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中国航空学报（英文版）
中国航空学报（英文版）

朱自强

双月刊

1000-9361

cja@buaa.edu.cn

010-82317058

100083

北京学院路37号西小楼

中国航空学报（英文版）/Journal Chinese Journal of AeronauticsCSCDCSTPCD北大核心EISCI
查看更多>>本学报1988年创刊，中国航空学会主办，原为中文版《航空学报》选刊，1996年开始改为直接从来稿中录用文章，两刊不再重复。主要栏目有空气动力学、飞行力学、自动控制、航空电子、发动机、材料、制造工艺及飞行器设计等。
正式出版
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    makeTwin:A reference architecture for digital twin software platform

    Fei TAOXuemin SUNJiangfeng CHENGYonghuai ZHU...
    1-18页
    查看更多>>摘要：Digital twin is currently undergoing a significant transformation from the conceptual and theoretical research phase to the implementation and application phase.However,a universally adaptable research and development platform for digital twin is critically needed to meet the devel-opment requirements.Specifically,a publicly accessible simulation,testing,and validation platform which can support digital twin model building,data processing,algorithm design,configuration,etc.,is urgently required for researchers.Furthermore,for developers from the industry,a low-code development platform that can offer a customizable suite of functions such as model creation,data management,protocol configuration,and visualization is urgently needed.Meanwhile,for enterprise users,there is a lack of an application management platform that can be configured and migrated for various application scenarios,functions,and modes.Therefore,based on the sys-tem research of digital twin theories and key technologies by the authors(such as the five-dimension digital twin model,digital twin modeling and digital twin data theory,digital twin standards,and so on),a digital twin software platform reference architecture,namely makeTwin,is proposed and designed,as well as its ten core functions.The workflow of the makeTwin and the interaction mech-anisms among its core functions are described.Finally,a digital twin application system for a chem-ical fiber textile shop floor(CFTS)which was developed according to makeTwin,is introduced,which validates the proposed reference architecture.
      原文链接:
    • NETL
    • NSTL
    • 万方数据
    • 维普

    Matched Volterra reduced-order model for an airfoil undergoing periodic translation

    Lianrui NIEZiniu WU
    19-23页
    查看更多>>摘要：This paper is devoted to application of the Reduced-Order Model(ROM)based on Vol-terra series to prediction of lift and drag forces due to airfoil periodic translation in transonic flow region.When there is large amplitude oscillation of the relative Mach number,as appeared in heli-copter rotor movement in forward flight,the conventional Volterra ROM is found to be unsatisfac-tory.To cover such applications,a matched Volterra ROM,inspired from previous multistep nonlinear indicial response method based on Duhamel integration,is thus considered,in which the step motions are defined inside a number of equal intervals with both positive and negative step motions to match the airfoil forward and backward movement,and the kernel functions are con-structed independently at each interval.It shows that,at least for the translation movement consid-ered,this matched Volterra ROM greatly improves the accuracy of prediction.Moreover,the matched Volterra ROM,with the total number of step motions and thus the computational cost close to those of the conventional Volterra ROM method,has the additional advantage that the same set of kernels can match various translation motions with different starting conditions so the kernels can be predesigned without knowing the specific motion of airfoil.
      原文链接:
    • NETL
    • NSTL
    • 万方数据
    • 维普

    Technologies and studies of gas exchange in two-stroke aircraft piston engine:A review

    Yu ZHOUXueyu LIShuiting DINGShuai ZHAO...
    24-50页
    查看更多>>摘要：The in-cylinder gas exchange process is crucial to the power performance of two-stroke aircraft piston engines,which is easily influenced by complex factors such as high-altitude perfor-mance variation and in-cylinder flow characteristics.This paper reviews the development history and characteristics of gas exchange types,as well as the current state of theory and the validation methods of gas exchange technology,while also discusses the trends of cutting-edge technologies in the field.This paper provides a theoretical foundation for the optimization and engineering design of gas exchange systems and,more importantly,points out that the innovation of gas exchange types,the modification of theoretical models,and the technology of variable airflow organization are the key future research directions in this field.
      原文链接:
    • NETL
    • NSTL
    • 万方数据
    • 维普

    Mechanism of capture section affecting an intake for atmosphere-breathing electric propulsion

    Siyuan ZHANGJinyuan YANGCheng LIHaolin LI...
    51-63页
    查看更多>>摘要：Atmosphere-Breathing Electric Propulsion(ABEP)can compensate for lost momentum of spacecraft operating in Very Low Earth Orbit(VLEO)which has been widely concerned due to its excellent commercial potential.It is a key technology to improve the capture efficiency of intakes,which collect and compress the atmosphere for ABEP.In this paper,the mechanism of the capture section affecting capture efficiency is investigated by Test Particle Monte Carlo(TPMC)simulations with 3D intake models.The inner surface smoothness and average collision number are determined to be key factors affecting capture efficiency,and a negative effect growth model is accordingly established.When the inner surface smoothness is less than 0.2,the highest capture effi-ciency and its corresponding average collision number interval are independent of the capture sec-tion's geometry and its mesh size.When the inner surface smoothness is higher than 0.2,the capture efficiency will decrease by installing any capture section.Based on the present results,the manufac-turing process and material selection are suggested to be prioritized during the intake geometry design in engineering projects.Then,the highest capture efficiency can be achieved by adjusting the length and mesh size of the capture section.
      原文链接:
    • NETL
    • NSTL
    • 万方数据
    • 维普

