge irregularities, affecting processing quality. This study explores the impact of a flame environment on groove characteristics. Results show that in ambient air, high-energy laser pulses induce microcracks, especially at high scanning speeds, while the flame environment suppresses microcracks and improves edge uniformity. The flame preheats the material, reduces thermal shock, and enhances material removal, leading to deeper and more consistent grooves. These findings provide insights for optimizing laser processing parameters to improve machining stability and surface quality. © 2025 Optica Publishing Group. All rights, including for text and data mining (TDM), Artificial Intelligence (AI) training, and similar technologies, are reserved.

关键词： Laser materials processing

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Numerical and experimental study on leakage characteristics of combined elastic metal seal

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Hangkong Dongli Xuebao/Journal of aerospace Power 2025年第5期40卷

作者： Huang, Chanyuan Wen, Shuaifang Sun, Dan Li, Yu Yang, Zemin Zhang, Xiaolin Wu, Lijun Shenyang Aerospace University Liaoning Key Laboratory of Advanced Testing Technology of Aeronautical Propulsion System Shenyang Aerospace University Shenyang110136 China Shenyang Turbine Machinery Key Laboratory of Advanced Sealing Technology School of Aero-Engine Shenyang Aerospace University Shenyang110136 China Commercial Aircraft Engine Company Limited Aero Engine Corporation of China Shanghai200241 China

In order to study the leakage characteristics of the combined elastic metal seal，two kinds of numerical calculation models for the leakage characteristics of the contact leakage channel and the gap leakage channel were established. On basis of the numerical calculation results of the macroscopic mechanical characteristics，a solution model for the leakage characteristics of the combined elastic metal seal considering the actual rough contact surface was established based on the fractal theory. An experimental device for leakage characteristics of the combined elastic metal seal was designed and built. Based on experimental verification of the accuracy of the numerical solution model， the mechanical characteristics and leakage characteristics of the combined elastic metal seal under different pressure difference and compression amount of the internal and external cavities were studied， and the sealing mechanism under the influence of roughness was analyzed. The results showed that the equivalent stress increased with the increase of pressure difference and compression quantity. The leakage decreased gradually with the increase of compression and temperature，and the leakage decreased by 24.12% under the conditions of maximum pressure ratio and maximum compression. Surface roughness had a great influence on the leakage amount of the combined elastic metal seal，and roughness and compression could affect the leakage channel gap at the contact and then affect the flow field distribution. The numerical calculation method considering roughness had less error than the traditional method，and can calculate the leakage amount of the combined elastic metal seal more accurately， providing a theoretical basis for analysis of leakage characteristics of the combined elastic metal seal. © 2025 Beijing University of Aeronautics and Astronautics (BUAA). All rights reserved.

关键词： Brinell Hardness

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Theoretical Research on the Combustion Characteristics of Ammonium Dinitramide-Based Non-Toxic aerospace Propellant

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aerospace 2025年第4期12卷 295-295页

作者： Han, Jianhui Wen, Ming Hong, Yanji Du, Baosheng Jiang, Luyun Cui, Haichao Feng, Gaoping Song, Junling State Key Laboratory of Advanced Space Propulsion Department of Aerospace Science and Technology Space Engineering University Beijing101416 China

Propellants play a crucial role in the propulsion systems of aerospace vehicles, and their combustion characteristics are susceptible to external environmental conditions. This study systematically investigated the impact of various initial conditions on the combustion process of ADN-based propellant, including combustion products, equilibrium pressure, adiabatic temperature, and ignition delay time. The results indicate that the primary combustion products of ADN-based propellant include N2O, N2, CO2, OH, and others. ADN-based propellant exhibits a distinct two-stage combustion process under low pressure and temperature conditions (P0 = 2 atm, T0 = 586 K). Conversely, under high pressure and temperature conditions (P0 = 10 atm, T0 = 2930 K), the two stages of combustion occur almost simultaneously, making them difficult to distinguish. Furthermore, as the initial temperature increases, the ignition delay time decreases significantly, and the combustion rate accelerates. When the initial temperature rises from 400 K to 2800 K at a pressure of P0 =10 atm, the ignition delay time decreases from 3.5 ms to 0.6 μs. Interestingly, changes in initial pressure have a relatively minor impact on the ignition delay time compared to changes in temperature. Therefore, temperature has a more crucial influence on the combustion characteristics of ADN-based propellant than pressure. This study holds promise for providing new combustion optimization strategies for the aerospace industry and promoting the development of aircraft designs towards higher performance and sustainability. © 2025 by the authors.

关键词： Ignition

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