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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。
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    Macro electrochemical milling and its hybrid variants

    Ningsong QUXiaolong FANGJunzhong ZHANGHuanghai KONG...
    1-35页
    查看更多>>摘要：Macro electromechanical milling has recently attracted increasing attention because numerous large thin-walled structures composed of difficult-to-cut materials are employed in the aerospace field.This paper reviews recent developments in state-of-the-art macro electromechanical milling.The fundamental aspects of material removal mechanisms,such as the generation and breakdown behaviors of passive oxide films of typical difficult-to-cut materials,were discussed.Rapid methods for breaking down passive films are summarized,and simulation methods for the machining process coupling multiple physical fields are introduced.Specific electrochemical milling methods,including fly mode electrochemical milling and sink electrochemical milling,are classified.Efforts made to improve process performance,such as the material removal rate,surface quality,and machining accuracy,are discussed.In addition,the main hybrid electrochemical milling meth-ods,including electrochemical discharge milling,mechano-electrochemical milling,and electro-chemical mill grinding,are also presented.
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    Non-synchronous vibration of rotor blade in a six-stage transonic compressor

    Ronghui CHENGZhuo WANGHuawei YULin DU...
    36-48页
    查看更多>>摘要：This paper presents an experimental study on the Non-Synchronous Vibration(NSV)in a six-stage transonic compressor.The first part of the paper describes the NSV phenomenon of Rotor 1,which occurs when both Stator 1(S1)and Stator 2(S2)or S1 only are closed.Detailed mea-surements and analysis are carried out for the former case through the unsteady wall pressure and the Blade Strain(BS).The spinning mode theory used in the rotor/stator interaction noise is employed to explain the relation between the circumferential wave number of the aerodynamic dis-turbance and the Nodal Diameter(ND)of the blade vibration.The variations of the vibration amplitudes of different blades and the Inter-Blade Phase Angles(IBPAs)at different moments sug-gest that the evolution of NSV is a highly nonuniform phenomenon along the circumferential direc-tion.In addition,the difference between the wall-pressure spectra generated by the NSV and the classic flutter has been discussed.In the second part,the variations of aerodynamic loading due to the adjustment of the staggers of the Inlet Guide Vane(IGV),Sl and S2 have been investigated.It is found that closing S1 only can result in a great fluctuation to the performance of the front stages,which might be detrimental to the flow organization and increase the risk of NSV.In con-trast,the effect of closing S2 only on the performance of the first two stages appears to be slighter relatively.
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    Improving flight performance of UAVs by ice shape modulation

    Jiajun ZHANGXuecheng LIUHua LIANGLike XIE...
    49-62页
    查看更多>>摘要：Aircraft icing poses a great threat to flight safety.In response to the characteristics of high-power consumption,large volume,and heavy weight of traditional anti-/de-icing technologies,the concept of ice shape modulation is proposed,which is called ice tolerant flight.Firstly,the flight performance of Unmanned Aerial Vehicle(UAV)was compared in three states:no ice,full ice,and modulated ice through flight tests.It was found that ice shape modulation has a significant improve-ment effect on the aerodynamic performance of aircraft under icing conditions.Under the three modulated ice shape conditions in this experiment,the lift coefficient of the UAV under different ice shape modulation conditions increased by 18％-33％,and the stalling angle was delayed by 3°-5°.Subsequently,the pressure distribution,streamlines in the flow field,and detached vortex dis-tribution of the UAV model in these three states were obtained through numerical simulation,to study the mechanism of ice shape modulation on the aerodynamic performance of aircraft.The sim-ulation found that the reason for the improvement of the wings effect after ice shape modulation is that the modulated area forms a leading-edge protrusion structure similar to a vortex generator.This structure prolongs the mixed flow region on the wings surface and reduces the trend of flow separation,which plays a role in increasing lift and reducing drag for UAVs under icing conditions.Finally,a reverse reachable set that can be used for unexpected state recovery is used as the defini-tion of flight safety boundaries,and an aircraft dynamics model is established to obtain flight safety boundaries for different states.Research has found that the flight safety boundary of the UAV in a no ice state is greater than that in a modulated ice state,and the safety boundary in a modulated ice state is greater than that in a full ice state.Compared with the full ice state,the flight safety bound-ary after modulation has expanded by 27.0％.The scheme of ice shape modulation can provide a basis for the flight safety of aircraft under icing conditions.
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    Complicated flow in tip flow field of a compressor tandem cascade using delayed detached eddy simulation

