CONFERENCE PROGRAM

December 29-31, 2017, Yokohama, Japan

2017 Asia Conference on Mechanical and Aerospace

Engineering

(ACMAE 2017)

Workshop International Conference on Navigation and Communication Systems

(ICNCS 2017)

Organized by:

Supported by:

Published by:

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Dear Researcher,

The Asia Conference on Mechanical and Aerospace Engineering ACMAE 2017 is a sister

conference of ICMAE that has been running for many years and attracts many delegates (over 250

in 2017). The ACMAE 2017 is the first in its conference series and was started by popular demand

to meet those in Asia, which are wishing to attend local events. That does not mean only local

attendees, there will be researchers from America and Europe and more.

As the sister conference, it’s a good platform for academics, PhD students, researchers and

industrialist who want to publish their successful research and disseminate the findings to the wider

community. We particularly welcome junior researchers starting their careers and support them in

their development. For those who wish to present a poster we have a robust system that incorporates

these into the schedule. It allows for discussion and comparisons of work. Posters are the first stage

in publishing for researchers and what a better way to build confidence and make connections in

your research area.

If you just want to attend and listen, it is supported and at a reduced fee. Your inputs in sessions and

asking questions will be encouraged.

A full paper is encouraged. It will be double-blind review to ensure quality and the proceedings are

supported by MATEC Web of Conferences Proceedings (ISSN: 2261-236X). Our acceptance rate is

based on quantity not numbers. The quality can be seen in the range of expertise on the committee

and reviewers that come from some of the most prestigious universities.

The papers accepted will be presented and the time allowed for questions to highlight the

importance of the research. Sessions are chaired by experienced professors to ensure each presenter

is supported fully both academically and practically.

The submission dates and acceptances are efficient and please feedback if changes are needed.These

will be directed and specific. All accepted papers are encouraged to be revised for submission and

we will gladly help and encourage. If you have any questions please ask and mail as we are here to

help.

I personally look forward to meeting you in person.

Professor Ian R.McAndrew PhD FRAeS

Embry Riddle Aeronautical University - Florida -Arizona-Worldwide

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Conference Chair

Prof.Yoshifumi Yokoi, National Defense Academy of Japan, Japan

Conference Co-Chair

Prof. Ian McAndrew, Embry Riddle Aeronautical University, UK

Program Co-Chairs

Prof. Kenji Uchiyama, Nihon University, Japan

Prof. Nam Seo Goo, Konkuk University, Korea

Prof. Shiyin Qin, Beihang University, China

Steering Co-chairs

Prof. Simon Barrans, University of Huddersfield, United Kingdom

Prof. Ibrahim Ozkol, Istanbul Technical University, Turkey

Publication Chair

Prof. Renfu Li, Huazhong University of Science and Technology, China

International Publicity Co-chairs

Prof. Elena Vishnevskaya, Embry Riddle Aeronautical University, Germany

Prof. Peter Monka, TU Kosice, Faculty of manufacturing technologies, Slovakia

Technical Program Members

Prof. Ming-Liang Liao, Air Force Institute of Technology, Taiwan

Prof. Shariq Neshat Akhtar, University of Leeds, UK

Prof. Krishnakumar Shankar, Australian Defence Force Academy, Australia

Prof. Saijal Kizhakke Kodakkattu, Government Engineering College Kozhikode,

India

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Prof. Mohd Na'Im Abdullah, Universiti Putra Malaysia, Malaysia

Prof. D Ison, Embry-Riddle Aeronautical University, Worldwide

Dr. Balint Vanek, MTA SZTAKI. Systems and Control Lab., Hungary

Prof. Önder TURAN, Anadolu University, Turkey

Prof Osman Adiguzel, Firat University, Turkey

Prof. Joe Woong Yeol, Tennessee State University, USA

Prof.Kamel Mehdi, University of Tunis EL Manar, Tunisia

Prof. Vsevolod V. Koryanov, Bauman Moscow State Technical University, Russia

Prof. Rosario Pecora, Universita degli Studi di Napoli "Federico II", Italy

Prof. Antonin Pistek, Brno University of Technology, Czech Republic

Prof. Ferhan Kuyucak Şengur, Anadolu University, Turkey

Dr. Ahmed Kadhim Hussein, Babylon University, Iraq

Prof. Zhu, Zheng Hong, York University, Canada

Prof. Anshuman Srivastava, SIET Allahabad, India

Prof. Mahmut AdilCYÜKSELEN, Istanbul Technical University, Turkey

Dr. Viktor SZENTE, Budapest University of Technology and Economics, Hungary

Prof. Abd. Rahim Abu Talib, Universiti Putra Malaysia, Malaysia

Prof. PALMERINI Giovanni Battista, Sapienza University of Rome, Italy

Prof. KeeHo Yu, Chonbuk National University, Korea

Prof. Jae Wook Kim, University of Southampton, UK

Dr. Ivan Petrunin, Cranfield University, UK

Prof. Rosario Pecora, Universita degli Studi di Napoli "Federico II", Italy

Prof. Vsevolod V. Koryanov, Bauman Moscow State Technical University, Russia

Prof. Dharmahinder Singh Chand, Tagore Engineering College, India

Prof. Thomas Jin-Chee Liu, Ming Chi University of Technology, Taiwan

Prof. Fathinul Fikri AS, Universiti Putra Malaysia, Malaysia

Prof. ZHANG Yunfei, Beihang University, China

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Dr.Chung-De Chen, National Cheng Kung University, Taiwan

Dr. Feng Li, Northwestern Polytechnical University, China

Prof. Hajime Nakamura, National Defense Academy, Japan

Prof. Mohammad Hassan Rahimian, University of Tehran, Iran

Dr. Jiafeng Yao, Nanjing University of Aeronautics and Astronautics, China

Prof. Guoyi He, Nanchang Hangkong University, China

Dr. Anthony R. McAndrew, Cranfield University, UK

Prof. ANH DUNG NGO, Ecole De Technologie Superieur (U. of Quebec), Canada

Prof. İbrahimÖZKOL, Istanbul Technical University, Turkey

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Conference will be held at Hotel Plumm (ホテルプラム). Address: 220-0004 Kanagawa Prefecture,

Yokohama, Nishi-ku Kitasaiwai 2-9-1, Japan (神奈川県横浜市西区北幸 2-9-1)

UTC/GMT+9

The Weather Situation of Yokohama during Conference days

Currency

Japanese Yen (¥).

Important Contacts

Emergency Calls

Accident and Crime (Emergency Number: 110)

Hospitals (Emergency Number for Rescue, Ambulance: 119)

Police Boxes: The police box plays an important role in Japanese life. Police boxes are usually located

near train stations, in busy areas, and in residential areas. Police officers at satellite offices usually

conduct patrols both during the day and at night. Their work includes crime prevention, and locating

and arresting suspects in crimes in order to maintain security in the local area. Police officers are also

happy to give directions if you are lost or cannot find an address.

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Health Services

Minor illness or injury:

Tokyo Metropolitan Medical Institution Information "Himawari (Sunflower)" Counselors are always

ready to respond to your inquiries regarding medical institutions to provide treatment in foreign

language or information on the medical system of Japan.

Medical information service Phone:03-5285-8181.

Date and time: 9 00AM to 8 00PM Seven days a week

Illness or injury requiring immediate care:

Make a call to the Emergency Number for Rescue, Ambulance "119." Make sure to say you need an

ambulance service. An ambulance will be ready immediately.

Access

How to find the conference venue? Just some suggestions. Please google it. That could be more

correct.

From Haneda Airport

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From Narita Airport

From Nearby station: Yokohama Station (横浜駅)

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Oral presentations

Oral presentations for ACMAE have been allocated 15 minutes of effective presentation time, including Q/A

time between Session Chairs and speakers.

Authors must prepare their oral presentations to be sure to convey their message in clear and sharp manner,

including giving outline of the key principles, facts and results. More detailed discussions can continue during

the breaks.

In order to ensure a smooth performance during your session, we kindly ask you to consider the following

instructions:

Be at the session room 15 minutes before session starts and introduce yourself to the session chairs.

A video projector and a PC will be available in all conference rooms. Speakers suggested not use their own

laptop computer, avoiding useless time breaks in between presentations.

Bring your presentation on a USB memory stick in MS-PowerPoint or Adobe PDF formats, and upload it in the

Session Room computer no later than 10 minutes prior to your session start! You can also bring it earlier, during

the coffee/lunch breaks before your presentation. Please upload your presentation in a right place in order to

find it easily at the time of presentation.

Please wear formal clothes or national characteristics of clothing for participation.

In order to avoid any compatibility problems, read carefully the instructions below.

Power Point Instructions

For MS-PowerPoint presentations, please use the following versions only: PP 97-2003 (*.ppt) or 2007, 2010 to

guarantee that it will be opened successfully on the on-site PC

We recommend to the PPT/PPTX format instead of PPS

All videos or animations in the presentation must run automatically!

Pictures/Videos

We cannot provide support for embedded videos in your presentation; please test your presentation with the

on-site PC several hours before your presentation.

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In case your video is not inserted in MS-PowerPoint, it is possible to have it in other formats – MPEG 2,4, AVI

(codecs: DivX, XviD, h264) or WMV. Suggested bitrate for all mpeg4 based codecs is about 1 Mbps with SD

PAL resolution (1024x576pix with square pixels, AR: 16/9).

Fonts

Only fonts that are included in the basic installation of MS-Windows will be available (English version of

Windows). Use of other fonts not included in Windows can cause wrong layout/style of your presentation.

Suggested fonts: Arial, Times New Roman.

If you insist on using different fonts, these must be embedded into your presentation by choosing the right

option when saving your presentation:

Click on “File”, then “Save As”

Check the “Tools” menu and select “Embed True Type Fonts”

Poster presentations

Suggested Poster with size of 60cm*80cm(width*height).

Posters are required to be condensed and attractive. The characters should be large enough so that they are

visible from 1 meter apart.

