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ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
Message from the Chairman
I am extremely delighted to note that Department of Mechanical Engineering , I.T.S Engineering
College, Greater Noida is set to organize the First International Conference on Advancements
and Recent Innovations in Mechanical, Production and Industrial Engineering (ARIMPIE-2015)
in association with the Indian Society for Technical Education, New Delhi during April 10-
11,2015. It is my conviction that this conference will provide quick snapshot of major
developments and innovations in the subject area with special emphasis on technological
breakthrough, competing technologies on the horizon and some key innovations. It will also
expose students to the latest developments in the area of expertise and help them correlate with
the knowledge garnered during class room teaching.
I am sure this conference will provide an opportunity to the academicians, industrialists,
scientists and research scholars to present their view and exchange ideas on the above mentioned
subjects.
Finally, I would like to congratulate all the members of the organizing team for their persistent
efforts and commitments to make this event a grand one.
Dr.R.P.Chaddha
Chairman
I.T.S Education Group
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
Message from Organizing Chair
It is privilege and pleasure to welcome the conference speakers, presenters, delegates and
participants to the First International Conference on Advancements and Recent Innovations in
Mechanical. Production and Industrial Engineering ARIMPIE-2015. We would like to express
our personal gratitude to the sponsors and well wishers for their continued support as well as to
our students, faculty and staff who have worked with dedication for ensuring the success of the
Conference.
In the present day business environment technological edge and superiority is the major growth
engine for business. Academic institute provide the fertile ground for innovation and
technological breakthrough. Organizing conferences help in diffusion of knowledge and
exchange of ideas with the peer group.
We are fortunate to have received the support of the I.T.S Management, academic fraternity,
industry associates and sponsors. We thank one and all for the support and hope that we will
derive benefit from the deliberations in the conference.
We wish you all success in accomplishing the goals of the Conference.
Dr.Sanjay Yadav Dr.Vikas Dhawan
Organizing Chair ARIMPIE2015 Organizing Chair ARIMPIE2015
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
Message from Organizing Secretary
We are indeed privileged and delighted to host ARIMPIE-2015, the First International
Conference on Advancements and Recent Innovations in Mechanical, Production and Industrial
Engineering. This conference is aimed to provide a common platform for the interaction of the
academia and industry including personnel from research and development organizations.
The organizing committee, under the valuable guidance of our Director Dr.Vineet Kansal, has
been very active to ensure the successful organization of the conference. Special gratitude and
appreciation is due to the various track chairs as they are primarily responsible for the content
and conduct of the technical program. The Registrar, Dean Academics and faculty of I.T.S
Engineering College deserves special thanks for providing administrative and technical support
to ARIMPIE-2015. We wish to express a debt of gratitude to all the program committee
members and the outside reviewers. Thanks also to all those who submitted papers to the
Conference.
We heartily welcome all delegates, invitees, guests and participants to this conference.
Dr. Sanjay Mishra Mr. Manvendra Yadav
Organizing Secretary Organizing Secretary
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
I
Preface
Welcome to the First International Conference on Mechanical, Production and Industrial
Engineering ARIMPIE-2015. In order to improve the quality of living, implication of innovative
solutions and best practices in Mechanical, Industrial and Production Engineering have critical
role. In the near future Mechanical Engineering will be at the forefront in developing new
technologies. The prime goal of the conference is to promote research and developmental
activities in Mechanical, Production and Industrial Engineering. The conference aimed to
provide a common platform for professionals, academicians, researchers and industrialists to
share their knowledge and ideas for achieving focused development and advancements in
emerging field of these areas. It will help the participants to redefine their horizons in recent
innovation in these fields through technical paper presentations and panel discussions leading to
networking of participant organizations for effective collaboration in R & D and recognizing the
areas which require future research. The organizing committee believes that the conference will
assist the participants to connect with the pace of innovation in the Mechanical, Production and
Industrial Engineering.
This Proceeding is a compilation of quality papers accepted for presentation in the conference.
The organizing committee of ARIMPIE-2015 extends their thanks to the authors for accepting to
share their knowledge in these Proceedings. All the experts who peer-reviewed the papers are
most thanked for ensuring that quality material was published. The guidance given by the
members of the International Advisory Committee is greatly acknowledged. The organizations
associated with us are most sincerely thanked for making it possible for the Conference and its
Proceedings to be realized. Our special thanks to the Director of the college Dr. Vineet Kansal,
for providing an environment that was conducive for the smooth accomplishment of the editorial
work.
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
II
ORGANIZING COMMITTEE
Chief Patron
Dr. R. P. Chadha
(Chairman, I.T.S- The Education Group)
Patrons
Mr. Sohil Chadha
(Vice Chairman, I.T.S- The Education Group)
Mr. Arpit Chadha
(Vice Chairman, I.T.S -The Education Group)
Mr. B. K. Arora
(Secretary, I.T.S -The Education Group)
Dr Vineet Kansal
(Director, I.T.S Engineering College, Greater
Noida)
Organizing Chairs
Dr. Sanjay Yadav
Head, MED
Dr. Vikas Dhawan
Professor, MED
Organizing Secretaries
Dr.Sanjay Mishra
Associate Professor, MED
Mr. Manvendra Yadav
Assistant Professor, MED
Joint Secretaries
Dr.B.P.Sharma
Associate Professor, MED
Mr. Md. Kamal Asif Khan
Assistant Professor, MED
International Advisory Committee
Prof. Raj Kumar Roy, Cranfield University, UK
Prof. Mohammed Arif, University of Salford,
UK
Dr.Rajesh Piplani, Nanyang Technological
University, Singapore
Prof. Nikhil Ranjan Dhar, Bangladesh
University of Engineering and Technology,
Dhaka
Dr. Nandita Hettiarachchi, Ruhuna University,
Srilanka
Prof. R.K. Khandal, Vice Chancellor, Uttar
Pradesh Technical University, India
Prof. R.L.Sharma, Vice Chancellor, Himachal
Pradesh Technical University, India
Prof. R.S. Agarwal, Senior Advisor & Expert,
Ozone Cell, India
Dr.Sanjay Yadav, CSIR-National Physical
Laboratory, New Delhi, India
Prof. A.D. Bhatt, MNNIT Allahabad, India
Prof. Abid Haleem, Jamia Millia Islamia, New
Delhi, India
Prof. Anuj Jain, MNNIT Allahabad, India
Prof. Ashitava Ghosal, IISc Banalore, India
Prof. B. Sahay, IIT Patna,India
Prof. H.K.Raval, SVNIT Surat, India
Prof. Mohd. Islam, Jamia Millia Islamia, New
Delhi, India
Prof. M.D.Singh, MNNIT Allahabad, India
Prof. Mohd. Muzaffarul Hasan, Jamia Millia
Islamia, New Delhi, India
Prof. Puneet Tandon, IITDM Jabalpur, India
Prof. R.A.Khan, Jamia Millia Islamia, New
Delhi, India
Prof. R.S. Jadoun, G. B. Pant University of
Agriculture & Technology Pantnagar, India
Prof. Ravi Kumar, IIT Roorkee, India
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
III
Prof. S.K. Garg, Delhi Technological University,
India
Prof. Sanjay, NIT Jamsedhpur, India
Prof. Sanjay Sharma, NITIE Mumbai, India
Prof. Sehijpal Singh Khangura,GNDDC
Ludhiana, India
Prof. Sudhir Kumar, NIT Kurukshetra, India
Prof. Uday Shanker Dixit, IIT Guwhati, India
Prof. V.K. Jain, IIT Kanpur, India
Prof. Vinod Yadava, MNNIT Allahabad, India
Dr.Inderdeep Singh,IIT Roorkee, India
Dr.Narayan Agarwal,Delhi Institute of Tool
Engineering, New Delhi, India
Dr. P.M. Pathak, IIT Roorkee, India
Dr. Pulok M.Pandey, IIT Delhi, India
Dr. Vijay Pandey, BIT Mesra, Ranchi, India
Dr. Alok Kumar Das, ISM Dhanbad, India
Dr. Atul Thakur, IIT Patna, India
Dr. Akhilesh Barve, IIT Bhubaneswar, India
Dr. Rakesh Sehgal, NIT Hamirpur, India
Dr. Siddhartha, NIT Hamirpur, India
Dr. Varun, NIT Hamirpur, India
Mr. Arvind Sinha, SAS Motors, India
Mr. Deepak Maini, Cadgroup, Australia
Mr. R. K .Malhotra, SMC Pneumatics (India)
Pvt. Ltd, India
Mr. Raj Kumar Soni, Raj Soni & Co., India
Mr. Shraman Goswami, Honeywell Technology,
India
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
IV
TABLE OF CONTENTS
MECHANICAL Vol. 1
S. No. Paper Title and Author(s) Page
No. 1 Shape Oscillations of a Particle Coated Bubble During Rise in a Liquid Column
Prithvi R. Y., SabitaSarkar
1
2 Tensile Behaviour of 3-Ply Laminate Composite of Sheet Metals
Vijay Gautam, Bijender Prasad
7
3 Stress Analysis of Pelton Bucket using Mechanical APDL
Sonendra,NamanAgarwal, T.S.Deshmuk
13
4 Ships Steering Autopilot Design by Nomoto Model
Pradeep Mishra, S K Panigrah ,Swarup Das
19
5 Material Selection in Bearing Industry Using Multi Criteria based TOPSIS
Methodology
J. S. Karajagikar, R. R. Manekar
25
6 Data Acquisition and Monitoring of EMG (Electromyogram) Signals
MrinalJyotiSarma, RichaPandey
32
7 Sustainable Application of Compound Parabolic Solar Concentrator
D.K.Patel,P.K. Brahmbhatt
37
8 Effect of Radiative Heat Transfer Term in Weak NonLinear Waves in Fluid With Internal State Variables
Nahid Fatima
45
9 Investigation to Compare Heat Augmentation from Plane, Dimpled and Perforated
Dimple Rectangular Fins using ANSYS
Sachin Kumar Gupta, Harishchandra Thakur
50
10 Dynamic Response of Selected Fruits using Laser Doppler Vibrometer
JitendraBhaskar, Anand Kumar, Bishakh Bhattacharya
59
11 Experimental Study of Comparison of Simple VCRS and VCRS with Phase Change
Material(PCM) as Potassium Chloride (KCL)
TalivHussain, SahilChadha, Gaurav Singh, Jaggi,Sourabh,Gourav Roy
63
12 Study of Fatigue Life Calculation of Steel under Various Loading Condition
Anil Kumar , AbhishekPandey
67
13 Experimental Investigation of ThermalPerformance of Liquid Flat Plate Collector by
Comparing Single Glass Sheet with the Double Glass Sheet
TalivHussain, Wasiur Rahman, Saddamul Haque, Rocky Singh Labana, Md.Sabbir
Ali
71
14 Effect of Phase Change Material (PCM) as Sodium Chloride (Nacl) in VCRS System
as Compare to Simple VCRS System.