    Method for passivation of propellant residues in orbital stage tank of launch vehicle

    Valeriy TRUSHLYAKOVIvan LESNYAKAlexey PANICHKIN
    64-76页
    查看更多>>摘要：The problem of removing unused liquid propellant residues from the tanks of spent spacecraft and orbital stages of Launch Vehicles(LV)leads to their explosion and the formation of space debris in orbits.To provide a solution to this problem,a method for removing liquid pro-pellant residues from the LV tanks after the mission completion is proposed.The method is based on the gasification of liquid propellant residues in the tanks under acoustic-vacuum exposure and the discharge of the gasification products into the surrounding outer space.Experimental investiga-tions were carried out on a Ground-based Experimental Installation(GEI)to determine the coef-ficient of heat transfer from the surface of an acoustic radiator to a liquid.The obtained coefficient was then used to calculate the energy costs for the gasification of kerosene.Numerical estimates are given on the example of the tank with kerosene residues from a spent second stage of the LV"Soyuz-2.1 v".The optimal discharge rate at which kerosene does not freeze is 0.14 m3/s.Moreover,the acoustic exposure leads to an increase in the mass of evaporated kerosene over a given time by 96.1％,and the energy costs are 1756.7 kJ(approximately 50％of the remaining electrical energy).
      原文链接:
    • NETL
    • NSTL
    • 万方数据
    • 维普

    Elaborative collection of condensed combustion products of solid propellants:Towards a real Solid Rocket Motor(SRM)operational environment

    Wenchao ZHANGZhimin FANDongliang GOUYao SHU...
    77-88页
    查看更多>>摘要：A novel constant-pressure and constant-quenching distance Condensed Combustion Products(CCPs)collection system was developed,coupled with a timing control system,to collect the CCPs formed in the course of burning of aluminum-based composite propellants.The effects of adiabatic graphite plating,collection zone,quenching distance,time series of collection,and propel-lant burning rate on the microscopic morphology,particle size distribution and unburned alu-minum content of CCPs were investigated.It was verified that the graphite plating can provide a high-fidelity high-temperature environment for propellant combustion.The combustion efficiency is improved by 2.44％compared to the bare propellant case.The time series of collection has a sig-nificant effect on the combustion efficiency of aluminum,and the combustion efficiency of alu-minum in the thermal state(1.2-2.4 s)is 2.75％higher than that in the cold state(0-1.2 s).Similarly,the characteristics of the CCPs in different collection zones are different.At the quench-ing distance of 5 mm,the combustion efficiency of aluminum in the core zone(85.39％)is much lower than that in the outer zone(92.07％),while the particle size of the CCPs in the core zone(172 μm)is larger than that in the outer zone(41 μm).This indicates that the core zone is more likely to produce large-sized and incompletely burned agglomerates during the propellant combus-tion process.Different burning rates also lead to a significant difference in particle size distribution and combustion efficiency.High burning rates result in higher combustion efficiency.A detailed sequence of the elaborative collection process of CCPs is proposed,mainly including the setting of ignition delay time,burning rate,working pressure,plating length and time series of collection.The findings of this study are expected to provide a reliable tool for the evaluation of the combus-tion efficiency of solid propellants.
      原文链接:
    • NETL
    • NSTL
    • 万方数据
    • 维普

    A reduced-order model for fast predicting ionized flows of hypersonic vehicles along flight trajectory

    Jingchao ZHANGChunsheng NIEJinsheng CAIShucheng PAN...
    89-105页
    查看更多>>摘要：An improved Reduced-Order Model(ROM)is proposed based on a flow-solution pre-processing operation and a fast sampling strategy to efficiently and accurately predict ionized hypersonic flows.This ROM is generated in low-dimensional space by performing the Proper Orthogonal Decomposition(POD)on snapshots and is coupled with the Radial Basis Function(RBF)to achieve fast prediction speed.However,due to the disparate scales in the ionized flow field,the conventional ROM usually generates spurious negative errors.Here,this issue is addressed by performing flow-solution preprocessing in logarithmic space to improve the conventional ROM.Then,extra orthogonal polynomials are introduced in the RBF interpolation to achieve additional improvement of the prediction accuracy.In addition,to construct high-efficiency snapshots,a trajectory-constrained adaptive sampling strategy based on convex hull optimization is developed.To evaluate the performance of the proposed fast prediction method,two hypersonic vehicles with classic configurations,i.e.a wave-rider and a reentry capsule,are used to validate the proposed method.Both two cases show that the proposed fast prediction method has high accuracy near the vehicle surface and the free-stream region where the flow field is smooth.Compared with the conventional ROM prediction,the prediction results are significantly improved by the proposed method around the discontinuities,e.g.the shock wave and the ionized layer.As a result,the pro-posed fast prediction method reduces the error of the conventional ROM by at least 45％,with a speedup of approximately 2.0 x 105 compared to the Computational Fluid Dynamic(CFD)simu-lations.These test cases demonstrate that the method developed here is efficient and accurate for predicting ionized hypersonic flows.
      原文链接:
    • NETL
    • NSTL
    • 万方数据
    • 维普