During poster session, the author should stand by your poster, explaining and answering doubts or questions.

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December 29 Registration

9:00-17:00 Note: *Collecting conference materials

*Certificate of oral presentations will be signed and issued after each session.

*Certificate of poster presentations and listeners will be got when collect conference materials

at Registration Desk, please ask chair to sign it for you.

*Accommodation not provided, and it’s suggested to make an early reservation.

*Take care of all your belongings during the conference days.

December 30 Presentation Day

GEROGE V EAST (3F)

9:00-9:10 Opening Remark- Prof. Ian McAndrew, Embry Riddle Aeronautical University,UK

9:10-9:50 Keynote Speech I- Prof. Jae-Hung Han, Korea Advanced Institute of Science Technology, Korea

9:50-10:30 Keynote Speech II- Prof. Ian McAndrew, Embry Riddle Aeronautical University,UK

10:30-11:00 Group photo&Coffee Break@ Salon de Fleur (2F)

11:00-11:30 Plenary Speech I- Prof. Kenji Uchiyama, Nihon University, Japan

11:30-12:00 Plenary Speech II- Prof. Shiyin Qin, Beihang University, China

10:30-11:30 Poster Presentation @ Salon de Fleur

12:00-13:00 Lunch @ GEROGE V WEST(3F)

Palais Royal I (2F) Palais Royal II (2F)

13:00-14:45 Parallel session A-1 Parallel session B-1

14:45-15:00 Coffee Break @ Salon de Fleur (2F)

15:00-17:30 Parallel session A-2 Parallel session B-2

18:00-20:00 Dinner @ GEROGE V WEST(3F)

December 31 One day tour

9:00-17:00 Note: Five top scenic spots of Yokohama are recommended on page 44.

*The Group Photo will be updated online.

**One best presentation will be selected from each session; the best one will be announced at the end of each

session and awarded a certificate at dinner. The winners’ photos will be updated online.

***Best Presentation will be evaluated from: Originality; Applicability; Technical Merit; PPT; English.

****Please arrive at the conference room 10 minutes earlier before the session starts, copy your PPT to the

laptop.

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Prof. Jae-Hung Han

Korea Advanced Institute of Science Technology, Korea

About Prof. Jae-Hung Han: Jae-Hung Han is a professor and the head of the department of aerospace Engineering, KAIST

(Korea Advanced Institute of Science Technology), Korea. He received his B.S. in the department of mechanical department,

KAIST in 1991. He received his M.S. and Ph.D. in the department of aerospace engineering, KAIST in 1993 and 1998,

respectively. Before joining KAIST as a faculty member in 2003, he worked at the Institute of Fluid Science, Tohoku Univ.,

Japan and communication satellite development center of ETRI (Electronics and Telecommunications Research Institute),

Korea. His research and teaching activities have focused on the development of new technologies and systems that utilize

the smart materials and structures, and information technology (electronics) with the emphases on elegant design and

reliable control. Recent research topics include Shape Reconstruction of Structures; Micro Vibration Suppression for Jitter

mitigation; Pyrotechnic-Mechanical Device and Pyroshock, Bio-inspired Flying Robot, and so on. He is an associate Fellow of

AIAA, a member of ASME and SPIE. He is an associate editor for Aerospace Science and Technology, Journal of intelligent

Materials Systems and Structures, and International Journal of Aeronautical and Space Sciences. He is also an editorial

board member for Advanced Composite Materials. He has published more than 110 international journal papers, and has

received several awards including the best paper award in 2010 World Automation Congress (Sep., Kobe, Japan) and KAIST

Creative Teaching award in 2007.

“Smart Materials Systems to Mitigate Some Vibration and Shock Problems in Aerospace

Systems”

Abstract: The lightweight structural design has become essential in aerospace industry to reduce

aircraft/spacecraft weight, to improve performances, and to reduce fuel consumption. However,

lightweight structures are often accompanied by more serious vibration problems. Often these excessive

vibration problem can be mitigated by employing smart material systems. This talk focuses on smart

material systems that pertain to vibration monitoring and suppression. Firstly, the full-field real-time

measurement of vibrations of a structure based on fiber-optic technology will be introduced. Optical fibers

are the preferred sensor material for vibration monitoring because optical fibers are small and lightweight,

consume less power, and are immune to electromagnetic interference. Real-time shape estimation of

several composite structures including a wind turbine blade model was accomplished at SSS KAIST using

strain data gathered by the arrayed fiber Bragg grating (FBG) sensors. Secondly, a new type of shock and

vibration isolator using SMA materials will be introduced. A novel frequency tuning method of the isolator

is proposed to achieve both shock attenuation performance and avoidance of the vibration amplification.

The last topic is about micro-vibration problems in satellite. Why the microvibration is important is

explained, and their effects on optical payloads are systematically estimated. Some vibration isolator

designs and their performances are presented.

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Prof. Ian McAndrew, Embry Riddle Aeronautical University,UK

About Prof. Ian McAndrew: Ph.D. in Mechanical Engineering ; M.Sc. in Manufacturing MA in Education Management ; Pg.D.

in Education Training; B.A. (Hons) in Mechanical Engineering; B.A. in Production Engineering Member of the Institute of

Electrical Engineers. Dr McAndrew spent 12 years in industry as a designer before entering academia. He has over 20 years

of teaching experience in the UK, Europe, Middle East and Far East. He has supervised many PhD students and published

extensively for over 20 years. He is the author of a book and Editor of a new Journal being produced with a focus on

Aviation. Currently he is the Department Chair of Graduate Studies in the College of Aeronautics Worldwide at Embry Riddle

Aeronautical University. His research interests are in Aerodynamics and Effective Education, which he has published

extensively. He has presented at many Conferences and believes these are critical research meetings for those that are new

to research and the experienced to mentor the next generation.

“An Aerodynamic Analysis of Low Speed Wing Design using Taguchi L9 Orthogonal”

Abstract: The study of aerodynamics has been preoccupied with understanding flight at increasing speeds

and ultimately supersonic. Today, this pursuit has advanced the science for both Hypersonic and

Transonic flight to near Mach 1 supporting economical commercial flight operations. This research

presents the data from a Taguchi array on low speed with twin wing designs to establish the design

parameters for their use in low speed and high altitude. Also presented is how aerodynamic advantages

can be achieved through understanding the interactions of parameters and their use. This is compared to

operational effectiveness when applied to remotely piloted aircraft that are not constrained by direct

requirements. The research concludes with suggestions for improved designs and further work that may

enable higher altitudes with low speeds.

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Prof. Kenji Uchiyama, Nihon University, Japan

About Prof. Kenji Uchiyama: Kenji Uchiyama received PhD degree in control of aerospace systems from Tokyo Metropolitan

Institute of Technology. He is a professor at department of aerospace engineering of Nihon University. He was a member of

editorial committee of the Japan Society of Aeronautical and Space Sciences. With over 20 years of experience in guidance

and control of mechanical systems, he has published articles in the areas of micro electro mechanical systems, space robots,

lunar landers, attitude control systems for small satellites, space rovers, and unmanned aerial systems. He was a visiting

researcher of the University of Strathclyde and the University of Glasgow, and has collaborated with professors in the

University.

“Unmanned Vehicle: Guidance, Control, and its Potentialities”

Abstract: Unmanned vehicles, especially Unmanned Aerial Vehicle (UAV) has seen unprecedented growth

during the last decade, with even more expectations for future utilization in a very wide spectrum of

possible applications such as inspection in inconvenient or dangerous area. While benefiting from the

growth, new challenges arises as improvement on structural design. We have developed a quad tilt wing

UAV like a multicopter to widen application range of an unmanned system. The UAV is capable of vertical

takeoff and landing like a helicopter and level flight like an airplane during a mission. On the other hand,

Unmanned Ground Vehicle (UGV) has been actively used for exploration of unknown environment,

disaster monitoring, and surveillance. The vehicle sometimes requires simultaneous localization and

mapping in non-GPS environment, irregular ground traveling, and collision avoidance for an exploration.

It is important for the vehicles to realize real time control, to have robustness against disturbances and to

consider fault tolerance. In this talk, recent research work will be highlighted in this area, focusing on

guidance and control of nonlinear dynamics of the vehicles. Furthermore, this talk will present work on

formation flying of UAVs and cooperation of UAV-UGV for constructing efficiency system. Our work will

also be presented with successful demonstration.

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Prof. Shiyin Qin, Beihang University, China About Prof. Shiyin Qin: Shiyin Qin is now a professor at the School of Automation Science and Electrical Engineering in

Beihang University (Beijing University of Aeronautics and Astronautics). He had ever been a standing member of the council

and the secretary-general of Chinese Association for Artificial Intelligence (CAAI) during 2001-2010, and the vice-chairman

of the Society of Intelligent Control and Intelligent Management in CAAI during 2001-2012, and is also a member of the

Committee of Intelligent Automation of Chinese Association of Automation (CAA) in 1994-2010. He received the Bachelor

Degree and the Master Degree of Engineering Science in Automatic Controls and Industrial Systems Engineering from

Lanzhou Jiaotong University in 1978 and 1984 respectively, and the Ph.D. Degree in Industrial Control Engineering and

Intelligent Automation from Zhejiang University in 1990. He had ever been a professor in Xi’an Jiaotong University and

Beijing University of Technology. He took up the post of cochair of International Program Committee of Conference D

(Automatic Control) and the Editor-in-Chief of the proceedings in the 2001 International Conferences on Info-tech and

Info-net. He has published more than 260 papers in journals and proceedings in the fields of pattern recognition and

machine learning, image processing and machine vision, intelligent controls for large scale systems, hybrid control systems,

artificial intelligence, neural networks, fuzzy control systems, evolutionary computation and entropy optimization, and so on.