TalivHussain, Sourabh, NeerajKatoch, SahilChadha, Rahul Wandra
76
1. Preface I 2. Organizing Committee II
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
V
15 Experimental Analysis of A Waste-Heat-Utilization-Strategy using Thermoelectric
Device in C.I. Engine
R. Srivastava, S.K. Dhiman, J.V. Tirkey
80
16 Effect of Various Cut-Out on Buckling Analysis of Laminated Composite Plate using
FE Simulation
Rekha Shakya, Tushar Sharma, Rajendra Bahadur
85
17 To Evaluate the Performance of VCRS System by Comparing Lesser Superheated
Refrigerant(R-134a) to Higher Superheated Refrigerant (R143a)
Rahul Wandra, TalivHussain, JagannathVerma, Arjun Sharma,Gourav Roy
91
18 Kinematic Design Optimization of Planer-Link Mechanism Based Manipulator
Jagdish M Prajapati
96
19 In-Plane Free Vibrations of Symmetrically Laminated Rectangular Composite Plates
Kumar Pankaj ,UjjwalBhardwaj,Priyanka Singh 101
20 Experimental Investigation of Comparison of Air Cooled and Water Cooled Condenser
Attached with Cooling Tower
Gourav Roy, TalivHussain, Rahul Wandra
117
21 Computational Fluid Flow Analysis of High Speed Cryogenic Turbine using CFX
SushantUpadhyay, ShreyaSrivastava, SiddharthSagar, Surabhi Singh, Hitesh Dimri 122
22 Thermal Analysis of Various Perforated Tree Shaped Fin Array using ANSYS
Sachin Kumar Gupta, Rahul Singh, DivyankDubey, Harishchandra Thakur
129
23 A Review on the Analytical Analysis and Modeling of Earth Air Tunnel Heat
Exchanger
JagjitKaur, HarminderKaur
137
24 Ecoflush - Wastewater Recycling and Rainwater Harvesting Toilet Flush System
Mukesh Roy, AyushGoyal, Vivek Kumar
143
25 Experimental Investigation of Enhancing the COP of VCRS System by using Cooling
Tower
Gourav Roy,TalivHussain, Rahul Wandra
147
26 Improvement in Thermal Efficiency of a Compression Ignition Engine using A Waste
Heat Recovery Technique
Aashish Sharma, Ajay Chauhan, HimanshuNautiyal,Pushpendra Kumar Sharma,
Varun
152
27 Motion Control System of Dc Motor Drive Through PID Control
Pragya Singh, HemantChouhan
161
28 Effect of Subcooling in VCRS as Compared to Simple VCRS System
TalivHussain, Arjun Sharma ,Navin, Rahul Wandra, Gaurav Roy
167
29 Comparison of Different Failure Theories of Composite Material: A Review
SupriyaKabra, N.D. Mittal
174
30 Use of Polymer Matrix Composites for Conventional Steel Drive Shafts: A Study
Yusuf Abdulfatah Abdu
179
31 Experimental Investigation of Comparison of VCRS with Phase Change Material as
Sodium Sulphate (Na2SO4) and Simple VCRS System.
Rahul Wandra, Taliv Hussain, Gaurav Singh Jaggi, Sourabh,Gourav Roy
187
32 Behaviour of Polymer Matrix Composite under Different Environmental Conditions
Pathak, ShubendraNathShukla,VikasChaudhary, Kaushalendra Kr Dubey
191
33 Study of Flow Field of River for Hydro Kinetic Turbine Installation
A. Mishra, A.Kumar, M. Singhal,
195
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
VI
34 A Review on the Performance of the Nano Fluid Based Solar Collectors - Solar Energy
Kapil Sharma, Satnam Singh, ManvendraYadav, Sanjay Yadav, Naveen Mani Tripathi
201
35 Study of Hardness & Microstructure of AISI 1050 Medium Carbon Steel after Heat
Treatment Processes
Sanjeev Kumar Jaiswal, Rajesh M, .T.Sharma, Vineet Kumar
213
36 Condition based Predictive Maintenance on board Naval Ships
S Jaison, KarajagikarJayant
220
PRODUCTION & INDUSTRIAL Vol. 2
S. No. Paper Title and Author(s) Page
No. 37 Soft Computing Technique for Product Design Suggestion in Smart Manufacturing
Industry
Jitesh Kumar Khatri, Jyoti Kumar
228
38 Experimental Investigation of Electrical Discharge Face Grinding of Metal Matrix
Composite (Al/Sic)
Ram Singar Yadav, Gyan Singh, Vinod Yadava
233
39 Heuristic for Enabling Lean Characteristics in Cellular Manufacturing using
Reconfigurable Machines
Rajeev Kant, L N Pattanaik, Vijay Pandey
240
40 Finite Element Analysis of Laser Beam Percussion Drilling of TBC Superalloys
Km Afsana, VinodYadava
245
41 Dynamic Modelling and Machining Stability in A New Mill-Spindle Design for Drilling
Machine
JakeerHussain, Srinivas J
252
42 An Experimental Investigation of Travelling Wire Electrochemical Spark Machining
(TW-ECSM) of Epoxy Glass Using One-Parameter-At-A-Time (OPAT)
