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Chinese Journal of Aeronautics 2015年第1期28卷 152-163页

作者： Tian Yongliang Liu Hu Yin Jiao Luo Mingqiang Wu Guanghui School of Aeronautic Science and Engineering Beihang University Chengdu aircraft Design Institute commercial aircraft corporation of china ltd.

Simulation-based training is a promising way to train a carrier flight deck crew because of the complex and dangerous working environment. Quantitative evaluation of simulation-based training quality is vital to make simulation-based training practical for aircraft carrier *** paper develops a personal computer-based aircraft carrier marshalling simulation system and a cave automatic virtual environment（CAVE）-based immersive environment. In order to compare the training effectiveness of simulation-based training and paper-based training, a learning cubic model is proposed and a contrast experiment is carried out as well. The experimental data is analyzed based on a simplified Kirkpatrick＇s model. The results show that simulation-based training is better than paper-based training by 26.80% after three rounds of testing, which prove the effectiveness of simulation-based aircraft carrier marshalling training.

关键词： aircraft cubic dangerous simplified questionnaire vital train deviation pyramid judge

Blade containment evaluation of civil aircraft engines

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Chinese Journal of Aeronautics 2013年第1期26卷 9-16页

作者： Yang Bin Aeronautical Science & Technology Research Institute of commercial aircraft corporation of china

The potential hazard resulting from uncontained turbine engine rotor blade failure has always been the long-term concern of each aero engine manufacturer, and to fully contain the failed blades under critical operating conditions is also one of the most important considerations to meet the rotor integrity requirements. Usually, there are many factors involving the engine containment capability which need to be reviewed during the engine design phases, such as case thickness, rotor support structure, blade weight and shape, etc. However, the premier method to demonstrate the engine containment capability is the fan blade-off test and margin of safety （MS） analysis. Based on a concrete engine model, this paper aims to explain the key points of aero engine containment requirements in FAR Part 33, and introduces the implementation of MS analysis and fan blade-off test in the engine airworthiness certification. Through the introduction, it would be greatly helpful to the industrial community to evaluate the engine containment capability and prepare the final test demonstration in engine certification procedure.

关键词： Airworthiness Engine containment Fan blade-off Margin of safety analysis Method of compliance

Microstructure and properties of an Al–Ti–Cu–Si brazing alloy for SiC–metal joining

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International Journal of Minerals,Metallurgy and Materials 2017年第5期24卷 557-565页

作者： Chun-duo Dai Rui-na Ma Wei Wang Xiao-ming Cao Yan Yu School of Materials Science and Engineering Hebei University of Technology commercial aircraft corporation of china Ltd.

An Al–Ti–Cu–Si solid–liquid dual-phase alloy that exhibits good wettability and appropriate interfacial reaction with SiC at 500–600°C was designed for SiC–metal joining. The microstructure, phases, differential thermal curves, and high-temperature wetting behavior of the alloy were analyzed using scanning electron microscopy, X-ray diffraction analysis, differential scanning calorimetry, and the sessile drop method. The experimental results show that the 76.5Al–8.5Ti–5Cu–10Si alloy is mainly composed of Al–Al2Cu and Al–Si hypoeutectic low-melting-point microstructures (493–586°C) and the high-melting-point intermetallic compound AlTiSi (840°C). The contact angle, determined by high-temperature wetting experiments, is approximately 54°. Furthermore, the wetting interface is smooth and contains no obvious defects. Metallurgical bonding at the interface is attributable to the reaction between Al and Si in the alloy and ceramic, respectively. The formation of the brittle Al4C3phase at the interface is suppressed by the addition of 10wt% Si to the alloy. © 2017, University of Science and Technology Beijing and Springer-Verlag Berlin Heidelberg.

关键词： Alloys Aluminum copper alloys Ceramic materials Differential scanning calorimetry Intermetallics Joining Melting point Metals Microstructure Scanning electron microscopy Silicon Silicon alloys Silicon carbide Soldering alloys Titanium alloys Wetting X ray diffraction analysis

Assessment on critical technologies for conceptual design of blended-wing-body civil aircraft

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Chinese Journal of Aeronautics 2019年第8期32卷 1797-1827,1794页

作者： Zhenli CHEN Minghui ZHANG Yingchun CHEN Weimin SANG Zhaoguang TAN Dong LI Binqian ZHANG School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China Shanghai aircraft Design and Research Institute Commercial Aircraft Corporation of China LtdShanghai 201210China

