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Stability characteristics and airworthiness requirements of blended wing body aircraft with podded engines

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Chinese Journal of Aeronautics 2022年第6期35卷 77-86页

作者： Lixin WANG Ning ZHANG Hailiang LIU Ting YUE School of Aeronautics Science and Engineering Beihang UniversityBeijing 100083China

Blended-Wing-Body(BWB)aircraft have a relatively short fuselage and no horizontal tail,and they usually adopt podded engines and a V tail instead of a vertical ***,BWB aircraft have decreased longitudinal and directional static stability and *** this paper,the three-axis static and dynamic stability characteristics of an example BWB aircraft with podded engines are *** to the differences in flight characteristics of BWB aircraft and conventional aircraft,the different airworthiness requirements for BWB aircraft are analyzed:first,based on current airworthiness regulations and transport aircraft flying quality specification,the relaxation requirement of longitudinal static stability for BWB aircraft is studied;second,the influences of podded engines on longitudinal trim,attitude and trajectory responses and maximum directional control power requirement of BWB aircraft are analyzed;third,the changes in the proportional relationships between the takeoff characteristic speeds of the example BWB aircraft are *** view of these variations in directional control power requirement and relationships between takeoff characteristic speeds,new recommendations for airworthiness evaluation are proposed for BWB *** conclusions of this paper are helpful references for configuration design,flight control law design and airworthiness evaluation of BWB aircraft.

关键词： airworthiness Blended wing body Podded engine Relaxed static stability Stability characteristics

airworthiness engineering and practices of COMAC C919 airplane

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Aerospace Traffic and Safety 2024年第1期1卷 20-26页

作者： Yuerang Zhao Commercial Aircraft Corporation of China Ltd.Shanghai 200126China

This paper systematically summarizes the basic philosophy and principles of airworthiness that COMAC follows in the process of developing C919 large passenger *** carries out type certification along with the aircraft development process,and plans and implements compliance activities for airplane design *** the airworthiness requirements,COMAC has also established an airworthiness management system,including design assurance system and continuing airworthiness system,to ensure that aircraft are designed in accordance with airworthiness requirements,to show compliance with airworthiness requirements and to continuously ensure the airworthiness of airplane by dealing with continuing airworthiness events in service.

关键词： Commercial Aircraft Corporation of China,Ltd.(COMAC) C919 airplane airworthiness

Optimization of Continuous airworthiness Problems

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Journal of Traffic and Transportation Engineering 2018年第6期6卷 292-301页

作者： Qusay Hassan Kamila kustroń Marek Jaszczur Mazin Ajaweed AGH University of Science and Technology Faculty of Energy and FuelsPoland University of Diyala Department of Mechanical EngineeringIraq Warsaw University of Technology Faculty of Power and Aeronautical EngineeringPoland Baghdad University of Technology Department of Control Systems EngineeringIraq

Recently aviation accident data shows that many fatal accidents in aviation are due to airworthiness issues despite the fact that all civil and private aircraft are required to comply with the airworthiness standards set by their national airworthiness *** paper presents a unique approach to continuous airworthiness problems optimization needed to reduce the risk associated with the gap between aircraft designers&manufacturing organization and continuing airworthiness(state of civil aviation authority and air operators).As a result of the paper summarizes these problems and searching of the possible solutions to be optimized,these problems are achieved to get more integration between(designers&manufacturing and air operators),finally the recommendations are drawn to address the safe operation of the aircraft and can be given to the International Civil Aviation Organization(ICAO),Federal Aviation Administration(FAA)and European Aviation Safety Agency(EASA)and Civil Aviation Authorities(CAAs)for more integration between all of them structure.

关键词： airworthiness optimization aviation safety

Optimization of Continuous airworthiness Problems

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Journal of Traffic and Transportation Engineering 2023年第3期11卷 121-130页

作者： Qusay Hassan Department of Mechanical Engineering University of DiyalaIraq

Recently aviation accident data shows that many fatal accidents in aviation are due to airworthiness issues despite the fact that all civil and private aircraft are required to comply with the airworthiness standards set by their national airworthiness *** paper presents a unique approach to continuous airworthiness problems optimization needed to reduce the risk associated by the gap between aircraft designers&manufacturing organization and continuing airworthiness(state of civil aviation authority and air operators).As a result of the paper summaries these problems and searching of the possible solutions to optimized,these problems are achieved to get more integration between(designers&manufacturing and air operators),finally there is recommendations are drawn to address the safe operation of the aircraft and can be given to the International Civil Aviation Organization(ICAO),Federal Aviation Administration(FAA)and European Aviation Safety Agency(EASA)and Civil Aviation Authorities(CAAs)for more integrate between all of them structure.