Vevek Kumar, VinodYadava
258
43 Experimental Study of Electrical Discharge Machining on Stainless Steel Workpiece
using One Parameter at A Time Approach
Param Singh,VinodYadava, Audhesh Narayan
264
44 Dry Sliding Wear Behaviour of Mg/Tip (Mg)-Based Composite Obtained Through P/M
Route
SanketPatro, M.Appoothiadigal, B.K.Raghunath
270
45 Effect of Magnetic Field on Electrode Wear Ratio in Electro-Discharge Machining
Govindaraju Anand, Komaraiah, S.Satyanarayana, Manzoor Hussain
276
46 A Quantitative Analysis of Modular Manufacturing in Garment Industry by using
Simulation
B.Sudarshan, D. NageswaraRao
281
47 Emerging Modelingand Simulation Techniques for Friction Stir Welding- A Review
PrashantPrakash, Shree PrakashLal, Sanjay Kumar Jha
288
48 Preparation and Mechanical Properties of Sintered Zrb2-Graphite Composites by Spark
Plasma Sintering (SPS) Method
NiteshKuma, Binay Kumar,Lokesh.C. Pathak
296
49 ANN Modelingand Multi Objective Optimization of Electrical Discharge Machining
Process
SanjeevKumarSinghYadav, DeepakAzad
300
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
VII
50 Optimization of Aluminium Die Casting Process using Artificial Neural Network
SanatanRatna, SwetNisha
310
51 A Review on Sisal, Jute and Bamboo Based Natural Fibers
Amrinder Singh Pannu, Sehijpal Singh, VikasDhawan
315
52 Multiobjective Optimization for Wire EDM of WC-Co Composite using GRA with
Entropy Measurement
Sachin Dev Barman, Ajay Suryavanshi
321
53 Optimization Of Electro Discharge Machining of Superalloys and Composites: A
Review
AmritShiwani, Amit Sharma
331
54 A Investigation of Machinability of Inconel 718 In EDM using Different Cryogenic
Treated Tools: A Review
Pradeep Joshi, Shiv DayalDhakad
340
55 Present &Future of Automation in Automotive Industries.
HemangSolanki, K.V.Parmar
349
56 Friction Stir Welding of AluminumAlloys 6xxx
Naveen Gadde, ShikharGoel, PiyushGulati
356
57 Development and Characterization of Green Composites: A Review
Jai InderPratap Singh, VikasDhawan, Sehijpal Singh
366
58 Study of Mechanical Properties of Rice Husk Composites
V K Joshi, V. Upreti, A., Chaudhary
374
59 An Overview of Turning Process
Monika Saini,Ravindra Nath Yadav, Sunil Kumar
377
60 Research and Developments in Laser Beam Machining A Review Bhaskar Chandra Kandpal, Nilesh Ramdas, Rakesh Chaurasia, Abhishek singh,
Vishal Rawat, Saatvik Singh
387
61 Effect of Transverse Weld Feed Rate on Microstructure and Tensile Properties of FSW
Weld of AA6061
Ashwani Kumar, R S Jadoun
393
62 Modelling and Simulation of Temperature Distribution in Laser Cutting of Ti-Alloy
Sheet
ShivaniPandey, Arun Kumar Pandey
399
63 To Study the Effect of Various Parameters on Finishing of Inner Surfaces of Brass
Tubes using Magnetic Abrasive by RSM
Jai InderPratap Singh, VikasDhawan, Sehijpal Singh
405
64 Simulation of Hole-Taper And Material Removal Rate Due to Single Pulse Laser Beam
Drilling
Sanjay Mishra, VinodYadava
416
65 Analysis of Process Parameters of CNC Lathe Turner by Response Surface
Methodology RichaSaxena, AbhishekPandey
422
66 Modelling of Electro-Discharge Machining of Difficult-to-Machine Materials: An
Overview Achal Gupta,AdityaAgrawal, Amit Sharma
429
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
VIII
INDUSTRIAL Vol. 2
S.No. Paper Title and Author(s) Name
Page
No. 67 Urban flooding and its risk associated with governance and management strategies: a
case study of Anand District, Western India
Pankaj Kumar, Srikantha, Herath, Ram Avtar, Kazuhiko Takeuchi
438
68 Ant colony optimization for scheduling of PCBs using single machine
Akshaye Malhotra, Vijay Pandey, S.K. Sahana, Somak Datta
441
69 Assessing the Success of Six Sigma: An Empirical Study
S. K. Tiwari, R. K. Singh, S. C. Srivastava
448
70 Product Development by Using Modular Design Structure Matrix
Puneet Saini, Ayush Dubey, Vijay Pandey
462
71 Design of a simple Vending Machine using Radio Frequency Identification
(RF-id)
Sunil Kumar, Richa Pandey
468
72 Imperatives of Green Manufacturing
Abhishek Kumar Singh, Sanjay Kumar Jha, Anand Prakash
472
73 Understanding Quality In Home Based Brassware Manufacturing Units in India
Kapil Deo Prasad, Sanjay Kumar Jha, Ritesh Kumar Singh
479
74 Application of Lean Manufacturing to Improve the Electronics Industry in Egypt: a
Case Study
Ali Abd El-Aty , Ahmad Farooq , Azza Barakat , Mohamed Etman
484
75 Solving Multi-Objective Problem on Supply Chain Performance Measure by multi-
Objective Evolutionary Algorithm
Susmita Bandyopadhyay, Indraneel Mandal
490
76 Multi-objective Goal Programming and its Applications: A review
Jyoti, Himani Mannan
496
77 Modeling the Individual/Group Knowledge Sharing Barriers: An Approach of
Similarity Coefficient
B P Sharma, Harsh Gupta
502
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
1
1. SHAPE OSCILLATIONS OF A PARTICLE COATED BUBBLE
DURING RISE IN A LIQUID
COLUMN
Prithvi R.Y
Department of Metallurgical and Materials
Engineering
Indian Institute of Technology Madras
Chennai, India
Sabita Sarkar
Department of Metallurgical and Materials
Engineering
Indian Institute of Technology Madras
Chennai, India
sabita.sarkar@iitm.ac.in
Abstract Particle coated bubble and its stability plays a major role during particle
recovery in flotation process. A rising bubble
undergoes shape oscillations which are subjected
to change when particles are coated on the
surface of a bubble. Experiments were
performed to understand the effect of particle
coating on a rising bubble in a liquid column.
Hydrophobic Low density polyethylene particles
were used to coat the bubble surface and water
was used as liquid medium. Two images (one
direct and mirror image) were taken for all
position during rise of the bubble. Effect of
different fraction of particle coating on the
bubble surface oscillations was studied. It is
observed that the shape oscillations of bubbles
are arrested as coating fraction increased from
10% to 50% with the latter undergoing almost
no deformation in shape. The bubble in this case
behaves like a rigid body and exhibits pure
rotation as it moves up.
Keywordsshape oscillations; particle coated bubble; single bubble rise ; coating
fraction.
I. INTRODUCTION
Bubble flotation in presence of particles is a
phenomena which has wide spread application
like waste water treatment, petrochemical plants,
froth flotation process, paper industry and in
refining operations like secondary steel making
process. Understanding the behaviour of bubble
motion and its characteristics in presence of
particles is a key step in evaluating preliminary
variables like air flow rate, bubble size, particle
size etc. with respect to its application in each
field. A significant amount of research has been
carried out in understanding the behaviour of a
single bare bubble rising in a fluid column [2,6].
The theory behind shape oscillations of a single
rising bubble has been given in detail by several
researchers [1,3 & 5]. However motion of
particle coated bubble in liquid medium is not so
evident in literature. In this work, motion of
particle coated single bubble was studied
experimentally. The effect of particle coating on
the bubble surface oscillation and the overall
bubbly motion was main focus of this study.
Strongly hydrophobic polymeric Low Density
Polyethylene (LDPE) particles were chosen with
interest to alumina inclusions present in molten
steel [4]. The shapes of bubbles were chosen in
the ellipsoidal regime which is commonly used
for removal of alumina inclusion in tundish [7].
II. EXPERIMENTAL METHODOLOGY
In order to study the shape oscillations of single
bubble during rise with particles coated on the
bubble surface, a bubble column made of plexi-
glass was fabricated. A schematic representation
of the experimental set-up is shown in Figure 1.
The tank comprised of two compartments
located one below the other. Initially the tank
was filled with distilled water up to a height of
0.55 m in the presence of polymeric LDPE
particles inside the lower compartment. The
particles which have specific gravity of 0.92
were prevented from floating to the upper
compartment by providing a slide door whose
opening was controlled manually. An air bubble
was held at the tip of a nozzle using an infusion
pump and the particle-water mixture was stirred
inside the compartment with the help of an
impeller arrangement powered by a universal
motor. The speed of rotation of the impeller and
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
2
duration of rotation controlled the coating
fraction of particles on the bubble surface. In
this study the size of LDPE particles chosen
were from 150-210 microns and the bubble sizes
were 6.8 and 4.2 mm. After allowing sufficient
time for the particle-water mixture to reach a
quiescent state the slide door was opened and the
air pump was operated again. The particle laden
bubble was detached from the nozzle and moved
upwards due to buoyancy.
A test section between the heights 0.019 m to
0.028 m in the upper portion of the tank was
illuminated with white coloured diffuse back
lighting. This was the region where the particle
coated bubble behaviour was studied. A mirror
was placed inside the tank at an angle of 45 to the camera axis. Light was projected on to the
mirror using a screen as a reflector and this
method provided back lighting for front view
where the bubble appeared white with dark
background and the side (reflected) lighting
illuminated the mirror image. In this way both
the front and side views of the bubble could be
obtained using a single camera placed in front of
the experimental setup.
The bubble rise and shape oscillations was
captured using a CMOS camera (Teledyne
Dalsa) having a frame rate of 300 frames per
second and a resolution of 640 480 pixels. The
images recorded were originally in greyscale
format.
The greyscale images were then converted
to binary format in subsequent steps by the
method of intensity thresholding, using Matlab-
14 software. At these stage properties like major
axes, minor axes, centroid, and bubble boundary
were measured using Matlab 14 - image
processing toolbox. In order to determine the
particle coating fraction on the bubble, the area
of particle coverage was determined by fitting a
closed spline around the periphery of the region
covered with particles using Image J-image
processing software.