He is the author of 3 monographs: “The Theory and Methodology of Intelligent Control Systems (1994)”; “Introduction to

Intelligent Controls (1997)” and “An Introduction to Hybrid Dynamical Systems (2007)”. He was awarded the First Level

Prize of “1999’ National Excellent Books of Science and Technology and the Progress of Science and Technology”, and the

Gold Medal Prize of the Excellent Software of “the 5th National Engineering Design”(1999). His current research interests

include intelligent autonomous controls of UAV systems; autonomous intelligent controls of formation process for

multi-robot system; fault diagnosis and fault-tolerant controls; image processing and machine vision; pattern recognition

and machine learning; computational intelligence and entropy optimization.

“Approach to Detection and Tracking of Infrared Small Target Based on Reinforcement

Learning and Discriminative Classification with Gaussian Mixture Model”

Abstract: In this talk, some research results are presented about detection and tracking of infrared small

target, which may exhibit one side of the speaker’s recent achievements in the Lab of Pattern Recognition

and Intelligent Systems, Beihang University, Beijing, China. At first, an adaptive detection method of

infrared small target is introduced based on target-background separation via robust principal component

analysis. Then an approach for moving small target detection is presented under a pipeline framework

with an optimization strategy based on reinforcement learning in view of background clutter and target

size variation with time. Finally an infrared small target tracking method is addressed by means of

discriminative classification with Gaussian mixture model of compressive appearance distribution. Frankly

speaking, it is a challenge topic to implement high performance detection and tracking of infrared small

target, we hope to exchange some beneficial research progress and consult with our colleagues and

experts so as to make more efforts to achieve great success in some relevant research fields.

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Technical Program

Oral Presentation

Saturday Afternoon, 30 December 2017, 13:00-17:15

Time Palais Royal I (2F)

13:00-14:45 Session A-1: Aircraft Structure Design and Aerodynamic Performance Analysis

14:45-15:00 Coffee Break

15:00-17:15 Session A-2: Aerospace Electronics System Control and Communication

Note:

* Please control each presentation time within 15 mins, including Q & A.

* The certificate of Oral presentations will be awarded at the end of each session.

* Best Presentation of each session is encouraged to award to student author prior.

* Winner of Best presentation will be announced at the end of session and winner certificate will be awarded at the

dinner.

* To show the respect to other authors, especially to encourage the student authors, we strongly suggest you attend

the whole session.

* The scheduled time for presentations might be changed due to unexpected situations, please arrive meeting room

at least 10 Mins before Session starts.

* Session photo will be taken at the end of the session and updated online.

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Saturday, 30 Dec., 13:00-14:45

Session A-1: Aircraft Structure Design and Aerodynamic Performance

Analysis Room: Palais Royal I (2F)

Chair:

Time: 13:00-13:15

Fluid Similarity Criterions in Aircraft Landing Gear

Mr. Liu Xiang-yong, Li Wan-li, Xu Zhi-qiang

School of Mechnical Engineering, Tongji University, China,

Facing the design difficulty and risk of aircraft landing gear, the fluid similarity theory

and model experiments are used to predict large prototype’s property, which provide

guidance for hydraulic designation and selection to reduce risk. Firstly, the matrix

method is used to establish the fluid similarity relationship between the prototype and

the model’s luffing mechanism, and the above conclusions are used to design the

prototype’s hydraulic system. Secondly, the luffing mechanism’s dynamical model with

accumulator was established, the initial motion condition was set, and the pressure’s

similarity ratio is obtained by simulation method. Finally, the dynamic model and

similarity ratio about time, velocity and pressure are verified by the prototype and

model’s experimental data.

Time: 13:15-13:30

Numerical Experiment of Initial Flow Patterns and Fluid Force Characteristics of

Tandem Arrangement Two Symmetrical Airfoils

Prof. Yoshifumi Yokoi

National Defense Academy of Japan, Japan

A numerical simulation was performed using a vortex method in order to investigate

the fluid mechanical interferences of two tandem airfoils at variable angles of attack.

Based on the shape of a vessel or a submarine, the mutual distance between the two

airfoils (distance ratio) and the range of angle of attack were chosen. A symmetrical

airfoil NACA0012 was used and the Reynolds number was Re = 3.8×105. The setting

of distance ratio was L/C = 5.0, the attack angle of airfoils were varied as α = 0, ±5,

±10 and ±15 degrees. The initial stage was observed in this study. As a result of

calculations, the flow pattern in each case was obtained, the variation of the fluid force

in each case was investigated, and the variation of an overall lift coefficient was shown.

By the mutual interference of two airfoils, it was found that the rapid variation of the

overall lift coefficient occurs in an early stage.

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Time: 13:30-13:45

Research and Application of Virtual Simulation Technology in the Aerospace Bearing

Design and Manufacture

Dr. Liu Jiangshan, Chen Ming and Liu Jinfei

Tongji University, Shanghai,China

Bearings are widely used in aerospace and other fields, its performance directly affects

the production efficiency and safety. Nowadays, virtual simulation technology has

become an indispensable part of intelligent manufacturing field. As a virtual simulation

technology, FEA has been widely used in bearing design. China needs to import many

aerospace bearings every year in aerospace area, Chinese national defense and other

high precision technology is limited because the blockade of advanced bearing

technology. We can use dynamics modeling and virtual simulation technology to

achieve the predictive design, and strive to achieve foreign level. In this paper, the

author proposed a method of bearing design based on virtual simulation technology.

The factors of bearing which affect the dynamic characteristics are considered, the

process of design bearing based on virtual simulation is also considered. According to

the different design parameters, the simulation results are used to verify the rationality,

these can reduce the cost and improve the reliability. The virtual simulation technology

is applied to design the 7016C angular contact ball bearing which used in aerospace

area, and supported decision-making in structure design and data analyze. Finally, The

feasibility of this method is verified by experiments.

Time: 13:45-14:00

Structure design of an innovative adaptive variable camber wing

Mr. An-Min Zhao, Zou Hui, De-Shan Liu, Bing-Fei Liu

School of Aeronautical Science and Engineering, Beihang University, China

In this paper, an innovative double rib sheet structure is proposed, which can replace

the traditional rigid hinge joint with the surface contact. On the one hand, the variable

camber wing structural design not only can improve the capacity to sustain more load

but also will not increase the overall weight of the wing. On the other hand, it is a

simple mechanical structure design to achieve the total wing camber change. Then the

numerical simulation results show that the maximum stress at the connect of the wing

rib is 88.2MPa, and the double ribs sheet engineering design meet the structural

strength requirements. In addition, to make a fair comparison, the parameters of

variable camber are fully referenced to the Talon Unmanned Aerial Vehicle (UAV). The

results reveal that the total variable camber wing can further enhance aircraft flight

efficiency by 29.4%. The design of the whole variable camber wing structure proposed

in this paper has high engineering value and feasibility.

Time: 14:00-14:15

Measurement of mutual interference sound of columnar objects in air flow

Mr. Shohji Hamada and Yoshifumi Yokoi

National Defense Academy, Japan

When a columnar object is put in a flow, Karman vortex is formed, and aerodynamic

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noise is generated. It is known that when multiple columnar objects are put in a flow,

the flow state becomes complex. This can be known by flow visualization experiment.

On other hands, there are few researches on flow sound in the case of mutual

interference, that it is not as far as the authors know. Measurement of flow sound is

performed using a microphone. Therefore, it is necessary to confirm the sound of the

interference flow field reaches the microphone outside the flow field without changing.

In this research, experiments were measured to confirm flow sound transmits to a

microphone placed outside the flow field without changing. Based on the results, the

aerodynamic noise measurement from the columnar object was performed using a low

noise wind tunnel experimental apparatus. As a result, it was obtained that some

findings on the sound of flow in mutual interference flow field.

Time: 14:15-14:30

Design of a Symmetrical Quad-rotor Biplane Tail-Sitter Aircraft without Control

Surfaces and Experimental Veritification

Hongyu Wang, Mr. Xun Zhao, Cunyue Lu, Baoming Zhang, Cong Li

Department of Instrument Science and Engineering, Shanghai Jiao Tong University,

Shanghai, China

This paper presents the design of a symmetrical quad-rotor biplane tail-sitter VTOL

UAV (Vertical Take-off and Landing Unmanned Aerial Vehicle) which is composed of

four rotors and two symmetrically mounted fixed wings. This aircraft achieves high

accuracy in the attitude control and smooth flight mode transition with four rotors

rather than the conventional VTOL UAVs using control surfaces. The proposal of

angled rotor mounting is adopted to address the issue of insufficient yaw control

authority. The layout of symmetrically mounted fixed wings makes the aircraft have

capability of rapid bidirectional flight mode transition to improve maneuverability. To

validate the performance of the aircraft, simulation and flight experiments are both

implemented. These results show that the aircraft has a rapid yaw response under

condition of the stable attitude control. In comparative experiment, it is shown that the

aircraft is more flexible than other similar configuration of aircrafts. This symmetrical

quad-rotor biplane tail-sitter VTOL UAV will have a wide range of potential

applications in the military and civilian areas due to its superior performance.

Time: 14:30-14:45

A computational study of the aerodynamic performance of a dragonfly forewing in

gliding flight

Mr. Huixiang Liu, Guoyi He ,Chengyu Ma, Qi Wang and Yun Luo

School of Aircraft Engineering, Nanchang Hangkong University, China

Gliding flight is a common mode of flight for dragonfly, the objective of the current

research is to use numerical simulations to explore whether the corrugations have

positive effect on aerodynamic performance of the dragonfly wings in gliding flight. In

order to compare aerodynamic performance of the dragonfly wing and flat plate, a

three-dimensional model of the dragonfly forewing and a three-dimensional flat plate

with the same shape of the dragonfly forewing are established. The flow fields around

three-dimensional dragonfly forewing and flat plate are simulated for Re=10000 and

angles of attack changing from 0° to 25°(with an interval of 5°), numerical simulation

indicate that aerodynamic performance of the dragonfly wing is slightly better than the

flat plate over the entire range of parameters tested, especially the effect of the

corrugateions on the flow is more evident at large angle of attack.