Civil aviation faces great challenges because of its robust projected future growth and potential adverse environmental effects. The classical Tube-And-Wing(TAW) configuration following the Cayley’s design principles has been optimized to the architecture’s limit, which can hardly satisfy the further requirements on green aviation. By past decades’ investigations the BlendedWing-Body(BWB) concept has emerged as a potential solution, which can simultaneously fulfill metrics of noise, emission and fuel burn. The purpose of the present work is to analyze the developments of critical technologies for BWB conceptual design from a historical perspective of technology progress. It was found that the high aerodynamic efficiency of BWB aircraft can be well scaled by the mean aerodynamic chord and wetted aspect ratio, and should be realized with the trade-offs among stability and control and low-speed performance. The structure concepts of non-cylinder pressurized cabin are of high risks on weight prediction and weight penalty. A static stability criterion is recommended and further clear and adequate criteria are required by the evaluations of flying and handling qualities. The difficulties of propulsion and airframe integration are analyzed. The energy to revenue work ratios of well-developed BWB configurations are compared,which are 31.5% and 40% better than that of TAW, using state-of-art engine technology and future engine technology, respectively. Finally, further study aspects are advocated.

关键词： Aerodynamic design Bended-wing-body Propulsion Airframe Integration Stability and control Structure

Consideration on aircraft tire spray when running on wet runways

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Chinese Journal of Aeronautics 2020年第2期33卷 520-528页

作者： Xianpeng ZHANG Fei XU Xuanqi REN Xiangyang GAO Rengang CAO School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China commercial aircraft corporation of china Ltd.Shanghai 200126China

The tire spray produced by aircraft running on wet runways may enter the intake of engines,which may lead to the compressor stall,surge,or even combustion ***,it is necessary to do some research work on the tire spray to help to solve this ***,the mechanism of tire spray is analyzed,and some parameters are defined to describe the spray ***,the numerical model of tire spray is established by coupled Smoothed Particle Hydrodynamics(SPH)and Finite Element Method(FEM)in LS-DYNA software,and the model is validated by a simplified water spray *** some influence factors on the spray pattern are studied by numerical ***,some suggestions are proposed on different types of aircraft to avoid too much tire spray being ingested into the engine intakes.

关键词： aircraft tires Engine ingestion SPH Spray pattern Wet runway

Nacelle-airframe integration design method for blended-wing-body transport with podded engines

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Chinese Journal of Aeronautics 2019年第8期32卷 1860-1868页

作者： Zhenqing XIN Zhenli CHEN Wenting GU Gang WANG Zhaoguang TAN Dong LI Binqian ZHANG School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China Shanghai aircraft Design and Research Institute Commercial Aircraft Corporation of ChinaLtd.Shanghai 200232China

Strong shock waves and flow separation often occur during the integration of nacelle and airframe for blended-wing-bodies with podded engines. To address this problem, this paper presents an integration method with numerical simulations. The philosophy of channeling flow and avoiding the throat effect on the nacelle and airframe is established based on the analysis of flow interference in the initial configuration. A parametric integration design method is proposed from twodimensional plane to three-dimensional space with control mechanisms and selection principles of the key parameters determined by their influences. Results show that strong shock waves and flow separation can be successfully eliminated under the influence of both the reshaped channel and decelerated inflow below the nacelle. Supersonic regions around the nacelle are effectively reduced, concentrating mainly on the lip position. Thus, a significant cruise drag reduction(8.7%) is achieved though the pressure drag of the nacelle increases.

关键词： Blended-wing-body Computational fluid dynamics Drag reduction Flow interference Nacelle-airframe integration

Effects of stability margin and thrust specific fuel consumption constrains on multi-disciplinary optimization for blended-wing-body design

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Chinese Journal of Aeronautics 2019年第8期32卷 1847-1859页

作者： Minghui ZHANG Zhenli CHEN Zhaoguang TAN Wenting GU Dong LI Changsheng YUAN Binqian ZHANG School of Aeronautics Northwestern Polytechnical UniversityXi’an 710072China Shanghai aircraft Design and Research Institute Commercial Aircraft Corporation of ChinaLtd.Shanghai 200232China

Blended-Wing-Body(BWB) configuration, as an innovative transport concept, has become a worldwide research focus in the field of civil transports development. Relative to the conventional Tube-And-Wing(TAW) configuration, the BWB shows integrated benefits and serves as a most promising candidate for future ‘‘green aviation'. The objective of the present work is to figure out the effects of the stability margin and Thrust Specific Fuel Consumption(TSFC) on the BWB design in the framework of Multi-Disciplinary Optimization(MDO). A physically-based platform was promoted to study the effect static stability margin and engine technology level. Low-order physically based models are applied to the evaluation of the weight and the aerodynamic performance. The modules and methods are illustrated in detail, and the validation of the methods shows feasibility and confidence for the conceptual design of BWB aircrafts. In order to find out the relation between planform changes and the selection of stability and engine technology level, two sets of optimizations are conducted separately. The study proves that these two factors have dominant effects towards the optimized BWB designs in both aerodynamic shapes, weight distribution, which needs to be considered during the MDO design process. A balance diagram analysis is applied to find out a reasonable static stability margin range. It can be concluded that a recommended stability margin of a practical BWB commercial aircraft can be half of that of a conventional TAW design.