III. RESULTS AND DISCUSSION
A. Behaviour of Particle coated Bubble
Bubbles with different extent of particle
coating and at different times were observed
during the experiments. In case of the bubble
with 10% particle coating at the surface,
oscillations were altered and reduced drastically
from the case of that of bare bubble. The
oscillations were accompanied by rotation of the
bubble as it moved upwards. The region where
the interface was coated with particles showed
no surface oscillation and behaved like solid
surface. The surface oscillations were prevalent
only at the regions where there were no
particles. This altered the overall oscillating
behaviour of the bubble.
When the extent of coating on the bubble surface
increased to almost half of the bubble surface
area, the oscillations were completely arrested.
The polymer particles completely retarded the
surface deformation and the bubble did not
undergo any shape oscillation during rise.
Instead the bubble exhibited only rotation about
its minor axis. The flow past the bubble at the
Figure 1. Schematic of the Experimental Set-up
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
3
boundary experienced no slip at regions where
the surface retardation had occurred. Visual
images of a bubble of 6.8 mm diameter with
different particle coatings and at different times
are compared and shown in Figure 2. The
particle coating on the bubble increases drag
force that it experiences and reduces the rise
velocity.
Experiments were done with a bubble having
diameter of 4.2 mm (Figure 3) and a similar
behaviour was observed. The only difference
was that the amplitude of oscillations undergone
by the 4.2mm bubble was comparatively lesser
than that of the 6.8mm bubble. The rise velocity
in this case is more when compared to that of
6.8mm diameter bubble, as coating fraction is
more and the bubble area is lesser. The force due
to buoyancy for the 4.2mm bubble exceeds the
drag force.
B. Effect of particle coating on shape
oscillations
The shape oscillations of bubbles are
generally expressed in terms of spherical
harmonics with 2,0 and 2,2 as the dominant
modes [3]. These two modes are the dominant
modes of shape oscillation for an ellipsoidal
bubble. Mode 2,2 shape oscillations of the
bubble are axisymmetric in nature. In this mode,
the capillary wave is assumed to travel around
the equator of the bubble and is characterized by
the ratio of major axes obtained from the direct
image (dd) to the major axis of that from the
mirror image (dm), R=dd/dm. The interpretation
of this mode of oscillation is that the bubble is
an ellipsoid rotating about its minor axis as it
travels vertically upwards and as it does a 2-D
projection of the 3-D bubble in either the front
or side plane will constitute major axes of
different lengths. Thus the ratio of major axes R
interprets change in the major axes length due to
rotation about its minor axes.
Figure 4 shows mode 2,2 oscillations for
bare bubble and 10% particle coated bubble. The
6.8 mm bubble shows a distinctive difference in
oscillation between the bare bubble and a
particle coated bubble, whose values of R are
varying from 0.5 to 1.5 for a bare bubble and
limited from 0.8 to 1.2 for the particle coated
bubble. This is an indication that the particle
coating has a decreasing effect on the extent of
elongation of the major axes. However for the
4.2 mm bubble size, particle coating seems to
have resulted in increased length of one of the
major axis (one seen from the direct image) as
the value of R remains always greater than unity.
t = 1 s
t = 1.012 s
t = 1.024 s
t = 1 s
t = 1.012 s
t = 1.024 s
t = 1 s
t = 1.012 s
t = 1.024 s
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
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Figure 2. Images of a 6.8 mm bubble for a time up to 0.036 s A) bare bubble undergoing shape deformation B)
10% coated bubble undergoing partial deformation C) 50 % coated bubble with no deformation
Figure 3. Images of a 4.2 mm bubble for time up to 0.036 s A) bare bubble undergoing shape deformation B)
10% coated bubble undergoing partial deformation C) 50 % coated bubble with no deformation
t = 1.036 s t = 1.036 s t = 1.036 s
t = 1.012 s
t = 1.024 s
t = 1.036 s t = 1.036 s
t = 1.024 s
t = 1.012 s
t = 1 s t = 1 s
t = 1.012 s
t = 1.024 s
t = 1.036 s
A B C
t = 1 s
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
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Figure 4. Plot of R vs time for bare bubble and 10 % particle coated bubble. A) 4.2 mm bubble B) 6.8 mm bubble
Figure 5. Plot of Deq vs time for bare bubble and 10 % particle coated bubble. A) 4.2 mm bubble B) 6. 8 mm bubble
Mode 2,0 shape oscillation is represented by
equivalent major axis defined as deq = (dd dm). This is an interpretation of the bubble
fluctuating from oblate spheroid to prolate
shape. In reality it does not transform
completely to prolate shape but as it tends to
oscillate in the 2,0 mode with alternating
elongation and contraction of the major axes.
This mode of oscillation is non-axisymmetric
in nature and the capillary waves are assumed
to be moving around the bubble from one end
of the bubble pole to another. Thus it is
characterized by obtaining an equivalent
diameter of a circle whose surface area is the
same as that of the ellipse in the cross-section
plane containing the two major axes (Deq).
It can be seen from Figure 5 that in the case of
a bare bubble as well as partially coated
bubble the amplitude of 2, 0 mode of
oscillation is greater for the size
corresponding to 6.8mm bubble size since it
naturally has greater major axes lengths. For
this bubble size when particles are coated the
elongation in major axis length gets reduced
since the particles inhibit wave action at the
bubble surface and behave as a rigid body.
For the 4.2mm bubble size the arrest in major
axes shrinkage is seen more predominantly as
there is a drastic decrease in amplitude of Deq
of particle coated bubble. The complete
Deq Deq
Time (s) Time (s)
A B
B A
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
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prevention of surface deformation when
almost half of the bubble surface area was
coated can be evidently seen in the images in
Figure 2C and Figure 3C and it is
inappropriate to
use surface harmonics to describe such a body
which does not undergo shape oscillation. As
the bubble surface deformation is completely
arrested the restoring capillary force is
retarded preventing any further shape
oscillation.
IV. CONCLUSIONS
LDPE particles do not detach from the bubbles for both sizes of 4.2mm
and 6.8mm due to shape oscillations
during rise in the static liquid column.
When the coating fraction on the bubbles is as mild as 10 %, the bubble
surface deformation occurs only at
regions, where particles are absent.
Thus overall oscillation in amplitude
is reduced
The reduction in elongation of major axes is more for a particle coated
smaller ellipsoidal (4.2mm size) than
the larger ellipsoidal bubbles (6.8 mm
size).
Heavily coated bubbles with coating fraction as high as 50%, shows no
deformation behaviour, instead they
behaves like a rigid body undergoing
pure rotation during rise.
V. REFERENCES
[1] C. Brucker, Structure and Dynamics of the wake of the
bubbles and its relevance for bubble
interaction, Physics of fluids, vol. 11(7), pp. 1781-
1796, 1999.
[2] P.C. Duineveld, The rise velocity and shape of bubbles
in pure water at high Reynolds number, J.Fluid Mech, vol
292, pp. 325-332, 1995.
[3] K. Lunde, R.J. Perkins, Shape Oscillations of Rising
Bubbles, Applied Scientific Research, vol.58, pp.387-408,
1998
[4] J.P. Rogler, Modeling of inclusion removal in a tundish
by gas bubbling , M.S. Thesis, Ryerson University,
2001.
[5] C. Veldhuis, A. Biesheuvel , L. van
Wijngaarden, Shape oscillations on bubbles rising in clean and
in tap water, Physics Of Fluids, vol.20, pp. 1-12, 2008.
[6] A.W.G de Vries, A. Biesheuvel, L. van
Wijngaarden,
Notes on the path and wake of a gas bubble rising in pure
water, International Journal of Multiphase Flow,
vol.28(11), pp.1823-1835, 2002.
[7] L.Zhang, S.Taniguchi, Fundamentals of inclusion
removal from liquid steel by bubble
Flotation, International Materials Reviews, vol.
45(2), pp.59-82,
2000.