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Saturday, 30 Dec., 15:00-17:15

Session A-2: Aerospace Electronics System Control and Communication Room: Palais Royal I (2F) Chair: Prof. Nam Seo Goo, Konkuk University, Republic of Korea

Time: 15:00-15:15

Comparing the Performance of Reference Trajectory Management and Controller

Reconfiguration in Attitude Fault Tolerant Control

Rouzbeh Moradi, Dr. Alireza Alikhani and Mohsen Fathi Jegarkandi

Aerospace Research Institute, Ministry of Science, Research and Technology, Tehran,

Iran

Reference trajectory management is a method to modify reference trajectories for the

faulty system. The modified reference trajectories define new maneuvers for the system

to retain its pre-fault dynamic performance. Controller reconfiguration is another

method to handle faults in the system, for instance by adjusting the controller

parameters (coefficients). Both of these two methods have been considered in the

literature and are proven to be capable of handling various faults. However, the

comparison of these two methods has not been considered sufficiently. In this paper, a

controller reconfiguration mechanism and a reference trajectory management are

proposed for the spacecraft attitude fault tolerant control problem. Then, these two

methods are compared under the same conditions, and it is shown that the proposed

controller reconfiguration has better performance than the proposed reference

trajectory management. The reason is that the controller reconfiguration has more

variables to modify the closed-loop system behavior.

Time: 15:15-15:30

Blocking Force of Shape Memory Polymer Composite Hinges For Space Deployable

Structures

Thanh Duc Dao, Van Luong Le, Prof. Nam Seo Goo, and Woong Ryeol Yu

Konkuk University, Republic of Korea

This study introduces a method to measure the blocking force of a shape memory

polymer composite (SMPC) hinge to quantify the performance of an SMPC hinge for

space deployable structure applications. A detailed design of how to select heating

elements for a self-deployable configuration is also suggested. The SMPC hinge

consists of two reverse carpenter SMPC tapes that were made from carbon-epoxy

fabric, SMP resin, and one heating element. The heating element was attached to the

SMPC tape using the composite manufacture method and used as a heating source in

the deployment test. The blocking force and moment of the hinge were measured using

a pulley-mass system setup to examine the mechanical performance of the hinge.

During the test, the shape change was recorded with the use of a camera to calculate

blocking moment. The blocking force and moment were 7.21 N and 0.47 Nm,

respectively, at the initial test. The blocking force and moment decreased slightly with

the working cycle and were 6.27 N and 0.41 Nm at the repeated test. Additionally, the

- 21 -

results revealed that a pop-up phenomenon occurred at the middle period of

deployment. These results show that the SMPC hinge is a good candidate for space

deployable structure applications, and a guideline for performance evaluation of the

SMPC hinge is suggested.

Time: 15:30-15:45

High Accuracy Positioning using Jet Thrusters for Quadcopter

Mr. ChenHuan Pi, JinKwan Lin and Stone Cheng

National Chiao Tung University, Department of Mechanical Engineering, Taiwan

A quadcopter is equipped with four additional jet thrusters on its horizontal plane and

vertical to each other in order to improve the maneuverability and positioning accuracy

of quadcopter. A dynamic model of the quadcopter with jet thrusters is derived and two

controllers are implemented in simulation, one is a dual loop state feedback controller

for pose control and another is an auxiliary jet thruster controller for accurate

positioning. Step response simulations showed that the jet thruster can control the

quadcopter with less overshoot compared to the conventional one. Over 10s loiter

simulation with disturbance, the quadcopter with jet thruster decrease 85% of RMS

error of horizontal disturbance compared to a conventional quadcopter with only a dual

loop state feedback controller. The jet thruster controller shows the possibility for

further accurate in the field of quadcopter positioning.

Time: 15:45-16:00

Concept development of control system for perspective unmanned aerial vehicles

Vsevolod V. Koryanov, Tatiana V. Kokuytseva, Alexey G. Toporkov, Stepan N.

Iljukhin, Il'ya O. Akimov, Mr. Noa Mohamado

Peoples Friendship University of Russia (RUDN University), Russian Federation

Presented actual aspects of the development of the control system of unmanned aerial

vehicles (UAVs) in the exaFmple of perspective. Because the current and future UAV

oriented to implementation of a wide range of tasks, taking into account the use of

several types of payload, in this paper discusses the general principles of construction

of onboard control complex, in turn, a hardware implementation of the automatic

control system has been implemented in the microcontroller Arduino platform and the

Raspberry Pi. In addition, in the paper presents the most common and promising way to

ensure the smooth and reliable communication of the command post with the UAV as

well as to the ways of parry considered and abnormal situations.

Time: 16:00-16:15

UAV Delivery Monitoring System

Ms. Khin Thida San, Sun Ju Mun and Yoon Seok Chang

School of Air Transportation and Logistics, Korea Aerospace University, South Korea

UAV-based delivery systems are increasingly being used in the logistics field,

particularly to achieve faster last-mile delivery. This study develops a UAV delivery

system that manages delivery order assignments, autonomous flight operation, real time

control for UAV flights, and delivery status tracking. To manage the delivery item

assignments, we apply the concurrent scheduler approach with a genetic algorithm. The

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present paper describes real time flight data based on a micro air vehicle

communication protocol (MAVLink). It also presents the detailed hardware components

used for the field tests. Finally, we provide UAV component analysis to choose the

suitable components for delivery in terms of battery capacity, flight time, payload

weight and motor thrust ratio.

Time: 16:15-16:30

Construction and Application Research of Knowledge Graph in Aviation Risk Field

Ms. Zhao Qian, Li Qing and Wen Jingqian

School of Mechanical Engineering and Automation, Beijing University of Aeronautics

and Astronautics, China

Since the causes of aviation accidents and risks are complicated, concealed,

unpredictable and difficult to be investigated, in order to achieve the efficient

organization and knowledge sharing of the historical cases of aviation risk events, this

paper put forward the method of constructing vertical knowledge graph for aviation risk

field. Firstly, the data-driven incremental construction technology is used to build

aviation risk event ontology model. Secondly, the pattern-based knowledge mapping

mechanism, which transform structured data into RDF (Resource Description

Framework) data for storage, is proposed. And then the application, update and

maintenance of the knowledge graph are described. Finally, knowledge graph

construction system in aviation risk field is developed; and the data from American

Aviation Safety Reporting System (ASRS) is used as an example to verify the

rationality and validity of the knowledge graph construction method. Practice has

proved that the construction of knowledge graph has a guiding significance for the case

information organization and sharing on the field of aviation risk.

Time: 16:30-16:45

Factorial Experiment on Route Structures Using SAAM on A Specified Area in

ASEAN

Ms. Su Myat Phyoe, Jin Wen Goh, Rui Guo and Zhao Wei Zhong

Air Traffic Management Research Institute, Nanyang Technological University,

Singapore

Due to a rapid growth in the air transport industry, ASEAN (Association of Southeast

Asia Nations) region has experienced a surge in the air traffic movement in recent

years. Several forecasting papers foretell to have the continuous traffic growth for

ASEAN region. The pilot study of ATS routes forecasts also conclude that there is a

need to relook at the current route structures in selected areas in ASEAN. The

interaction between the structure of ATS routes and the number of intersections has

been studied by using the number of conflicts. This paper will serve as a continuation of

the previous study, and the objective is to determine whether there is any consistency in

the conclusion when the selected area is changed, using the methodology proposed.

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Time: 16:45-17:00

Research on Human-Error Factors of Civil Aircraft Pilots Based On Grey Relational

Analysis

Dr.Yundong Guo, Youchao Sun, Si Chen

Nanjing University of Aeronautics and Astronautics, China

In consideration of the situation that civil aviation accidents involve many human-error

factors and show the features of typical grey systems, an index system of civil aviation

accident human-error factors is built using human factor analysis and classification

system model. With the data of accidents happened worldwide between 2008 and 2011,

the correlation between human-error factors can be analyzed quantitatively using the

method of grey relational analysis. Research results show that the order of main factors

affecting pilot human-error factors is preconditions for unsafe acts, unsafe supervision,

organization and unsafe acts. The factor related most closely with second-level indexes

and pilot human-error factors is the physical/mental limitations of pilots, followed by

supervisory violations. The relevancy between the first-level indexes and the

corresponding second-level indexes and the relevancy between second-level indexes

can also be analyzed quantitatively.

Time: 17:00-17:15

A Method of Coding for Aerospace Product Quality DNA

Mr. Yao Jiayu

School of Mechnical Engineering, Tongji University, China,

Aiming at the problem that the manufacturing process of our aerospace products is

relatively discrete and the lack of appropriate quality monitoring and feedback

mechanism, a method of coding for aerospace product quality DNA was proposed.

Based on the structure of biological DNA and the theory of quality assessment,

equipment diagnosis and quality traceability, the biological DNA structure was

transformed into the structure of aerospace product quality DNA, and the concept of

aerospace product quality DNA was defined, including the genetic and variation

characteristics of aerospace product quality DNA. The coding rules of aerospace

product quality DNA were designed, and the designed encoding rules are applied to the

case of welding of wall panels in the manufacturing process of aerospace products. The

results show that the coding method can monitor and feedback the core information

related to quality in the manufacturing process of aerospace products.

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Technical Program

Oral Presentation

Saturday Afternoon, 30 December 2017, 13:00-17:15

Time Palais Royal II (2F)

13:00-14:45 Session B-1: Mechatronics and Application

14:45-15:00 Coffee Break

15:00-17:15 Session B-2: Materials Science and Mechanical Engineering

Note:

* Please control each presentation time within 15 mins, including Q & A.

* The certificate of Oral presentations will be awarded at the end of each session.

* Best Presentation of each session is encouraged to award to student author prior.

* Winner of Best presentation will be announced at the end of session and winner certificate will be awarded at the

dinner.

* To show the respect to other authors, especially to encourage the student authors, we strongly suggest you attend

the whole session.

* The scheduled time for presentations might be changed due to unexpected situations, please arrive meeting room

at least 10 Mins before Session starts.