    Botao ZHANGXiaochen MAOBo LIUHejian WANG...
    63-78页
    查看更多>>摘要：The complex flow characteristics in the tip region of a tandem cascade with tip clearance have been calculated and analyzed using Delayed Detached Eddy Simulation(DDES).The coher-ent mechanism of the vortex structures near the blade tip was discussed,and the unsteady behaviors and features in the tip flow field were analyzed.Additionally,the interaction between the tip leakage flow and the gap jet was revealed.The results show that,compared to the datum cascade,the blade tip load of the rear blade increases while that of the front blade decreases.Unsteady fluctuations of the tandem cascade are mainly caused by the interaction between the tip leakage flow and gap jet,and by the mixing of the vortex structures,but there is no essential change in the spectrum feature of the tip leakage flow.Finally,a detailed analysis of the development of vortices in the tip region is conducted by the topological structures of the flow field.Combined with the three-dimensional vor-tex structures,the schematic diagram of the vortex system of the datum single-row cascade and tan-dem cascade is summarized.
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    A numerical simulation strategy for a compressor's underlying axisymmetric characteristic and its application in body force model

    Shijie LIUTianyu PANQiushi LI
    79-90页
    查看更多>>摘要：Accurate prediction of the aerodynamic response of a compressor under inlet distortion is crucial for next-generation civil aircraft,such as Boundary Layer Ingestion(BLI)silent aircraft.Therefore,research on the Body Force(BF)model plays a significant role in achieving this objec-tive.However,distorted inlet airflow can lead to varying operating conditions across different spa-tial locations of the compressor,which may cause some regions to operate outside the stability boundary.Consequently,the accuracy of BF model simulations might be compromised.To address this issue,this paper proposes a numerical simulation strategy for acquiring the steady axisymmetric three-dimensional flow field of a compressor operating at low mass flow rates,which is known as the Underlying Axisymmetric Pressure Rise Characteristic(UAPRC).The proposed simulation accounts for two different rotor speeds of a transonic compressor and identifies initial positions in the flow field where deterioration occurs based on prior experimental investigations.Moreover,simulation results are incorporated into the BF model to replicate hub instability observed in exper-iments.Obtained results demonstrate that this strategy provides valid predictions of the UAPRC of the compressor,thereby addressing the limitations associated with the BF model.
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    Numerical and experimental research on axial injection end-burning hybrid rocket motors with polyethylene fuel

    Xiangyu MENGHui TIANLingfei HEJingfei GAO...
    91-105页
    查看更多>>摘要：This study investigates the end-burning hybrid rocket motors with polyethylene fuel by the numerical simulation and experiment.Based on computational fluid dynamics,a numerical model is developed.The model is validated by two firing tests in this hybrid rocket motor,which uses oxygen and polyethylene as propellants.The results show that the numerical and experimental data are in good agreement,and the error of the chamber pressure is less than 2.63％.Based on the simulation mode,the blowoff limit of the end-burning hybrid rocket motors is investigated.When the nozzle throat diameter and the inner diameter of grain are large,it is more difficult for the hybrid rocket motor to achieve end-burning mode,i.e.,the flame spreading is prevented in the nar-row duct.The main reason is that when the nozzle throat and the grain port are large,chamber pressure and oxidizer flow velocity are low.Therefore,the friction velocity considering the pressure and flow velocity is proposed.The critical friction velocity is about 4.054-4.890 m/s in the hybrid rocket motors.When the friction velocity exceeds the critical friction velocity,the combustion mode in hybrid rocket motors changes from the flame spreading mode to the end-burning mode.More-over,the regression rate formula is obtained by fitting,which shows that the regression rate has a good correlation with combustion chamber pressure.The critical friction velocity and regression rate formula can provide an important reference for end-burning hybrid rocket motors.
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    Insights into thermodynamic performance of a hypersonic precooled air-breathing engine with a complicated multi-branch closed cycle

    Yifan WANGZhengping ZOUPengcheng DULichao YAO...
    106-123页
    查看更多>>摘要：An advanced precooled airbreathing engine with a closed Brayton cycle is a promising solution for high-speed propulsion,of which the Synergetic Air Breathing Rocket Engine(SABRE)is a representative configuration.The performance of the latest SABRE-4 cycle was analyzed in this paper.Firstly,a relatively complete engine performance model that considers the characteristics of turbomachinery and heat exchangers was developed.Then,Sobol'global sensitivity analysis of key performance parameters was carried out to identify the most influential design variables.Optimal specific impulses under different target specific thrusts were obtained by particle swarm optimiza-tion,of which the thermodynamic parameters corresponding to a specific thrust of 1.12 kN-s-kg-1 and a specific impulse of 3163 s were chosen as the design values.Four different control laws were analyzed in contrast,and the charge control method had the strongest ability of thrust regulation as well as maintaining a favorable specific impulse performance.Finally,working characteristics under the charge control and over a typical flight envelope were calculated,in which the average value of the maximum specific impulse was as high as 5315 s.This study would help to deepen the under-standing of SABRE-4 thermodynamic characteristics and other precooled airbreathing engine cycles with similar layouts.
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    Spray characteristics of different regions downstream of a swirl cup