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
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2. TENSILE BEHAVIOUR OF 3-PLY LAMINATE COMPOSITE OF
SHEET METALS
Vijay Gautam1, Assistant Professor,
Department of Mechanical Engineering, Delhi
Technological University, Delhi-110042. Email:
vijay.dce@gmail.com
Bijender Prasad2, Research scholar,
Department of Mechanical Engineering, Delhi
Technological University, Delhi-110042. Email:
bijendra121@gmail.com
Abstract- Recently, clad metallic materials,
consisting of two or more layers, have been
preferred in various industrial applications
because of their unique corrosion resistance,
specific strength, and surface properties. The
present study has been carried out on three ply
composite laminate, containing AISI304L
austenitic stainless steel on one side and
AISI430 on the other side with AA1050 in the
core of the blank. Apart from excellent corrosion
and mechanical properties of stainless steel three
ply composite laminate possesses exceptional
thermal and electrical conductivities, which
makes it useful for utensils formed by deep
drawing process. Circular blanks of composite
laminate, produced by cold roll bonding, with a
combined thickness of 2.5mm, were procured in
the annealed condition from a leading
manufacturer. To ensure the bond strength of 3-
ply AISI304/AA1050/AISI430 sheets, peel tests
on various specimens were performed according
to ASTM-D1876-08 standard. Tensile samples
as per ASTM E8M standard, were laser cut in
three different directions i.e. parallel, inclined at
45 and transverse with respect to rolling
direction. Tensile specimens were tested to study
the deformational behaviour in uniaxial tension,
on a 50kN UTM.
Keywords- Clad metals; Three ply laminate
composite; cold roll bonding; peel test; tensile
behavior.
I. INTRODUCTION
With the advancement in technology in
forming with sheet metals, new clad materials
have been evolved and designed for various
industrial applications such as automobile,
aerospace and electrical industries. These
laminated sheets consist of different kind of
sheet metals with different mechanical, physical
properties and specifications to suit the various
applications. Various parameters such as
material type, thickness ratio, arrangement and
multiplicity of the metals, surface preparation,
bonding parameters and post heat treatment
results in unique deformational behavior [1-5].
Although, Clad sheets have been produced by
several solid state bonding methods such as
diffusion, explosive and roll bonding but cold
roll bonding (CRB) is the most efficient and cost
effective [6,7]. Many researchers have
contributed significantly on the various issues
related to formability of roll bonded clad sheets.
In the recent development of the clad sheets,
most widely used material combinations are Al
with Cu, Al-Fe, Al with stainless steel, Zn- Al
with stainless steel, Al-Cu with steel, Ti with
steel etc. [8,9]. Akramifard et al 2014 carried out
experimental studies on effect of reduction and
subsequent annealing temperatures on
mechanical properties and bond strength of three
layered AA1050-304L-AA1050 clad sheets,
during roll bonding. An important contribution
of their work was the correlation of tensile and
peel test on the basis of principles of mechanics
of materials. The mechanical properties of some
laminated composite sheets, mainly of stainless
steel/aluminium sandwich sheets, have been the
subject of examination for many years. Choi et
al. 1997 experimentally investigated the
deformation behaviour of Al-STS430 bi-layer
clad sheets under uniaxial tension and concluded
that a difference in planar and normal anisotropy
results in the warping of edges of tensile
specimens. The material property of the
laminated sheet changes in the thickness
direction, their deformation behavior should be
affected by the blank placement position during
forming by deep drawing, i.e. which side of the
sheet would contact punch or die. Because of
such interesting formability issues, the behavior
of laminated sheets is the subject of much
research. However, only a few studies have
discussed the combination of 3-ply clad sheets
of AISI304/AA1050/AISI430. In view of the
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above the present study deals with the tensile
behaviour of 3-ply laminate composite.
II. METHODOLOGY
A. Selection of material
Selection of material is based on the
increasing popularity of multi ply clad sheets in
deep drawn utensils, owing to the advantages of
excellent formability, good surface finish of
class of 2B, uniform heating and better heat
transfer. Circular blanks of 3-ply clad sheet of
AISI304/AA1050/AISI430 material of effective
thickness of 0.4, 1.5 and 0.6mm respectively,
that are joined by roll bonding and thermal
treatment, due to a metallurgical bond under
high pressure, was procured from a leading
supplier in India. The chemical composition of
individual sheets were obtained by
spectrometry- analysis and are given in Table 1.
B. The peeling test
To investigate the bond strength due to CRB,
the peeling test was performed according to
ASTM-D1876-08 standard (subsized).
Specimens for the peel test were laser cut in the
sub-size of 160X 25 mm due to limited
availability of the material. Since it is difficult to
detach the bonded sheets mechanically, one end
of the each specimen was immersed in the
solution of sodium hydroxide to dissolve
aluminium. The remaining length with intact
bond was used for the peel test as shown in the
Fig. 1. The specimens were prepared in such a
way that each bonded sheet of steel i.e. AISI304
and 430 be peeled from aluminium bond
respectively. The stainless steel sheet to be
peeled was held in the lower fixed jaw and the
rest with the upper movable jaw fixed with the
cross -head on the 50kN UTM. All the tests were
conducted at a cross head speed of 10mm/min.
Fig. 1. Peel test arrangement on 50kN UTM
C. The tensile test
Most common approach to characterize the
behaviour of a material is by conducting uniaxial
tensile tests. In this work, simple tension tests
were carried out on a universal testing machine
of maximum capacity 50 kN as shown in Fig. 2.
The tensile test specimens as per standard
ASTM-E8M, were prepared by laser cutting of
the blank as shown in Fig. 4. The anisotropy of
the 3-ply clad sheet metal was investigated by
performing tensile tests at specimen orientation
of 0, 45 and 90 to the rolling direction (RD)
and are shown in Fig. 5. The tests were carried
out include monotonic loadings in tension. Each
test is performed at least three times to ensure
good reproducibility of the experiments. The
tests were carried out at a cross head speed of
2.5mm/min. Typical engineering stress strain
curve is plotted on the basis of force and
displacement data acquired from the dedicated
software.
D. Determination of tensile properties
The strain hardening exponent (n) and the
strength co efficient (K) values are calculated
from the stress strain data in uniform elongation
region of the stress strain curve.
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
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Fig. 2. 50kN Universal testing machine
Fig. 3. Tensile tested specimens
TABLE I CHEMICAL COMPOSITIONS OF SHEET MATERIALS USED IN THE LAMINATE
Steel Sheet
material
C M
n
Si Al Ni Cr S P
AISI304 0.05 1.450 0.820 0.044 9.620 18.03 0.009 0.023
AISI430 0.12 0.902 0.675 0.038 0.621 17.02 0.023 0.026
AA1050 0.18 0.018 0.156 Rest 0.032 0.012 0.015 0.034
The plot of ln(true stress) versus ln(true strain)
which is a straight line is plotted as discussed below :
The power law of strain hardening is given as :
= K n (1)
where and are the true stress and the true strain respectively.
Taking log on both sides
Log ( ) = log (K) + n log () (2)
Fig. 4. Laser cutting of tensile specimens
Fig. 5. Tensile specimens at different orientations w.r.t. RD
This is an equation of straight line and the
slope of which gives the value of 'n' and 'K' can
be calculated taking the inverse natural log of
the y intercept of the line as shown in Fig. 8.
III. RESULTS AND DISCUSSION
To determine the bond strength of AA1050
with AISI304 and 430 respectively, the peel test
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
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specimens were prepared and tested on 50kN
UTM of Tenius Olsen make. The peeling force
and distance data were recorded using a
dedicated software Horizon and the plot between
them is shown in Fig. 6.
The average peel strength was determined as
the ratio of peeling force to the peeling width.
The range of the peeling strength of AISI 304
from AA 1050 was between 30 to 51N/mm,
whereas peeling strength of AISI430 from
AA1050 was found to be between 20 to
26N/mm. The experimental investigation
showed that the peeling strength of AISI304 is
higher than AISI430 by a factor of 1.5
approximately. In both the peeling tests, the
peeling strength remained stable for an
appreciable length of 80mm with a slight dip in
between at 40mm of peeling distance.
Fig. 6. Curve between Peeling force and
Peeling distance
The peeling strength of aluminium from AISI
304 was 40N/mm on an average basis, whereas
the peeling strength of AISI430 was 25N/mm.
Peeling strength became maximum as the
peeling distance reaches near the end of the
specimens. Same trend was observed in all the
tests conducted.
To investigate the deformational behaviour,
tensile tests were performed on the specimens
cut at three different orientations i.e. parallel to,
inclined at 45 and perpendicular to the RD. The
various tensile properties are given in Table 2. In
all the tensile tested specimens, nucleation of
crack was observed to initiate from 0.6mm thick
AISI430 which may be contributed to the lower
ductility of this steel grade. Some waviness or
warping were seen at the edges of the tested
specimens due to the difference in anisotropy of
individual sheets. A typical true stress-strain
curve is shown in Fig. 7. Tensile specimens
oriented at 45 to the RD showed maximum
ductility on an average of 57% whereas least
ductility was found with the specimens oriented
at 0 to the RD. Highest tensile strength of order
of 260MPa was observed in the specimens
oriented at 90 to the RD and least strength was
seen in specimens oriented at 0 to the RD. The
strain hardening exponent (n) as shown in Fig.
8, which is an indicator of workability at room
temperature was found to be of order of 0.25 on
an average basis. High ductility coupled with
excellent strain hardening exponent and strength
is required in deep drawing of the utensils.
