2011, 2(1):1-11.
Abstract:As the topology optimization of continuum structure can produce new configurations during the optimization,it is significant for automatic structure design.At present,the most commonly used topology optimization methods of continuum structure are: the homogenization method,variable thickness method,variable density method,evolutionary structural optimization method,level set method,independent continuous mapping method.Firstly,the development processes of above methods are systematically reviewed,their curr...
Yan Zhijiang , Liu Peiqing , Duan Huishen , Liu Jie
2011, 2(1):12-18.
Abstract:Combining the characteristics of three-dimensional laminar flow induced by single perforation suction,in this paper,boundary layer of a three-dimensional laminar flow induced by a row of perforations suction is simulated by using Fluent as numerical solver.The effect of different perforation spacing and suction parameters on flow field structure is then studied.The final results show that a vertical vortex pair will interact and come into being periodic shedding horseshoe-shape vortex when the perforation s...
Hu Handong , Yang Qide , Zhu Minghong , Deng Xueying
2011, 2(1):19-26.
Abstract:In the real flight and wind tunnel testing of aircraft configuration with pointed nose slender,the coefficients of side force and yawing moment which are generated by high angle of attack are inconsistency,leading to difficulty for analyzing and using.In order to remove this difficulty,an experimental technique in which a micro-perturbation is attached on nose tip of model is suggested in wind tunnel testing for measuring side force and yawing moment.Based on this technique,an experimental study was conduct...
Liu Feng , Luo Jiaqi , Cai Jinsheng
2011, 2(1):27-36.
Abstract:Reduction of flow loss in turbo-machinery is significant for improving the performance of turbine blades in design of aviation turbine blade.In this paper,the application of a continuous viscous adjoint equation method to the aerodynamic design optimization of a low aspect-ratio turbine blade to reduce the secondary flow loss through endwall profiles contouring is presented.Firstly,an inverse design case is performed to achieve a given flow turning distribution at the outlet through re-staggering the blade ...
2011, 2(1):37-42.
Abstract:The emergency evacuation slide system of civil aircraft will ensure rapid and effective occupant evacuation in the event of emergency with a minimum probability of incurring injury.The slide system will affect life safety of occupant of aircraft directly,it is indispensability important system.There is one regional aircraft has simply slide system in our country,for big civil aircraft,because of the aircraft structure is high,the passenger door is high,the off-wing emergency door is high,and occupants is mo...
Zhang Wei , Guo Qing , Zhang Yizhe
2011, 2(1):43-47.
Abstract:Subscale model flight test technique is an important part of flight test technology,guiding many aspects of research and development for modern aircraft design as effectively technique approaches,such as new concept aircraft layout,control system application,propulsion mechanism,and so on.In this paper the key points of flight test system utilized in dynamically-scaled vehicles that enable the application of subscale flight test results to full scale vehicles are described,and then,the group research works ...
2011, 2(1):48-55.
Abstract:The technologies of loitering munitions,which is a new kind of UAV,have been paid more and more attention in domestic and overseas. In this paper,the distinguishing feature,working mechanism and the classification of loitering munitions of a new UAV are introduced at first.Its technique,including integrated design technique,equipment opposing high acceleration technique,the technique of decreasing rotating and increasing stability,dynamic response of morphing procedure,warhead technology and so on,are analy...
Yuan He , Jiang Shenglin , Zhang Guangzu
2011, 2(1):56-60.
Abstract:Icing is one of the major sources of flight accidents,which therefore needs to be removed from the aircrafts.Among various de-icing systems,electric-expulsive approach removes ice by the electro magnetic repulsion force,which is featured by its low power consumption,high efficiency,less influence to flight stability,as well as flexible installation.With ANSYS simulator and based on magnetic-vector finite element method(FEM),the FEM models for the single component is built in this paper.The effect of the rep...
Zhang Bin , Zhan Hao , Zhu Jun
2011, 2(1):61-65.
Abstract:High lift device design is a very important task in aircraft design.In this paper,based on the multi-block grid,two turbulence models(SST Fully turbulent and SST Gamma Theta model) are used for numerical simulation of three-dimensional high lift device to study the characteristic of aerodynamic and flow filed,and the applicability of the different turbulence model is studied by comparing the numerical simulation results with wind tunnel experimental results.
2011, 2(1):66-69.
Abstract:In this paper,focusing on the characteristics of coastal and offshore environment,analyzing the reason of aircraft's structure corrosion and fatigue damage,as well as the problem of present prevention and control measures. The establishment of the quaternary closed-loop control system of aircraft design and manufacture department-equipped department-research institute-fleet maintenance group is suggested.The enhanced measures should be taken and all factors should be considered by all participants in order ...