* Session photo will be taken at the end of the session and updated online.

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Saturday, 30 Dec., 13:00-14:45

Session B-1: Mechatronics and Application Room: Palais Royal II

Chair: Prof. Hajime Nakamura, National Defense Academy, Japan

Time: 13:00-13:15

Torque and Ripple Analyses of a Small BLDC Motor for a Surgical Device

Prof. Cheol Kim, Mingzhe Li and Changmin Park

Department of Mechanical Engineering, Kyungpook National University, Korea

A small BLDC motor is under consideration to operate small dental and surgical

hand-pieces instead of low torque air turbines, due to high torque density compared to

a size. Electromagnetic analyses were carried out numerically in order to improve the

performance of a hand-piece motor such as torque output and torque ripple. Several

case studies on the characteristics of electromagnetic torque outputs were carried out

by increasing numbers of coil wires from 11 to 30 wound and the maximum motor

torque was obtained with 20 wound wires at the electromagnetic angle of 90o. The

stator slot made of Teflon was found to be better than steel in the magnetic flux density

from a material comparison study. In an effort to reduce torque ripple of the motor, the

changes in torque ripples for several slot shapes of a stator were evaluated by finite

element analyses and compared. The slot with both circular holes and V-cut showed a

best ripple performance that was 6.10%, compared to 7.80% of the current design.

Time: 13:15-13:30

Computational modelling of an Organic Rankine Cycle (ORC) waste heat recovery

system for an aircraft engine

Dr. SAADON Syamimi

Department of Aerospace Engineering, Faculty of Engineering, University Putra

Malaysia, Malaysia

Escalating fuel prices and carbon dioxide emission are causing new interest in methods

to increase the thrust force of an aircraft engine with limitation of fuel consumption.

One viable means is the conversion of exhaust engine waste heat to a more useful form

of energy or to be used in the aircraft environmental system. A one-dimensional

analysis method has been proposed for the organic Rankine cycle (ORC) waste heat

recovery system for turbofan engine in this paper. The paper contains two main parts:

validation of the numerical model and a performance prediction of turbofan engine

integrated to an ORC system. The cycle is compared with industrial waste heat

recovery system from Hangzhou Chinen Steam Turbine Power CO., Ltd. The results

show that thrust specific fuel consumption (TSFC) of the turbofan engine reach lowest

value at 0.91 lbm/lbf.h for 7000 lbf of thrust force. When the system installation weight

is applied, the system results in a 2.0% reduction in fuel burn. Hence implementation

of ORC system for waste heat recovery to an aircraft engine can bring a great potential

to the aviation industry.

- 26 -

Time: 13:30-13:45

Cooling Fan Model for Thermal Design of Compact Electronic Equipment (Modeling

of swirl flow at the exit of axial-flow-fan)

Prof. Hajime Nakamura

National Defense Academy, Japan

In order to hasten the thermal design for forced convection electronic devices, cooling

fans should be modelled to reduce a computational load. A fan-curve-model, which

generates volumetric flow rate according to the PQ curve, is very simple and usually

incorporated into commercial CFD codes. However, the conventional model does not

specify the flow field at the exit of a fan since the PQ curve has no information on the

flow swirling. Thus, in this work, the swirl force acting on the flow was modelled

mathematically by introducing a non-dimensional “swirl coefficient”, which can be

incorporated into the fan-curve-model. The swirl coefficient was evaluated using the

detailed CFD simulation taking the rotating blades into account, and the result indicated

that this coefficient can be treated as a constant regardless of radial position of the

blade. Then, the flow behind the fan was simulated using the fan-curve-model

incorporated with the swirl coefficient. As a result, it was confirmed that a realistic

velocity distribution can be generated within the normal usable range of the fan where

the rotating stall does not occur.

Time: 13:45-14:00

Experimental and Numerical Design and Optimization of a Counter-Flow Heat

Exchanger

Dr. Salman Bahrami and Mohammad Hassan Rahimian

University of Tehran, Tehran, Iran

A new inexpensive counter-flow heat exchanger has been designed and optimized for a

vapor-compression cooling system in this research. The main aim is to experimentally

and numerically evaluate the effect of an internal heat exchanger (IHX) adaptation in an

automotive air conditioning system. In this new design of IHX, the high-pressure liquid

passes through the central channel and the low-pressure vapor flows in several parallel

channels in the opposite direction. The experimental set-up has been made up of

original components of the air conditioning system of a medium sedan car, specially

designed and built to analyze vehicle A/C equipment under real operating conditions.

The results show that this compact IHX may achieve up to 10% of the evaporator

capacity while low pressure drop will be imposed on this refrigeration cycle. Also, they

confirm considerable decrease of compressor power consumption (CPC), which is

intensified at higher evaporator air flow. A significant improvement of the coefficient of

performance (COP) is achieved with the IHX employment too. The influence of

operating conditions has been also discussed in this paper. Finally, numerical analyses

have been briefly presented, which bring more details of the flow behavior and heat

transfer phenomena, and help to determine the optimal arrangement of channels.

Time: 14:00-14:15

Fundamental Study on Operational Parameters of Diaphragmless Shock Tube

Mr. Masanori NISHIYAMA, Masato TAGUCHI and Masashi KASHITANI

- 27 -

Department of Aerospace Engineering, National Defense Academy of Japan

This paper shows influences of initial conditions on a diaphragmless shock tube

operation. This facility consists of a driver tube, a driven tube and a damp tank. The

driver tube has a circular cross section with diameter of 150 mm and the driven tube, a

rectangular cross section (60 mm x 150 mm). The shock tube is operated by using a

quick-opening pneumatic piston instead of a diaphragm. For the operation, pressure

inside the pneumatic piston (piston pressure) is quickly released by opening a solenoid

valve. In this paper, the initial piston pressure was chosen as a parameter to investigate

effects on test flow conditions created by the shock tube. As a result, it was found that

when the piston pressure at initial condition is large, piston pressure decreased more

rapidly than that obtained for a small piston pressure condition, regardless of the

pressure ratio of driver and the driven tube. In the condition of a constant initial

operational pressure ratio and a different piston pressure, the shock Mach number was

almost constant.

Time: 14:15-14:30

Experimental and Numerical Investigation of Shock Wave in a 1+1/2 Counter-Rotating

Turbine

Mr. Chao Li, Huo-Xing Liu, Zhi-Hong Zhou

School of Energy and Power Engineering, Beihang University, China

To investigate the internal distribution regularities of shock wave structure in 1+1/2

counter-rotating turbine, numerical simulation and experimental research about the

shock wave structure were conducted by using the schlieren apparatus under different

working conditions.From the point of the unsteady results, the unsteady effect has few

influence on the flow field of high pressure guide vane, but the wake of the high

pressure guide leaves periodically sweeps through the front edge of the high pressure

blade and there presents strong unsteady effect on flow field of high pressure rotor.

Because of periodic influence of external wake and shock wave, the unsteadiness of

flow in low pressure rotor is still strong but not that drastic compared to the high

pressure rotor. 50% height section of the blade of the three types of blades are extracted

respectively to make plane cascades which are conducted blowing experiments in

supersonic wind tunnel. The final photograph were analyzed by comparing with the

CFD results. Results show that with the increase of expansion ratio, the wave structures

in blade channel move toward the exit and the caudal interference between the outer tail

wave and is strengthened gradually.

Time: 14:30-14:45

Digital Internal Module Controller Shaped by Sensitivity Function of Platform Driven

by Ultrasonic Motor

Dr. PAN Song, XU Zhang-fan, HUANG Wei-qing

Nanjing University of Aeronautics and Astronautics, China

When the ultrasonic motor is used on the stabilized platform, load is applied on the

motor and the motor’s motion state is changed. It is necessary to carry out some relative

researches on the problem. Firstly, this paper establishes the dynamics model of

stabilized platform driven by ultrasonic motor. Secondly, combined with the established

model, the internal model controller is designed to satisfy the stability requirement of

the stabilized platform from the disturbance to the output. In order to verify the control

effect of the proposed controller, the control effect of the proposed controller is

- 28 -

simulated and compared with the Proportion-Integral-Derivative Controller. We can

find that this control method is better than classical Proportion Integral Derivative

controller. The unit step response time reduces 0.03s. The tracking error of 1Hz

sinusoidal reference signal reduces from 1.9% to 0.6%. The ability of restraining the

external disturbance improves about 10dB and suppression band at about -30dB also

increased by about 4Hz.

- 29 -

Saturday, 30 Dec., 15:00-17:15

Session B-2: Materials Science and Mechanical Engineering Room: Palais Royal I I (2F)

Chair: Prof. Venkatraman Ramamoorthi, School of Mechanical Engineering, SASTRA

Univeristy, India

Time: 15:00-15:15

Nonlinear dynamic responses of a honeycomb sandwich plate subject to transverse

excitations

Ms. Dongmei Wang, Wei Zhang, Minghui Yao and Yinli Liu

Beijing University of Technology, China

Nonlinear dynamic behaviors of a simply supported honeycomb sandwich plate

subjected to the transverse excitations are investigated in this paper. Based on the

classical thin plate theory and Von Karman large deformation theory, the governing

equation of motion for the honeycomb sandwich plate is established by using the

Hamilton principle. The nonlinear governing partial differential equation is discretized

to the ordinary differential equations by differential quadrature method and then solved

by Runge-Kutta-Fehlberg method. Based on the numerical simulations, combined with

nonlinear dynamic theory, the influences of the frequency and amplitude of the

transverse excitation are investigated respectively by using the bifurcation diagrams,

Poincare maps and phase portraits. The results exhibit the existence of the period-1,

period-2 and chaotic responses with the variation of the excitations, which demonstrate

that those motions appear alternately.