TABLE II TENSILE PROPERTIES OF COMPOSITE LAMINATE AT DIFFERENT
ORIENTATIONS wrt RD
Orientation
w.r.t.
Rolling
Direction (RD)
Yield Stress
(MPa)
Ultimate
Tensile
strength
(MPa)
Percentage
elongation
(%)
Strain
Hardening
Coefficient
(n)
Strength
Coefficient,
(K)
(MPa)
0 171 242 44.7 0.234 420
45 177 254 56.0 0.256 456
90 178 262 47.2 0.255 470
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Fig. 7. True stress vs True strain plot for composite laminate oriented at different directions
Fig. 8. ln(True stress) vs ln(True strain) plot for composite laminate
IV. CONCLUSIONS
On the basis of the experimental
investigations conducted to study the
deformational behaviour in uniaxial tension test
of 3-ply laminate composite of
AISI304/AA1050/AISI430, following
conclusions can be drawn:
1. The peeling strength of the bond of AISI 304 with AA1050 is of order of 40N/mm
which is approximately 1.5 times higher
than that of AISI 430 with AA1050.
2. The peeling strength increases towards the end of the peeling distance.
3. Tensile specimens oriented at 45 to the RD showed maximum ductility on an
average of 57% whereas least ductility
was found with the specimens oriented at
0 to the RD.
4. In all the tensile tested specimens, nucleation of crack was observed to
initiate from 0.6mm thick AISI430 which
may be contributed due to the lower
ductility of this steel.
References
[1] J.Y. Jin and S.I. Hong , Effect of heat treatment on tensile deformation
characteristics and properties of
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
12
Al3003/STS439 clad composite. Mater.Sci.Eng., A 2014; 596:18.
[2] L. Chen , Z. Yang , B. Jha , G. Xia and
J.W. Stevenson Clad metals, roll bonding and their applications for SOFC
interconnects, J Power Sources 2005;152:405.
[3] E.Y. Kim ,J.H. Cho ,H.W. Kim and S.H.
Choi . Evolution of deformation texture in Al/Al Mg/Al composite sheets during cold-roll cladding, Mater.Sci.Eng, A 2011;530:24452.
[4] I.K. Kim and S.I. Hong . Effect of component layer thickness on the
bending behaviors of roll-bonded tri-
layered Mg/Al/STS clad composites. Mater.Des. 2013;49:93544.
[5] H.G.Kang , J.K. Kim, M.Y. Huh and O.
Engler . A combined texture and FEM study of strain states during roll-
cladding of five-ply stainless
steel/aluminum composites. Mater.Sci.Eng, A 2007;452453:34758.
[6] I.K. Kim and S.I.Hong.
Mater.Des.49(2013)935944. [7] H.R.Akramifard , H. Mirzadeh and
M.H. Parsa,Estimating interface bonding strength in clad sheets based on
tensile test results , 2014, Mater.Des. [8] H.R.Akramifard , H.Mirzadeh and
M.H.Parsa Cladding of aluminum on AISI 304L stainless steel by cold roll
bonding: Mechanism, microstructure,
and mechanical properties Mater.Sci.Eng. A613 (2014)232239.
[9] S.H. Choi ,K.H. Kim, K.H. Oh and D.N.
Lee .Tensile deformation behavior of stainless steel clad aluminium bilayer
sheet, Mater.Sci.Eng. A222 (1997) 158-165.
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
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3. STRESS ANALYSIS OF PELTON BUCKET USING MECHANICAL
APDL
Sonendra*1,N. Agarwal*2,
T.S.Deshmuk#3 *Mechanical Department, ITS
Engineering College, Gr. Noida,Uttar Pradesh
(India) #Civil Department. MANIT Bhopal,
Madhya Pradesh (India)
1sonendra.me@its.edu.in
namanaryan.agarwal@gmail.com 3manit_tsd@yahoo.com
Abstract----In the present work an attempt has
been made to analyse the stress developed on the
surface of Pelton bucket using Mechanical
APDL. The geometric modeling of this bucket
has been done using CATIA software for a 50 m
head and stress analysis has been done in
Mechanical APDL. The stress analysis has been
done considering bucket as a cantilever element
fixed to the disc at one end with the force of jet
applied at the splitter. The stress analysis has
been done for flow rates ranging from 100 lit/sec
to 150 lit/sec and speed ranging from 700 rpm to
900 rpm. It is observed that 1st principle stress is
higher than 2nd principle stress and 3rd principle
stress. Von Mises stress as well as all three
principle stresses decreases as rotational speed
of pelton wheel increases.
I.INTRODUCTION
The Pelton turbine is a hydraulic prime
mover which generates power by first converting
the pressure energy of water into kinetic energy
with the help of jet nozzle assembly and then
mechanical power is developed from this kinetic
energy with the use of runner. Runner of Pelton
turbine is made of buckets which are mounted
on the periphery of a disc.The bucket of Pelton
turbine has very complex geometry. The kinetic
energy of a jet of water is converted into angular
rotation of the bucket as the jet strikes. The high-
velocity jet of water emerging from a nozzle
impinges on the bucket and sets the wheel into
motion.Pelton turbine is tangential flow impulse
turbine.APelton turbine consists of a series of
buckets mounted around the periphery of a
circular disc.
II.GEOMETRIC MODELLING
The geometric modelling of the given pelton
bucket has been done using CATIA software. In
the present work, the runner of a Pelton turbine
model for 50 m head has been used for stress
analysis. The modelling of the runner blade
surface was done with the help of profile
coordinates at various sections.
The coordinates were available for 6 sections(A-
A, B-B, C-C, D-D, E-E, F-F) along the length of
the blade and 5 sections (U-U, W-W, S-S, K-K,
R-R) along the width of the blade. In addition to
this, the coordinates of the plan view as well as
lip surface were also available. Initially the
curves for all the 11 sections were plotted (in
different planes) with the distances between the
adjacent sections being determined on the basis
of plan view. Distance between splitter and E-E
curve, E-E curve and A-A curve, A-A curve and
F-F curve, F-F curve and B-B curve is 4.15 mm.
Distance between splitter and C-C curve is
28.07mm.
Fig.1 Profile of Pelton Bucket
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Distance between splitter and DD curve is 37.49
mm.Section U-U passes through origin. Distance
between U-U curve and W-W curve is
20.87mm. Distance between UU curve and SS
curve is 23 mm. Distance between W-W and K-
K curve 11.45 mm. Distance between R-R and
S-S curve is 11.45 mm. The width of the bucket
is 104.5 mm. Using the given co-ordinates,
curves were created using point and spline
commands. The final assembly of all the bucket
curves for 11 sections is shown below
Fig.2 Sections of bucket profile
After this using inner curve of all sections (A-A,
B-B, C-C, D-D, E-E, F-F, U-U,W-W, S-S, K-K,
R-R ),a surface is generated. This surface forms
the inner surface of bucket. Similarily using the
outer curve of all sections the outer surface of
bucket is created. Both surfaces are converted
into a solid bath tub type shape. After this the lip
area is created. In this way we obtained the
profile of half-bucket. Mirror command is used
to obtain remaining half profile of bucket. The
complete solid model of the bucket is shown
below
Fig.3. Solid Model of Pelton
Bucket
III.NUMERICAL SIMULATION
numerical simulation of this problem is done
using Mechanical APDL. This software is based
on the principle of Finite Element Analysis. The
basic steps involved in numerical analysis are as
follows:
A. Pre- Processing- In the pre-processor the
material definition and meshing of the imported
solid model was done. The element used in this
study is SOLID187. After selecting the element
type the material properties(Modulus of
Elasticity, Poissons Ratio, Tensile Strength, Ultimate)are defined. Meshing is very important
part of pre-processing in any FEA software.
Mechanical APDL offers two options - area,
volume. Area is for 2D geometry and volume is
for 3D geometry. In the present work volume
was chosen. Free volume meshing is used for
this analysis. Meshing done by this method is
based on default setting.The obtained meshing
of peltonbucket,had 38982 number of nodes.
B. Processing or Solution phase- In this phase,
all the details for solution are specified. The
analysis type used for stress calculations is static
structure analysis.Load and constraints are
considered as boundary conditions.
gr
Fig.4 Velocity diagram of Pelton Bucket
In this present work, a force according to
each operating condition (discharge and speed)
is applied on the splitter and the constraint is in
the form of fixed face of support of the bucket
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
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Fig.5 Boundary Conditions
A Total number of 9 operating conditions
have been considered for the analysis.