2011, 2(1):70-77.
Abstract:The flight safety will be greatly improved if crashworthiness is considered in the aircraft conceptual design stage.The progress made in crashworthiness on aircraft structures,including the research method and testing method in our country and abroad is briefly reviewed in this paper.It is emphasized on the simulation method and optimization design.The multi-objective crashworthiness optimization is presented.
Li Shanshan , Xing Lingge , Ding Huiliang , Duan Shihui
2011, 2(1):78-83.
Abstract:A method for design optimization considering damage tolerance requirements in the aircraft structure preliminary design process is introduced.Firstly,damage tolerance design requirements are defined by fatigue stress allowables and applied in the preliminary design optimization as new design constraints.Then,the global/local finite element approach is used to consider the local fatigue requirements in the global design optimization.A new strength criterion for design life requirements is provided through fa...
2011, 2(1):84-88.
Abstract:Morphing aircraft can change shape and size substantially in-flight to enable a single vehicle to perform multiple mission roles.The majority of shape change occurs in the wing resulting in a wide variety of changes in aerodynamic and structural features.The transmission instrument of the folding wing resolves special design,because the structure dynamics and transmission feature of folding wing will vary in motion.In this paper,a novel transmission instrument was designed using shaft and shaft sleeve,whose...
2011, 2(1):89-92.
Abstract:In this paper,the structural non-probabilistic reliability model based on fragment description is introduced to fracture structure reliability analysis.Combining the fracture criterion and fragment description,the non-probabilistic fracture mechanics analysis is realized.The limitation of probabilistic fracture mechanics in solving the problem of small sample is overcome.The over conservation of interval uniform distribution for unascertained information is also overcome.The reliability problem of fracture ...
Bo Xiangfeng , Liu Bo , Xiang Xiaorong , Wang Qingwei , Cao Zhiyuan
2011, 2(1):93-99.
Abstract:In this paper,the measure method is different from traditional method.Using the total pressure probe,the real total pressures in the boundary layer of cascade blade surface are measured.The flow Mach number is changed in the experiment.Some parameters about the boundary thickness are calculated.The purpose of the experiment is to examine the influence of the inlet flow conditions on the boundary layer of cascade blade surface.The experiment results indicate that the influence of the incidence on the boundar...
Zhu Yangli , Zhang Hualiang , Chen Haisheng , Tan Chunqing
2011, 2(1):100-104.
Abstract:Aeroengine modification for ground application is analyzed in this paper.Several technical schemes are presented first.The method of install power turbine after blending directly is implemented on the basic of entire thermodynamics calculation for specific turbofan engine.Full-3d numerical simulation of newly designed power turbine shows good performance.Moreover,modification of three other typical aeroengines are studied,which indicates that retired aeroengines could satisfy power generation and output dev...
Gao Guangliang , Niu Nan , Wang Yangang
2011, 2(1):105-109.
Abstract:The NASA Rotor35 with boundary layer suction(BLS) at blade suction surface and end-wall is investigated by numerical simulation to explore a better combination suction distribution to control the flow structure and performance of this transonic compressor rotor.The results show that: The performance of compressor is improved by the four combination suction with vary suction flow rate.Compared with the blade surface suction and end-wall suction,combination suction can obtain larger positive effect at higher ...
Wei chao , Yang Weidong , Mao Genwang
2011, 2(1):110-114.
Abstract:The polymer-gelation gel propellant is considered to be a very prospective gel propellant.The study of its rheological property is of great importance,and is the foundation and key to the application of gel propellant in propulsion technology.In this paper rheological behavior of a polymer-gelation gel propellant is studied experimentally by means of rheometer test and round-pipe flowing test respectively.A rheological model is developed on the basis of experimental measurements and the power law assumption...
Li Yonghong , Liu Cunliang , Zhu Huiren
2011, 2(1):115-121.
Abstract:Numerical simulation is carried out to investigate the film cooling mechanism of two converging-expanding holes with different exit-entry area ratios.The Realizable turbulence model with enhanced wall function is used.Results show that as the features of the flow fields and the temperature fields in the two holes are similar with each other,the distribution features of the film cooling effectiveness and the heat transfer coefficient of the two holes are also very similar.However,the cooling effectiveness of...
Liang Shuanggang , Xu Jiadong , Huo Yanning , Zhao Qian
2011, 2(1):122-126.
Abstract:A hybrid mode tune method is proposed on the base of the direct illumination and standard mode tune method.The tuner is rotating step by step while the transmit antennas illuminate the test region,and the max values of the field strength satisfy the field uniformity limit.According to the chamber calibration by three different ways,the experimental data is analyzed,and the feasibility of the hybrid mode tune is proved.