Time: 15:15-15:30

A Time-Domain Substructure Synthesis for Finite Rotations of Flexible Mechanical

Systems

Mr. Shulin Chen, Li Liu and Zhaoyue Chen

School of Aerospace Engineering, Beijing Institute of Technology, China

This paper presents a floating IBS method for dynamic prediction of structures with

finite rotations. The conventional IBS (impulse-based substructuring) method is

efficient and accurate in structural transient impact analysis. When facing about finite

rotations, the conventional IBS method will generate unreasonable results due to the

lack of consideration of geometric nonlinearity. In this paper, the idea of floating frame

of reference is introduced. The motions of structures are divided into the moving of

floating frame of reference and local vibrations which are described using the idea of

IBS method. Two numerical examples validate that the proposed method is available

for unconstrained single-body system (free-free rotating beam) and constrained

multibody system (a slider-crank system). Meanwhile, to some extent the local elastic

vibration degrees of freedom can be reduced by employing interpolation matrixes.

- 30 -

Time: 15:30-15:45

Investigation of Micro hardness, cooling rate and Microstructure of ATIG welded

samples of Al-SiC composite

Sivachidambaram Pichumani, Raghuraman Srinivasan and Prof. Venkatraman

Ramamoorthi

School of Mechanical Engineering, SASTRA Univeristy, India

Activated TIG welding has been performed on Al – 8% SiC composite 5mm plate with

various fluxes such as Al2O3, MnO2, CaO, MgO, SiO2 & TiO2, to study & analyze the

Microstructure, Micro hardness and cooling rate. Correlation study between micro

hardness, microstructure and cooling rate for Constant Current TIG welding and

Activated TIG welding on Al-SiC composite are also carried out to analyze the relation

between the effect of cooling rate on microstructure & the effect of microstructure on

micro hardness. The experimental results of ATIG welding on Al-SiC composite shows

fine grain weld microstructure on ATIG – SiO2 & ATIG – TiO2, which results in higher

micro hardness. Micro hardness values are taken in different locations of weld surface

at 1mm, 2mm & 3mm below the weld surface and the same is also observed along the

weld zone to heat affected zone upto 12mm for the center of the weldment. Minimum

micro hardness values found in ATIG – MnO2, ATIG – CaO & ATIG – MgO are due to

intermediate micro structure between coarse and fine in heat affected zone. ATIG –

Al2O3 weld zone & heat affected zone and heat affected zone of ATIG – MnO2, ATIG –

CaO & ATIG – MgO shows coarse microstructure leading to reduction in micro

hardness value. Cooling rate for the different CCTIG & ATIG welding are recorded

and correlation between the micro structures are studied. Coarse micro structure in weld

zone and heat affected zone have least cooling rate whereas fine micro structure in weld

zone resulted at higher cooling rate. Heat affected zone strongly depends on

temperature gradient between the weld center and weldment’s heat affected zone.

Time: 15:45-16:00

Research of Boundary Layer Transition characteristics Induced by Three-Dimensional

Discrete Roughness

Assoc. Prof. Feng Li, Chao Gao, Zijie Zhao and Xudong Ren

Northwestern Polytechnical University, China

Roughness strip is a necessary technology for wind tunnel experiment. In order to

improve the accuracy and reliability of transition simulation, a new fixed transition

technology based on the three-dimensional discrete roughness elements has been

established. The configuration parameters of roughness elements are calculated

theoretically and the formula and manufacturing processes of roughness elements are

developed. Using two-dimensional airfoil and three-dimensional combination

models, the transition and additional resistance characteristics of discrete roughness

elements are studied. Finally, the scale effect of roughness elements is analyzed and the

influence laws of height, diameter, and spacing on transition characteristics have been

obtained through numerical calculation. The results of this study indicate that this new

- 31 -

discrete roughness is better in transition and additional resistance performance than

conventional grit roughness. The results obtained in this paper has created a

more reliable and accurate fixed transition technology for wind tunnel experiment and

provided some reference for cross-flow transition mechanism.

Time: 16:00-16:15

Synchronous Surface Pressure and Velocity Measurements of standard model in

hypersonic flow

Dr. Sun Zhijun, Prof. GU Yunsong, CHEN Keming, Di peng, Yingzheng Liu

Nanjing University of Aeronautics and Astronautics(NUAA), China

Experiments in the Hypersonic Wind tunnel of NUAA(NHW) present synchronous

measurements of bow shockwave and surface pressure of a standard blunt rotary model

(AGARD HB-2), which was carried out in order to measure the Mach-5-flow above a

blunt body by PIV (Particle Image Velocimetry) as well as unsteady pressure around the

rotary body. Titanium dioxide (Al2O3) Nano particles were seeded into the flow by a

tailor-made container. With meticulous care designed optical path, the laser was guided

into the vacuum experimental section. The transient pressure was obtained around

model by using fast-responding pressure-sensitive paint (PSP)sprayed on the model. All

the experimental facilities were controlled by Series Pulse Generator to ensure that the

data was time related. The PIV measurements of velocities in front of the detached bow

shock agreed very well with the calculated value, with less than 3% difference

compared to Pitot-pressure recordings. The velocity gradient contour described in

accord with the detached bow shock that showed on schlieren. The PSP results

presented good agreement with the reference data from previous studies. Our work

involving studies of synchronous shock-wave and pressure measurements proved to be

encouraging.

Time: 16:15-16:30

Comparison of Efficiency of Conventional Shaped Circular and Elliptical Shaped

Combustor

Mr. Gautam Ganesh, Daamanjyot Barara, Suraj Anand and Dharmahinder Singh

Chand

SRM University, Kattankulathur, India

There have been concerted efforts towards improving the fuel efficiency of the jet

engines in the past, with an aim of reducing the incomplete combustion. The process of

combustion in a jet engine takes place in the combustor. A study was conducted for

enhancement of air-fuel mixing process by computational analysis of an elliptically

shaped combustor for a gas turbine engine. The results of computational analysis of an

elliptical shape combustor were compared with a circular shape combustor used in gas

turbine engines with a identical cross sectional area. The comparison of the

computationally derived parameters of the two combustors i.e. temperature, pressure,

and velocity are studied and analyzed. The study intends towards the comparison of the

combustion efficiencies of the circular and elliptically shaped combustors. The

combustion efficency of elliptical chamber is found to be 98.72% at the same time it

was observed 56.26% in case of circular type combustor.

- 32 -

Time: 16:30-16:45

Material Property and Stress Field near Notch Tip in Steel Plate under High Electric

Current

Thomas Jin-Chee Liu, Mr. Ji-Fu Tseng and Chun-Der Cheng

Department of Mechanical Engineering, Ming Chi University of Technology, Taiwan

Under high electric current, the material property and stress field near the notch tip in

the stainless steel plate have been investigated. Using the numerical and experimental

methods, the electric current density, temperature, stress, grain image and micro

hardness are obtained. Also, the melting and heat-affected zones at the notch tip are

investigated. At the tip region, the hardness value improves and the compressive

residual stress occurs. This result can reduce the stress level and prevent from the crack

initiation when the plate is subjected to the tensile load.

Time: 16:45-17:00

Investigations of Bending Singularity Orders in a V-notched Composite Laminate Plate

Based on the Ressiner-Mindlin Theory

Dr. Chung-De Chen

Department of Mechanical Engineering, National Cheng Kung University, Tainan,

Taiwan

In this paper, the bending singularity at the apex of a V-notched composite laminate

plate is investigated. The anisotropy of the laminate is modeled by the Stroh formalism.

Based on the eigenfunction expansion method, the bending singularity orders can be

determined by solving an eigenvalue problem numerically. The singularity orders

depend on the plate angle, material orientation, material anisotropy and the laminate

stacking sequence. The comparison cases show that the material orientation should

avoid in order to reduce the bending singularity. The layers near the free surfaces

have more significant effects on the singularity order. The findings presented in this

paper are helpful in the design of the composite laminate with V-notch.

Time: 17:00-17:15

Numerical Simulation of Nitrogen Inductively Coupled Plasma Flow with Considering

the Radiation Heat Transfer

Assoc. Prof. Minghao Yu, Jiafeng Yao

Xi’an University of Technology, China

Numerical study of nitrogen inductively coupled plasma (ICP) was carried out with

considering the effect of the radiative heat transfer on the flow-field of a 10-kW ICP

torch. Two-dimensional compressible axisymmetric Navier-Stokes (N-S) equations that

took into account 5 species and 8 chemical reactions were solved to get the flow

properties. The far-field magnetic vector-potential equations were tightly coupled with

the N-S equations to describe the heating process. A four-temperature model was

employed to model thermal nonequilibrium process in the discharge torch. It was found

that the radiation tends to make the temperature field of the ICP flow more uniform.

The high-temperature area of the ICP flow became wider when the radiation heat

transfer model was considered in the simulation.

- 33 -

Poster Presentation

Saturday Morning, 30 December 2017, 10:30-11:30

* The certification of poster presentations, will be get when collect conference materials at Registration Desk, please ask

chair to sign it for you.

Entropy Analysis of a Low Bypass Turbofan Engine: A Case Study for

JT8D

Mr. Mehmet Emin CILGIN, Onder TURAN,

Faculty of Aeronautics and Astronautics, Anadolu University, Turkey

Aircrafts are preserving their importance owing to being the fastest and as

well as safety mode of transport. Thus, it is a necessity to improve

efficiency of aircraft engines. In this study, entropy and performance

analysis of a low-bypass aircraft engine (JT8D) are carried out. Entropy

values of fan/LPC outlet, HPC outlet, combustion chamber outlet, HPT

outlet, LPT outlet and exhaust outlet are 0.0897, 0.1443, 0.78, 0.8088,

0.8474 and 0.5073 kJ/kg.K, respectively. Propulsive, thermal and overall

efficiencies are 33%, 32% and 11%, respectively. Calculated data are

shown on thermodynamic property diagrams such as enthalpy-entropy,

temperature-entropy and pressure-volume. A clear perspective for potential

improvements of turbofan engines is aimed via these analyses.