    Donghui WANGYong HUANGHongzhou ZHANG
    124-143页
    查看更多>>摘要：The spray characteristics of different regions downstream of swirl cups play a critical role in cold start and re-ignition of gas turbines.The spray measurements were performed at the fuel pressures of 0.5,0.8,1.0,1.5,and 2.0 MPa and the fuel temperatures of-23,-13,-3,7,17 and 27 ℃,respectively.The droplet size,droplet velocity,droplet number,and instantaneous spatial spray image of sprays from an aviation kerosene Jet-A were measured using a two-component phase Doppler particle analyzer and a digital off-axis holography system.As the fuel pressure and temperature increase,the Sauter Mean Diameter(SMD)and spray non-uniformity of the Spray Shear Layer(SSL)gradually decrease.As the fuel pressure increases,the SMD and spray non-uniformity of the Central Toroidal Recirculation Zone(CTRZ)gradually decrease,and the slopes of these curves both decrease.As the fuel pressure increases,the SMD and spray non-uniformity of the CTRZ rapidly decrease at the fuel temperature of-23 ℃,while slightly decrease at the fuel temperature of 27 ℃.The droplets in the CTRZ come from 3 different sources:simplex nozzle,venturi,and outside the CTRZ.As the fuel pressure increases,the proportion of droplets recirculated from outside the CTRZ decreases.This study proposed the concept of the"pressure critical point"for the swirl cups.As the fuel temperature decreases,the proportion of droplets recir-culated from outside the CTRZ increases below the critical pressure,while decreases above the crit-ical pressure.In addition,through the models of liquid film formation and breakup on the curved cylindrical wall,a semi-theoretical model was established to predict the SMD of SSL for swirl cups.The prediction uncertainty of this model is less than 6％for all 14 conditions in this paper.
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    Unsteady aerodynamic noise prediction of contra-rotating open rotor using meshless method

    Zhiliang HONGMeng SUHaitao ZHANGZerui XU...
    144-165页
    查看更多>>摘要：The Contra-Rotating Open Rotor(CROR)design confronts significant noise challenges despite being one of the possible options for future green aeroengines.To efficiently estimate the noise emitted from a CROR,a three-dimensional unsteady prediction model based on the meshless method is presented.The unsteady wake flow and the aerodynamic load fluctuations on the blade are solved through the viscous vortex particle method,the blade element momentum theory and vortex lattice method.Then,the acoustic field is obtained through the Farassat's formulation 1A.Validation of this method is conducted on a CROR,and a mesh-based method,e.g.,Nonlinear Harmonic(NLH)method,is also employed for comparison.It is found that the presented method is three times faster than NLH method while maintaining a comparable precision.A thorough para-metric analysis is also carried out to illustrate the effects of rotational speed,rotor-rotor spacing and rear rotor diameter on the noise level.The rotor speed is found to be the most influencing fac-tor,and by optimizing the speed difference between the front and rear rotors,a notable noise reduc-tion can be expected.The current findings not only contribute to a deeper comprehension of the CROR's aeroacoustic properties but also offer an effective tool for engineering applications.
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    Design-space adaptation method for multiobjective and multidisciplinary optimization

    Jongho JUNGKwanjung YEEShinkyu JEONG
    166-189页
    查看更多>>摘要：This paper developed a new method that adaptively adjusts a design space by considering the actual solution distribution of a problem to overcome the conventional design-space adaptation method that assumes the solutions distribution to be a normal distribution because the distributions of solutions are rarely normal distributions for real-world problems.The developed method was applied to nineteen multiobjective test functions that are widely used to evaluate the characteristics and performance of optimization approaches.The results showed that this method adapted the design space to an appropriate design space where the solution existence probability was high.The optimization performance achieved using the developed method was higher than that of the conventional methods.Furthermore,the developed method was applied to the conceptual design of an unmanned spacecraft to confirm its validity in real-world design and multidisciplinary-optimization problems.The results showed that the Pareto solutions of the developed method were superior to those of conventional methods.Additionally,the optimization efficiency with the devel-oped method was improved by more than 1.4 times over that of the conventional methods.In this regard,the developed method has the potential to be applied to complicated real-world optimiza-tion problems to achieve better performance and efficiency.
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