TABLE.I
Forces on Pelton Bucket at different flow
rates
Speed
discharge
700
rpm
820
rpm
900 rpm
100 lit/sec 2947
N
2491
N
2185 N
123 lit/sec 3624
N
3064
N
2687 N
150 lit/sec 4420
N
3736
N
3277 N
Force on bucket is given by- F = Q ( Vu1-Vu2)
C.Post- Processing- results have been plotted in
the form of contour plots of following:
1st Principal Stress
2nd Principal Stress
3rd Principal Stress
Von Mises Equivalent Stress.
IV.RESULT
The results of the simulation have been
presented in the form of contour plots obtained
through the APDL software for the three
principle as well as Von Mises stress.
Fig.6 Ist Principal Stress distribution for
discharge Q = 123 lit/secand speed N= 820 rpm
Fig.7 IInd Principal Stress distribution for
discharge Q = 123 lit/sec and speed N= 820 rpm
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Fig.8 3rd Principal Stress distribution for
discharge Q = 123 lit/sec and speed N= 820 rpm
A study of contour plots for principle stress with
respect to blade surface (Fig 5.1) shows that the
value of 1stprinciple stress is more or less
constant throughout the blade surface except for
a triangular region near the joint of the blade
surface and the support. Thereafter from the
joint to the fixed edge of the support the stress
increases steadily reaching a maximum value at
the edge. This is probably because the jet of
fluid returns back after reaching the end of blade
surface hence creating large stresses at the joint
of the jet and support.
2nd Principle stress (Fig 5.2) is constant
throughout the blade surface as well as the
support except at the fixed edge of the support
where it shows higher stress. As the jet
bifurcates at the splitter in two opposite direction
hence the axial thrust gets nullified.
3rd Principle stress also shows (Fig 5.3) uniform
stress all along the blade surface as well as the
support except at the location where the jet
strikes and at the fixed edge of the support.
Fig 9 Von MisesStress distribution for
discharge Q = 123 lit/sec and speed N= 700 rpm
. A study of contour plots of Von Mises stress
show that in general the Von mises stresses are
very low in the region between the lip section
and the point of application of jet. The stress
increases in a narrow zone from the point of
application of jet. This zone of high stress
widens gradually as we move towards the fixed
end of blade and simultaneously the magnitude
of stress also increases towards the fixed end.
This zone of high stress inside the bucket is
observed to follow the same pattern as that of
the jet flow. Initially it is a narrow band which
spreads out near the junction where the jet
returns from the blade surface. Within this wide
zone also the maximum stress is present in the
centre which happens to be the location of the
connection of the support. This increase in the
stress is probably due to the turning of the jet
which creates load on the blade surface.
When we consider the stress in the support then
it is seen that the stress increases continuously
from the connection with blade to the fixed end.
This is obvious due to the cantilever action.
Similarly if we consider the stress variation
across the depth of the support then maximum
stress are observed at the both bottom and top
surfaces with minimum stress at the center
region. This is also due to cantilever action.
It is observed that for a given discharge as the
rotational speed is increase there is
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
17
corresponding decrease in the magnitudes of all
three principle stresses. The reduction of all
three principle stresses and Von-mises stress
with speed is shown in table below
Table II. Variation of Stress with speed
Speed
Discharge
Stress
(N/m2)
100
lit/sec
123
lit/sec
150
lit/sec
900
rpm
Von
mises
Stress
8685 9628 11339
1st
Principle
Stress
11022 12445 14408
2nd
Principle
Stress
5137 5798 6713
3rd
Principle
Stress
3928 4415 5118
820
rpm
Von
mises
Stress
10578 13522 17091
1st
Principle
Stress
13501 17323 21857
2nd
Principle
Stress
6289 8072 10187
3rd
Principle
Stress
4784 6162 7793
700
rpm
Von
mises
Stress
14259 16746 22823
1st
Principle
Stress
18361 21359 29137
2nd
Principle
Stress
8556 9955 13580
3rd
Principle
Stress
6527 7617 10386
The principle stress vs speed graphs (fig 5.14 to
5.16) show that 1stprinciple stress is higher than
2nd and 3rd principle stresses.
The reason behind this is already discussed
while explaining the contour plots. It is observed
that at higher speed (900 rpm), maximum stress
is nearly same for all discharges. The value of
this stress is- about 13000 N/m2 for 1st principle
stress, 6000 N/m2 for 2nd principle stress and
4500 N/m2 for 3rd principle stress. At lower
speed (700rpm), there is very less variation in
stress for 100 lit/sec and 123 lit/sec. This
variation is about 14000N/m2 to 16000 N/m2for
1st principle stress, 8500N/m2 to 10000N/m2 for
2nd principle stress and 6500N/m2 to 7500
N/m2for 3rd principle stress. The stress increases
abruptly for 150 lit/sec. However in all cases the
maximum principle stress is well below the yield
limit of the material (650 MPa).
Fig 10. Variation of von mises stress with speed
it is also observed that for a given discharge as
the rotational speed is increased, there is a
corresponding decrease in the magnitude of the
stress.
V.CONCLUSION
The reason for this decrease in stress with
increase in rotational speed is probably due to
the fact that as the speed increases the contact
time of the jet on the blade decreases thus
reducing the stress.
REFERENCES
[1] Argyris J.H. (1954). Recent Advances in
Matrix Methods of
Structural Analysis, Pergamon Press,
Elmsgford, NY.
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
18
[2] Binaya K.C., BholaThapa, 2009, Pressure
Distribution at Inner
Surface of Selected Pelton Bucket For
Micro Hydro,
[3] Clough R.W., September 8-9 1960, The Finite Element
Method in Plane stresses Analysis ,Proceeding of 2nd ASCE
Conference on Electronic computation,
Pittsburg, P.A,.
[4] Hirt C.W., 1981, Nichols B.D, Volume of
fluid method for
dynamics of free boundaries, journal of
computational physics
[5] I.U. Atthanayake, Department of
Mechanical Engineering,
October 2010, The Open University of Sri
Lanka Nawala, Sri
Lanka.Analytical Study On Flow Through a Pelton Turbine
Bucket Using Boundary Layer Theory, International Journal
of Engineering & Technology IJET-IJENS
Vol:09 No:09
[6] Mr. Patel Dhaval, Mr.GajeraChintan,
Mr.ValaKuldip,
2010,Stress & Experimental Analysis Of Simple And
Advanced Pelton Wheel.
[7] Nakanishi Y., Kubota and Shin T.,2002,
Numerical simulation of flows on pelton bucket by partial method:
flow on a
stationary rotating flat plate, proceeding of 21th IAHR
symposium, Lausanne, Sept. 9-12
[8] Roache, P.J. (1972). Computational Fluid
Mechanics, Hermosa
Publishers Albquerque, NM
[9] R. Angehrn, Safety Engineering for the 423
MW-Pelton-
Runners at Bieudron, August 6 9, 2000 VATech ESCHER
WYSS, Zurich, Switzerland
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
19
4. SHIPS STEERING AUTOPILOT DESIGN BY NOMOTO MODEL
Pradeep Mishra
M.Tech student
Mechanical Engg Dept
DIAT (DU),Pune
Dr. S K Panigrahi
Professor and HOD
Mechanical Engg Dept
DIAT (DU),Pune
Lt Cdr Swarup Das
Faculty & Project Guide
MILIT
ABSTRACT
Ships manoeuvring can be automated by using
the autopilot system. The marine autopilot
system design is based on the mathematical
model of steering dynamics. Here in the present
paper a study on Nomoto model has been
undertaken for its selection for the ships steering
dynamics. Choice of selection of the model with
respect to fundamental properties of first and
second order models has been considered.
Effectiveness of the models has been assessed
on the basis of main properties of Nomoto model
i.e. controllability, observability, identifiability.
Further, reasonability of selecting state space
model and the transfer function model for the
study of different properties has been explained.
It is proven that the first order model is
controllable and observable whereas the second
order model is conditionally controllable. Zero
appearing in the transfer function model is found
responsible for the overshot behaviour which
indicates that the selection of second order
model is suitable if the overshoot behaviour has
to be studied. First and second order model are
identifiable with the ill conditioning problem
associated with the latter. hence the first order
model is suitable for autopilot applications.
Model reductions from fourth order to second
and then first order model has been undertaken
describing sway-yaw-roll dynamics and bode
plots for these models are drawn to show the
changes in frequency response due to model
simplification.
1. INTRODUCTON This paper is concerned with fundamental
properties like controllability, observability,
identifiability of Nomoto first and second order
model. State space model for Nomoto first and
second order model has been derived and solved
to find controllability, obeservability because
state space model represent non controllable as
well as non observable modes along with the
observable and controllable modes whereas the
transfer function model represents only
controllable and observable modes, non
controllable and non observable modes are
cancelled in transfer function model.
Subsequently the system overshoot with respect
to Nomoto second order model is explained.