Simulation and Effectiveness Analysis on One versus One Beyond Visual

Range Air Combat

Mr. LIU Haoyu, ZHANG Yunfei and LI Shihao

School of Aeronautic Science and Engineering, Beihang University, China

A kind of one versus one beyond visual range (BVR) air combat model has

been established, which includes functional models of radar, missile and

fighter and the process of several combat stages. Air combat effectiveness

ratio (ACER) is defined to analyse the result. The 2k factor design method

is used to design combat test case and analyses the influence of three

factors (fighter stealth character, missile range and flight height) on ACER.

Simulation result reveals that when RCS of one fighter is reduced from

0dBm2 to -10dBm2 which cannot remarkably affect the opposition

fighter’s radar detection distance and missile launch distance, the RCS

factor has small influence and the missile range factor has great influence.

When RCS of one fighter is reduced from -10dBm2 to -20dBm2, the

opposition fighter’s radar detection distance will be reduced and lead the

result of its missile launch distance be less than its missile range.

Compared with the former case, the effect of RCS factor increases and the

effect of missile range factor decreases. However, the effect of height is

not significant.

- 34 -

The Gradational Route Planning for Aircraft Stealth Penetration Based on

Genetic Algorithm and Sparse A-Star Algorithm

Mr. LI Maoquan, ZHANG Yunfei and LI Shihao

Beihang University, China

It is established for a gradational route planning algorithm which includes

two layers. The first layer makes use of genetic algorithm to obtain the

global optimal path by its global optimal characteristics. The second layer

makes use of A* algorithm to obtain the local optimal path by its dynamic

characteristic. When flying along the global optimal path, locating the new

threat and confirming its performance, the aircraft can plan the local

optimal path timely by A* algorithm. It is constructed for the cost function

with two goals of the range and the average detection probability, which is

used as the goal function for optimal path planning. Two paths that

obtained from two optimal methods are merged to construct the optimal

route comprehensively considering the threats and range. The simulation

result shows that the cost of new optimal route is lower than the original

optimal path obtained only by the genetic algorithm.It revealed that our

algorithm could obtain an optimal path when a new radar threas occured.

Energetic Efficiency and Power Calculation of PW4000 Turbofan

Engine

Mr. Hakan Aygun and Onder Turan

Anadolu University, Faculty of Aeronautics and Astronautics, Turkey

In this study, theory, methodology and example application are developed

and demonstrated for a PW4000 high-bypass turbofan engine in terms of

energy and performance perspective. For this aim, performance analysis is

performed for five main engine components at ≈260 kN thrust force.

Besides, overall efficiency of the turbofan is determined to be 33%, while

propulsive and thermal efficiencies of the turbofan are calculated to be

71% and 46%, respectively. Specific fuel consumption, another

performance parameter, is obtained to be 0.0383 kg/N.h. According to

measured engine data and related power equations, wasted power for the

fan and core exhaust and total airflow power of the engine are calculated

to be 8,256 kW, 7,281.16 kW and 54,929 kW, respectively. As a

conclusion, performance calculation of the PW4000 becomes main

motivation for a gas turbine propulsion system for medium-range air

transportation and aero-derivative cogeneration applications.

Nonlinear dynamics response of intrinsic continua beam by using point

interpolation meshless method

Assoc. Prof. Huan He and Panglun Liu

Nanjing University of Aeronautics and Astronautics, China

This paper reports on discretization formulations of geometrically exact

- 35 -

beam equations by using point interpolation meshless method. The

intrinsic beam theory, which is one of the exact beam formula, is quite

suitable to describe the large deformation of the flexible curved beam. The

strain and curvature are used to describe the configuration of the deformed

beam. Although the expression of the intrinsic beam equations is quite

simple and only with the first order nonlinear terms, however, it is very

difficult to solve. In order to solve the intrinsic beam equations in a

relative simple way, the point interpolation meshless method is applied to

the intrinsic beam equations to give a series of first order nonlinear

differential equations. Different from those equations by using finite

element method, only the differential of the shape functions are needed to

form the final discrete equations, which will bring to great advantage to

the computational efficiency. The accuracy of the presented method has

been evaluated by numerical example.

Dynamic Model Updating in Thermal Environment Using Pareto Optimal

Models

Dr. Cheng He and Huan He

Nanjing University of Aeronautics and Astronautics, China

Accurately determining the modal characteristics of these structures in a

high temperature environment is vital for supersonic vehicle and reentry

vehicle. However, the temperature–dependent characteristic of material

parameters and thermal stresses made an accurate dynamic model is

difficult to establish directly. In this paper, a structural model updating in

high temperature environment can be decomposed into temperature field

updating and dynamic structural updating based on hierarchical method.

Due to uncertainties arising from model and measurement errors, the

model updating problem is turned into a multi-objective optimization

problem that are consistent with the residues of modal frequency and

effective modal mass. Then, the metamodeling, support vector regression,

is employed to improve the efficiency of Pareto optimal models, and the

solution can be determined by Non-dominated Sorting Genetic

Algorithm-II. Finally, the proposed method is tested on an FE model of a

wing structure. The results of the study show that the developed method in

in a high temperature environment is capable of identifying the input

parameters of the temperature field and structure with good accuracy.

An Airborne Target Localization Algorithm Based on UKF and Optimal

Maneuver Strategy

Ms. Chunxiao Zhang and Xiaofeng Shi,

Beihang University, China

The airborne bearing-only passive target localization performance is

relevant with the specific filter and maneuver model. This paper presents a

combination of Unscented Kalman Filtering (UKF) with control inputs

and optimal route planning algorithm to improve the performance. Taking

the minimum trace of unbiased UKF estimation covariance matrix as

criteria, single-step heading traverse method is applied to reach every

optimal solution. A single flight path simulation and Monte Carlo analysis

- 36 -

validate that the optimal strategy can improve both the convergence and

localization accuracy.

Adaptive Command Filtered Integrated Guidance and Control for

Hypersonic Missile with Magnitude, Rate and Bandwidth Constraints

Mr. Liang Wang, Weihua Zhang, Ke Peng and Donghui Wang,

National University of Defense Technology, China

this paper proposes a novel integrated guidance and control (IGC) method

for hypersonic missile in terminal phase. Firstly, the system model is

developed with a second order actuator dynamics. Then the back-stepping

controller is designed hierarchically with command filters, where the first

order command filters are implemented to construct the virtual control

input with ideal states predicted by an adaptive estimator, and the

nonlinear command filter is designed to produce magnitude, rate and

bandwidth limited control surface deflection finally tracked by a terminal

sliding mode control with finite convergence time. Through a series of

6-DOF numerical simulations, it’s indicated that the proposed method

successfully cancels out the aerodynamics coefficient uncertainties and

disturbances in hypersonic flight under limited control surface deflection.

The contribution of this paper lies in the application and determination of

nonlinear integrated design of guidance and control system.

Analysis of the Problems Existing in Mechanical Structure Design of the

Legged Mobile Robot

Ms. MingJuan XIE, ChunYan ZHANG,XingLu YIN

Shanghai University of Engineering Science, China

Based on the analysis of the research background and current situation of

the legged mobile robots at home and abroad,in this paper we discusses

the existing research methods of the legged mobile robot in the

mechanical structure design; discusses the mainproblems in the design of

the mobile robot, and to focus on the emergence of instability and poor

adaptability and obstacle-surmounting performance of the legged mobile

robot to find the corresponding solution in the process of movement.

The effects of the use of single task-oriented maintenance concept and

more accurate letter check alternatives on the reduction of scheduled

maintenance downtime of aircraft

Ibrahim Ozkol, Caner Senturk

Faculty of Aeronautics and Astronautics,Istanbul Technical

University,Istanbul, Turkey

This paper provides a connection between an industrial problem of the

maximization of aircraft utilization and maintenance cost savings. A more

flexible structure is proposed to perform the maintenance not only during

scheduled periodic checks but also whenever the aircraft is on the ground

for any reason. The proposed method is the use of the single task-oriented

- 37 -

maintenance concept. The results obtained from a case study performed in

an airline company by using classical maintenance approach - rigid letter

check system and the single task-oriented maintenance concept are

compared to emphasize the benefits of the proposed concept. To help to

reduce scheduled maintenance downtime of aircraft, a software has been

developed to support the single-task oriented maintenance concept by

calculating more accurate and appropriate letter check alternatives for the

related maintenance task.

An ID-based Group Key Agreement Scheme for Controlling Access and

Privacy in Cloud

Jen-Ho Yang, Prof. Iuon-Chang Lin, and Po-Ching Chien

National Chung-Hsing University, Taiwan

As the population of cloud service, more and more people concerns the

privacy and security of cloud service. Therefore, an ID-based group key

agreement scheme is proposed. In this paper, the group key agreement

scheme is applied to the access control of cloud service. For achieving the

access control and the privacy of data, the data owner can determine who

can decrypt the encrypted data. In the aspect of computation cost, the

bilinear pairing is used to compute the session key and the symmetric

encryption is used to encrypt data in the scheme because of the bilinear

pairing and symmetric encryption have lower computation cost than

others. In the aspect of security, the scheme proposed in this paper not

only can assist two attacks: impersonation attack and man-in-the-middle

attack, but also can satisfy four security attributes: known-key security,

key control, unknown key-share and key compromise impersonation.