    Aeroengine thrust estimation and embedded verification based on improved temporal convolutional network

    Wanzhi MENGZhuorui PANSixin WENPan QIN...
    106-117页
    查看更多>>摘要：Thrust estimation is a significant part of aeroengine thrust control systems.The tradi-tional estimation methods are either low in accuracy or large in computation.To further improve the estimation effect,a thrust estimator based on Multi-layer Residual Temporal Convolutional Network(M-RTCN)is proposed.To solve the problem of dead Rectified Linear Unit(ReLU),the proposed method uses the Gaussian Error Linear Unit(GELU)activation function instead of ReLU in residual block.Then the overall architecture of the multi-layer convolutional network is adjusted by using residual connections,so that the network thrust estimation effect and memory consumption are further improved.Moreover,the comparison with seven other methods shows that the proposed method has the advantages of higher estimation accuracy and faster convergence speed.Furthermore,six neural network models are deployed in the embedded controller of the micro-turbojet engine.The Hardware-in-the-Loop(HIL)testing results demonstrate the superiority of M-RTCN in terms of estimation accuracy,memory occupation and running time.Finally,an ignition verification is conducted to confirm the expected thrust estimation and real-time perfor-mance.
      原文链接:
    • NETL
    • NSTL
    • 万方数据
    • 维普

    An interlaminar damage shell model for typical composite structures

    Jie ZHOUZhen WUZhengliang LIUXiaohui REN...
    118-137页
    查看更多>>摘要：Using the plate/shell elements in commercial software,accurate analysis of interlaminar initial damage in typical composite structures is still a challenging issue.To propose an accurate and efficient model for analysis of interlaminar initial damage,the following work is carried out:(A)A higher-order theory is firstly proposed by introducing the local Legendre polynomials,and then a novel shell element containing initial damage prediction is developed,which can directly predict transverse shear stresses without any postprocessing methods.Unknown variables at each node are independent of number of layers,so the proposed model is more efficient than the 3D-FEM.(B)Compression experiment is carried out to verify the capability of the proposed model.The results obtained from the proposed model are in good agreement with experimental data.(C)Sev-eral examples have been analyzed to further assess the capability of the proposed model by compar-ing to the 3D-FEM results.Moreover,accuracy and efficiency have been evaluated in different damage criterion by comparing with the selected models.The numerical results show that the pro-posed model can well predict the initial interlaminar damage as well as other damage.Finally,the model is implemented with UEL subroutine,so that the present approach can be readily utilized to analyze the initial damage in typical composite structures.
      原文链接:
    • NETL
    • NSTL
    • 万方数据
    • 维普

    Thermodynamic property of sandwich cylindrical shell structure with metallic wire mesh:Numerical modeling and experimental analysis

    Xin XUEGuojian SHENJuan LIAO
    138-152页
    查看更多>>摘要：As a new addition to lightweight composite structures,the sandwich cylindrical shell with a metallic wire mesh core has emerged as a promising solution for thermodynamic perfor-mance analysis at elevated temperatures.The intricate interwoven cellular formations within the metallic wire mesh pose difficulties for thermo-mechanical modeling and property evaluation.First,the constitutive models employed to characterize hysteresis phenomena were presented,comprising isotropic elasticity,Bergstrom-Boyce model,Ogden hyper-elasticity,and parameter identification through mechanical examinations at varying temperatures.Second,the finite element modeling of cylindrical shell structures was determined for modal and steady-state dynamic analyses.Third,the experimental procedures were carried out,including the preparation of the sandwich cylindrical shell and the dynamic testing platform.The first-order natural frequency of the cylindrical shell structure is close to the resonance frequency of the dynamic test results,with a maximum error of 6.5％,demonstrating the accuracy of the simulation model.When compared to the solid-core cylindrical shell,the average insertion loss of the sandwich cylindrical shell structure within the fre-quency range of 10-1000 Hz at room temperature is up to 11.09 dB.Furthermore,at elevated tem-peratures,the average insertion loss of the sandwich cylindrical shell decreases but fluctuates as the temperature changes.
      原文链接:
    • NETL
    • NSTL
    • 万方数据
    • 维普