关键词： Aerodynamic design Blended-wing-body Multi-disciplinary optimization Optimization design Thrust specific fuel consumption

Effective control allocation using hierarchical multi-objective optimization for multi-phase flight

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Chinese Journal of Aeronautics 2020年第7期33卷 2002-2013页

作者： Liguo SUN Qing ZHOU Baoxu JIA Wenqian TAN Hangxu LI School of Aeronautic Science and Engineering Beihang UniversityBeijing 100083China Shanghai aircraft Design and Research Institute Commercial Aircraft Corporation of China Ltd.Shanghai 201210China

For different flight phases in an overall flight mission,different control and allocation preferences should be pursued considering lift,drag or maneuverability *** multi-objective flight control allocation problem for a multi-phase flight mission is *** an overall flight mission,different flight phases namely climbing,cruise,maneuver and gliding phases are ***,a multi-objective control allocation problem considering drag,lift or control energy preference is ***,considering different control preferences at different flight phases,the analytic hierarchical process method is used to construct a comprehensive performance index from different objectives such as lift or drag *** active set based dynamic programming optimization method is used to solve the real-time optimization *** the validation,the Innovative Control Effector(ICE)tailless aircraft nonlinear model and the angular acceleration measurements based adaptive Incremental Backstepping(IBKS)are used to construct the validation ***,an overall flight mission is simulated to demonstrate the efficiency of the proposed multi-phase and multi-objective flight control allocation *** results show that the comprehensive performance index for different phases,which are determined from the Analytic Hierarchy Process(AHP)method,can suitably satisfy the preference requirements for different flight phases.

关键词： Adaptive control Control allocation Flying-wing aircraft Multi-phase and multi-objective Real-time optimization

Aerodynamic Design Methodology for Blended Wing Body Transport

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Chinese Journal of Aeronautics 2012年第4期25卷 508-516页

作者： LI Peifeng ZHANG Binqian CHEN Yingchun YUAN Changsheng LIN Yu College of Aeronautics Northwestern Polytechnical University Xi 'an 710072 China Shanghai aircraft Design and Research lnstitute Commercial Aircraft Corporation of China Ltd. Shanghai200232 China

This paper puts forward a design idea for blended wing body（BWB）.The idea is described as that cruise point,maximum lift to drag point and pitch trim point are in the same flight *** to this design idea,design objectives and constraints are *** applying low and high fidelity aerodynamic analysis tools,BWB aerodynamic design methodology is established by the combination of optimization design and inverse design *** lift to drag ratio,pitch trim and acceptable buffet margin can be achieved by this design *** 300-passenger BWB configuration based on static stability design,as compared with initial configuration,the maximum lift to drag ratio and pitch trim are achieved at cruise condition,zero lift pitching moment is positive,and buffet characteristics is *** burn of 300-passenger BWB configuration is also significantly reduced as compared with conventional civil *** aerodynamic design is carried out under the constraints of BWB design requirements,the design configuration fulfills the demands for interior layout and provides a solid foundation for continuous work.

关键词： blended wing body aerodynamic configurations computational fluid dynamics optimization design inverse design

Experimental Analysis of A Cooling System for Wind-Driven Generator Stator

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Transactions of Nanjing University of Aeronautics and Astronautics 2016年第2期33卷 180-186页

作者： Qian Xiaohui Jiang Yanlong Cheng Danfeng Liu Juan College of Aerospace Engineering Nanjing University of Aeronautics & Astronautics Shanghai aircraft Design & Research Institute Commercial Aircraft Corporation of ChinaLtd

A novel cooling system with cooling channels is proposed for the stator of 3MW wind-driven *** experimental platform is built to investigate the performance of the cooling system with different ***30%,50% or 80% generator loads,the temperatures meet the design ***,it is a little over the requirement at 100%load,duo to experimental errors and some unknown thermal *** the test at 100%load,the developing trends of the parameters of these two generators are similar and only minor differences occurs when they reach steady state our work can be benefit for the design and improvement of MW wind-driven generator cooling solutions.

关键词： wind-driven generator stator cooling channels cooling method, experimental study