- 38 -

Listeners

Mr. Zhaoyue Chen

School of Aerospace Engineering, Beijing Institute of Technology, China

Prof. Li Liu

School of Aerospace Engineering, Beijing Institute of Technology, China

Prof. Stone Cheng

National Chiao Tung University, Department of Mechanical Engineering,

Taiwan

Mr. JinKwan Lin

National Chiao Tung University, Taiwan

Prof. Masashi KASHITANI

Department of Aerospace Engineering, National Defense Academy of

Japan

Prof. Guoyi He,

School of Aircraft Engineering, Nanchang Hangkong University, China

- 39 -

Prof. Qi Wang

School of Aircraft Engineering, Nanchang Hangkong University, China

Mr. MBOH ELVIS TEKEM

ARABI COMPANY QATAR W.L.L , QATAR

Prof. Souhwan Jung

Soongsil University, Republic of Korea

Mr.VINCENT MALINSON

SUZLON ENERGY LIMITED, India

- 40 -

Author Index Name Paper Session Page

A

Alexey G. Toporkov AE031 A-2 21

Alireza Alikhani AE003 A-2 20

An-Min Zhao AE014 A-1 18

B

Baoming Zhang AE027 A-1 19

Bing-Fei Liu AE014 A-1 18

C

Caner Senturk AE1004 P 36

Changmin Park AE015 B-1 25

Chao Gao AE007 B-2 30

Chao Li AE030 B-1 27

CHEN Keming AE012 B-2 31

Chen Ming AE013 A-1 18

Cheng He AE1007-

A P 35

Chengyu Ma AE3002 A-1 19

ChenHuan Pi AE018 A-2 21

Cheol Kim AE015 B-1 25

Chun-Der Cheng AE017 B-2 32

Chung-De Chen AE025 B-2 32

Chunxiao Zhang AE032 P 35

ChunYan ZHANG AE1002 P 36

Cong Li AE027 A-1 19

Cunyue Lu AE027 A-1 19

D

Daamanjyot Barara AE016 B-2 31

De-Shan Liu AE014 A-1 18

Dharmahinder Singh

Chand AE016 B-2 31

Di peng AE012 B-2 31

Donghui Wang AE042 P 36

Dongmei Wang AE004 B-2 29

F

Feng Li AE007 B-2 30

G

Gautam Ganesh AE016 B-2 31

GU Yunsong AE012 B-2 31

Guoyi He AE3002 A-1 19

H

Hajime Nakamura AE021 B-1 26

Hakan Aygun AE034-

A P 34

Hongyu Wang AE027 A-1 19

Huan He AE1006-

A P 34

Huan He AE1007-

A P 35

HUANG Wei-qing AE043 B-1 27

Huixiang Liu AE3002 A-1 19

Huo-Xing Liu AE030 B-1 27

I

Ibrahim Ozkol AE1004 P 36

Il'ya O. Akimov AE031 A-2 21

Iuon-Chang Lin S002 P 37

J

Jen-Ho Yang S002 P 37

Ji-Fu Tseng AE017 B-2 32

Jin Wen Goh AE040 A-2 22

JinKwan Lin AE018 A-2 21

K

Ke Peng AE042 P 36

Khin Thida San AE033 A-2 21

L

Li Liu AE005 B-2 29

LI Maoquan AE010 P 34

Li Qing AE038 A-2 22

LI Shihao AE008 P 33

LI Shihao AE010 P 34

Li Wan-li AE1008 A-1 17

Liang Wang AE042 P 36

LIU Haoyu AE008 P 33

Liu Jiangshan AE013 A-1 18

Liu Jinfei AE013 A-1 18

Liu Xiang-yong AE1008 A-1 17

M

Masanori

NISHIYAMA AE024 B-1 26

Masashi

KASHITANI AE024 B-1 26

- 41 -

Masato TAGUCHI AE024 B-1 26

Mehmet Emin

CILGIN

AE002-

A P 33

Minghao Yu AE041 B-2 32

Minghui Yao AE004 B-2 29

MingJuan XIE AE1002 P 36

Mingzhe Li AE015 B-1 25

Mohammad Hassan

Rahimian AE023 B-1 26

Mohsen Fathi

Jegarkandi AE003 A-2 20

N

Nam Seo Goo AE3004-

A A-2 20

Noa Mohamado AE031 A-2 21

O

Onder TURAN AE002-

A P 33

Onder Turan AE034-

A P 34

P

PAN Song AE043 B-1 27

Panglun Liu AE1006-

A P 34

Po-Ching Chien S002 P 37

Q

Qi Wang AE3002 A-1 19

R

Raghuraman

Srinivasan AE1003 B-2 30

Rouzbeh Moradi AE003 A-2 20

Rui Guo AE040 A-2 22

S

SAADON Syamimi AE020 B-1 25

Salman Bahrami AE023 B-1 26

Shohji Hamada AE022 A-1 18

Shulin Chen AE005 B-2 29

Si Chen AE1001 A-2 23

Sivachidambaram

Pichumani AE1003 B-2 30

Stepan N. Iljukhin AE031 A-2 21

Stone Cheng AE018 A-2 21

Su Myat Phyoe AE040 A-2 22

Sun Ju Mun AE033 A-2 21

Sun Zhijun AE012 B-2 31

Suraj Anand AE016 B-2 31

T

Tatiana V.

Kokuytseva AE031 A-2 21

Thanh Duc Dao AE3004-

A A-2 20

Thomas Jin-Chee

Liu AE017 B-2 32

V

Van Luong Le AE3004-

A A-2 20

Venkatraman

Ramamoorthi AE1003 B-2 30

Vsevolod V.

Koryanov AE031 A-2 21

W

Wei Zhang AE004 B-2 29

Weihua Zhang AE042 P 36

Wen Jingqian AE038 A-2 22

Woong Ryeol Yu AE3004-

A A-2 20

X

Xiaofeng Shi AE032 P 35

XingLu YIN AE1002 P 36

XU Zhang-fan AE043 B-1 27

Xu Zhi-qiang AE1008 A-1 17

Xudong Ren AE007 B-2 30

Xun Zhao AE027 A-1 19

Y

Yao Jiayu AE3001 A-2 23

Yingzheng Liu AE012 B-2 31

Yinli Liu AE004 B-2 29

Yoon Seok Chang AE033 A-2 21

Yoshifumi Yokoi AE009 A-1 17

Yoshifumi Yokoi AE022 A-1 18

Youchao Sun AE1001 A-2 23

Yun Luo AE3002 A-1 19

Yundong Guo AE1001 A-2 23

Z

ZHANG Yunfei AE008 P 33

ZHANG Yunfei AE010 P 34

- 42 -

Zhao Qian AE038 A-2 22

Zhao Wei Zhong AE040 A-2 22

Zhaoyue Chen AE005 B-2 29

Zhi-Hong Zhou AE030 B-1 27

Zijie Zhao AE007 B-2 30

Zou Hui AE014 A-1 18

- 43 -

One day tour in Yokohama

No.1 Yokohama Chinatown------ Largest Chinatown in Asia

Yokohama Chinatown is located in Yokohama, Japan, which is located just south of Tokyo. Its history is about

150 years long. Today only a few Chinese people still live in Chinatown, but it has a population of about 3,000 to

4,000. Most of the residents are from Guangzhou (Canton) but many come from other regions.

Yokohama Chinatown is the largest Chinatown not only in Japan but also in Asia (larger than Chinatowns in both

Kobe and Nagasaki) and it is one of the largest in the world[citation needed]. There are roughly 250

Chinese-owned/themed shops and restaurants scattered throughout the district, with the highest concentration

centered on a 300 square metre area.

No.2 Minato Mirai 21 ------ central business district of Yokohama

Minato Mirai 21, is the central business district of Yokohama, Japan. Initially developed in the 1980s, Minato

Mirai 21 was designed as a large master-planned development and new urban center planned to connect

Yokohama's traditionally important areas and commercial centers of Kannai and the Yokohama Station area.

Today, Minato Mirai is a major center for business, shopping, and tourism, attracting visitors and businesspersons

throughout the Greater Tokyo Area. The business district is host to several major hotels, office towers including

the Yokohama Landmark Tower, the Pacifico Yokohama convention center, art museums, and numerous cafés and

shops in shopping centers and along its central pedestrian mall.

- 44 -

No.3 Yokohama Red Brick Warehouse

The Yokohama Red Brick Warehouse is a historical building that is used as a complex that includes a shopping

mall, banquet hall, and event venues. The complex, officially known as the Newport Pier Tax Keeping Warehouse,

was originally used as customs buildings, and has two sections: Warehouse No.1 and No.2. It is operated by

Yokohama Akarenga Co. Ltd., and located at the Port of Yokohama in Naka-ku, Yokohama, Kanagawa, Japan.

Building No. 1 is regarded as a cultural facility, and is utilized as an event venue for art exhibitions, film festivals,

musical competitions and plays.[4] Building No. 2 houses a shopping mall and restaurant arcade, and a balcony

from which visitors can view the harbour opened on the 3rd floor in 2007. Other sightseeing spots including

Yokohama Chinatown, Minato Mirai 21, and Yamashita Park are located nearby.

No.4 Yokohama Landmark Tower

The Yokohama Landmark Tower is the second tallest building and 4th tallest structure in Japan, standing 296.3 m

(972 ft) high. It is located in the Minato Mirai 21 district of Yokohama city, right next to Yokohama Museum of

Art. Work on the building was finished in 1993. When built, it was the tallest building in Japan until it was

surpassed by Abeno Harukas in 2012. When opened, it had the highest observation deck in Japan.On the 69th

floor there is an observatory, Sky Garden, from which one can see a 360-degree view of the city, and on clear days

Mount Fuji.

The building was designed by the architecture and engineering division of Mitsubishi Estate, now Mitsubishi

Jisho Sekkei and Hugh Stubbins and Associates, later KlingStubbins. The tower contains what were at their

inauguration the world's second fastest elevators, which reach speeds of 12.5 m/s (41 ft/s)[1] (45.0 km/h (28.0

mph)). This speed allows the elevator to reach the 69th floor in approximately 40 seconds.[3] The elevators' speed

record was surpassed by elevators of Taipei 101 (60.6 km/h, 37.7 mi/h) in 2004.

- 45 -

No.5 Yokohama Hakkeijima Sea Paradise

Yokohama Hakkeijima Sea Paradise is an amusement park consisting of an aquarium, shopping mall, hotel,

marina and amusement rides. It is located in Kanazawa-ku, Yokohama, Japan. It opened for business on May 8,

1993. It is a pay-as-you-go theme park, having no gates or admission charges. Visitors have the option of buying a

day pass or paying for each attraction separately. With 4,770,000 visitors in 2007, it ranks sixth among Asian

amusement parks in terms of attendance.

MEMO

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