关键词： airworthiness aircraft accident aviation safety

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

Sensitivity Analysis for Safety Design Verification of General Aviation Reciprocating Aircraft Engine

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Chinese Journal of Aeronautics 2012年第5期25卷 675-680页

作者： CAO Jiaokun DING Shuiting airworthiness Technologies Research Center Beihang UniversityBeijing 100191China

This paper presents an application of global sensitivity analysis for system safety analysis of reciprocating aircraft engine. Compared with local sensitivity analysis results, global sensitivity analysis could provide more information on parameter inter- actions, which are significant in complex system safety analysis. First, a deterministic aviation reciprocating engine thermody- namics model is developed and parameters of interest are defined as random variables. Then, samples are generated by Monte Carlo method for the parameters used in engine model on the basis of definition of factor distribution. Eventually, results from engine model are generated and importance indices are calculated. Based on the analysis results, design is improved to satisfy the airworthiness requirements. The results reveal that by using global sensitivity analysis, the parameters could be ranked with respect to their importance, including first order indices and total sensitivity indices. By reducing the uncertainty of parameters and adjusting the range of inputs, safety criteria would be satisfied.

关键词： sensitivity analysis safety analysis airworthiness reciprocating aircraft engine design verification

Numerical simulation of a UAV impacting engine fan blades

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Chinese Journal of Aeronautics 2021年第10期34卷 177-190页

作者： Jingyu YU Bingjin LI Jun LIU Naidan HOU Yingchun ZHANG Yafeng WANG Yulong LI School of Aeronautics Northwestern Poly technical UniversityXi'an 710072China Science and Technology on Reactor System Design Technology Laboratory Nuclear Power Institute of ChinaChengdu 610213China Shanghai Aircraft airworthiness Certification Center of CAAC Shanghai 200335China China Aircraft Strength Research Institute Xi'an 710065China

A 3D digital model of a small Unmanned Aerial Vehicle(UAV)is obtained by using the method of scanning reverse modeling and joint mapping.A numerical simulation of a small UAV strikes on rotary engine blades,presented in this paper,was performed with a Transient Nonlinear Finite Element code PAM-CRASH software.A test of motor strike on plate was developed and the dynamic response of the plate were obtained to validate the numerical simulation method of a UAV strike on *** on this,dynamic damage response caused by UAV on the engine blades were *** is indicated that the impact process between the UAV and a single blade can be divided into two typical stages:cutting and *** mainly leads to the failure of the leading edge material,and impact mainly leads to the plastic deformation of the *** the same time,it is compared with the damage impacted by bird with the same *** the same mass of bird and UAV,the damage caused by UAV striking fan blade is more serious,and 1.345 kg UAV striking fan blade of typical civil aviation engine is enough to cause damage to flight safety.

关键词： airworthiness Bird impact Engine fan blade Explicit dynamics UAV

Failure Assessment of Aero-engine Support Structure due to Blade-off

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Transactions of Nanjing University of Aeronautics and Astronautics 2018年第5期35卷 838-848页

作者： Liu Shuangli Chen Wei Chen Minghao College of Energy and Power Engineering Nanjing University of Aeronautics and Astronautics Nanjing 210016P.R.China The 28th Research Institute of China Electronics Technology Group Corporation Nanjing 210007P.R.China

Aero-engine blade-off event could cause serious malfunction and endanger flight safety,which is an important issue widely concerned for a long *** paper presents a comprehensive review on the regulation requirements,the major research methods and status at home and ***,the relevant certification regulations and standards about aero-engine structure safety due to blade-off event were overviewed and the research gaps between the abroad and the domestic were ***,the simulation and experimental methodologies on aero-engine supporting structures undertake abnormal load due to blade-off event were discussed as major ***,the safety certification verification technology system for aero-engine support structures during blade-off event was proposed.

关键词： aero-engine blade-off airworthiness certification standard support structure failure analysis safety assessment

TEST AND CONTROL SYSTEM DEVELOPMENT AND APPLICATION OF LANDING GEAR DROP TEST RIG

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Transactions of Nanjing University of Aeronautics and Astronautics 2011年第2期28卷 145-151页

作者：薛彩军戚文刚聂宏南京航空航天大学航空宇航学院

A control and test system of a landing gear drop test rig is developed considering the drop test specifica- tions for the ＂Seagull 300＂ multi-functional amphibious airplane. In order to realize the automation of drop test process, a servo system is proposed and programmable logic controller（PLC） technology is used. Several key technologies for measuring the horizontal load, the vertical load and the transient rotational speed are studied. According to the requirements of CCAR-23-R3, the drop test of landing gears of the ＂Seagull 300＂ airplane is accomplished. Test results show that the system has a high accuracy of data collection. The system is stable and reliable. The drop test satisfies the requirements of the drop test specifications and the results can be used as the certification of airworthiness for this kind of airplane.

关键词： drop test test and control system airworthiness landing gears