Overshoot is caused due to sway coupling effect
on yaw rate which is represented by zero and a
high frequency pole in Nomoto second order
model i.e.(1+T3S) and (1+T2S).However the ill
conditioning problem due to near cancellation of
zero and poles T3T2 makes second order model less preferable for autopilot design.
In this paper an alternative approach is
suggested for adaptive autopilot system which
comprises of keeping the zero of second order
model which is important for the study of
overshoot phenomenon at the same time keeping
T3 fixed and varying K, T1,T2 to avoid the ill
conditioning problem .further with the help of
Bode plots for forth ,second, first order model it
is proven that why simplification of fourth order
model to second order model is not significant
because the plots are almost similar except
humps in the fourth order plot. That means
coupling effect of roll mode on yaw motion is
negligible but effect of sway couple on yaw
motion which is represented by second order
bode plot cannot be neglected. Step input
response to Nomoto models is also studied.
2. SHIP STEERING DYNAMICS MODEL
SIMPLIFICATION
Ship response in waves is considered as 6 degree
of freedom motion in space. For manoeuvring
study 3 dof motion namely surge ,sway, yaw is
considered but for heavy vessels effect of roll
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
20
cannot be neglected hence our study will revolve
around 4 dof motion description namely surge,
sway, yaw and roll.
Here fourth order transfer function relating yaw
rate to rudder angle is derived. Further
simplification to second order and first order
model is also described
Figure 1 Sway-yaw-roll motion
coordinate system.
m( + u0r) = Y+ YVV + Y+ Y + Y PP + Yrr + Y + Y (1)
IX = KPP + K mgGM+ KVV+ K + Krr + K + K(2)
IZ = Nrr + N + N + NPP+ N + NVV + N + N (3)
where YV, Y , , indicate the hydrodynamic coefficients; for instance, YV indicates the
derivative of the sway force Y to the sway speed
V evaluated at the reference condition; m is the
mass of the ship; IX is the moment of inertia
about the x-axis; IZ is the moment of inertia
about the z-axis; V is the sway speed; u is the
surge speed; r is the yaw rate; is the heading angle defined by = r ; p is the roll rate; is the roll angle defined by = p and GM is the metacentric height, which indicates the restoring
capability of a ship in rolling motion.
Taking the Laplace transform of Eqs. (1)-(3) and
rearranging, we have
a1V = a2+ a3r + a4 (4)
b1= b2V + b3r + b4 (5)
c1r = c2V + c3+ c4 (6)
where
a1 = (m YV)S YV (7)
a2 = YPS + YPS + Y (8)
a3 = YS + Yr + mu0 (9)
a4 = Y (10)
b 1 = (IX KP)S KPS + mgGM (11)
b 2 = KVS + KV (12)
b 3 = KS + Kr (13)
b4 = K (14)
c1 = (IZ N)S Nr (15)
c2 = NVS + NV (16)
c3 = NPS + NPS + N (17)
c4 = N (18)
After eliminating the sway speed V and roll
angle from Eqs. (4)-(6), the following transfer function relating the yaw rate r to the rudder
angle can be obtained: r = a1(b1C4 + b4C3) + a2(b4C2 b2C4) + a4(b1C2 + b2C3)
a1(b1C1 b3C3) a2(b2C1 + b3C2) a3(b1C2 + b2C3)
(19)
It can be easily verified that the numerator of
Eq.19 is third order in S, while the denominator
is fourth order in S. Hence, Eq. (19) can be
expressed in the following form
r = K(1 + T3S)(S + 2S +
(1 + T1S)(1 + T2S)(S + 2nS +n (20)
where the quadratic factors are due to the
coupling effect from the roll mode on the yaw
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
21
rate. The zero (1+ T3S) and the pole (1 + T2S)
are due to the coupling effect from the sway
mode on the yaw dynamics. If the roll mode is
neglected, Eq. (20) can be further reduced to the
following form
r = K(1 + T3S)
(1 + T1S)(1 + T2S) (21)
Eq. (6) is known as the second order Nomoto
model, where K is the static yaw rate gain, and
T1, T2 and T3 are time constants. In practice,
because the pole term (1 + T2S) and the zero
term (1 + T3S) in Eq. (21) nearly cancel each
other, a further simplification of Eq. (21) can be
done to give the first order Nomoto model
r = ___K____
(1 + TS) (22)
Where
T = T1 + T2 - T3
First order Nomoto model is widely employed in
autopilot design and yaw dynamics which is
characterised by parameters K and T can be
determined by manoeuvring tests. Through first
order Nomoto model a transfer function relating
ships heading() to rudder angle() can be easily calculated by adding 1/S to transfer
function model.
3. CONTROLLABILITY &
OBSERVABILITY OF NOMOTO MODELS
Fundamental properties of Nomoto first order
model has been assessed here wrt state space
model because it represents uncontrollable as
well as unobservable modes whereas
identifiability property is assessed wrt transfer
function model.
Eq (22) can be expressed in time domain as-
Tr + r = K (23) With the notation
= r (24) T K (25)
Eq 24 and 25 can be arranged in the standard
state space form
x = Ax + Bu (26) y = Cx (27)
where
x = [ ; r]^T (28) u = (29) y = (30)
and
A=
B= [0 ; K/T]^T
C= [1 0]
According to linear system theory, the system
defined by Eqs. (12) is controllable if the
following matrix U is of full rank
U = [B AB]
=
and the system is observable if the following
matrix V is of full rank
V = [C CA]^T
=
Following can be observed from above
1. First order model is controllable and observable. Here controllability means that
ships heading and rate of turn can be
controlled via application of rudder.
2. Observability indicates that system states ships heading and rate of turn can be
obtained by measured data.
3. Identifiability represents that the parameters K and T can be determined from i/p (rudder
angle) and o/p (yaw rate) which is equivalent
to fitting first order model to rudder angle
and yaw rate to find K and T. Hence online
estimation of model parameters K and based
on rudder angle and yaw rate is possible and
adaptive control strategy can be
implemented.
Similar to the discussion about first order
model, for the second order model sway to
rudder transfer function can be achieved by
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
22
neglecting the roll mode then subsequently
eliminating the yaw rate r from eq (1) and (3)
V = Kv(1 + TvS)
(1 + T1S)(1 + T2S) (31)
where Kv =static sway gain coefficinet
Tv = sway time coefficient
4. If the system is controllable then state variables ,r,V should be able to move independently via application of rudder .It is thus inferred that for the system to be
controllable Tv T.
5. It can be easily verified that the system is observable that means that all the states (, r, v) can be reconstructed from the measured
heading angle .
6. For identifiability K , T1,T2,T3 should be able to determined via and r.However if T2=T3 zero and pole will cancel each other
and ill conditioning problem will occur.
Hence for identifiability T2 T3.
4. BEHAVIOUR OF SYSTEM
OVERSHOOT
Effect of zero term (1+T3S) on second
order Nomoto model by varying values of T3
and keeping T1,T2,K fixed and applying unit
step response has been studied here. Overshoot
is observed when T3 value is higher, for low
values of T3 overshoot are not visible. In order
to study overshoot behaviour the second order
Nomoto model is employed.
In second order model, the overshoot is
visible when the zero is on right side of poles
and near the imaginary axis. From the equations
above and unit steep response curves it is
evident that the overshoot is due to sway
coupling effect on yaw rate. It can be said that
the first order model is relatively simple, doesnt have ill conditioning problem and applied for
small rudder angle yaw dynamics, it requires
identification of only two parameters hence it is
the first choice for autopilot design.
Figure 2 Unit step response T3=500
Second order Nomoto model is employed where
overshoot phenomenon due to large rudder angle
turning manoeuvre is to be studied. however it
creates an ill conditioning problem due to near
cancellation of zero and a high frequency pole.
0 20 40 60 80 100 1200
2
4
6
8
10
12
Step Response
Time (sec)
Am
plit
ud
e
Figure 3 Unit step response T3=250
0 20 40 60 80 100 1200
1
2
3
4
5
6
7
8
9
10
Step Response
Time (sec)
Am
pli
tu
de
Figure 4 Unit step response T3=100
0 50 100 150 200 2500
2
4
6
8
10
12
14
16
Step Response
Time (sec)
Am
plit
ude
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
23
5. MODEL REDUCTION AND BODE
PLOTS
Here an alternative approach is suggested
for an adaptive autopilot implementation basing
upon the second order Nomoto model. Since the
zero of the transfer function helps better
describing the yaw dynamic overshoot
behaviour, its structure is retained and the
parameter is fixed at a value determined off-line
from input-output experiment data. A fourth
order linear state space model representing the
sway-yaw-roll modes of motion will be used as
the nominal model in constructing the
corresponding yaw to rudder transfer function.
Further simplification to the second order
Nomoto model and the first order Nomoto
model will also be presented. Using MATLAB,
the transfer function of the referred state space
model , from i/p rudder to the output yaw rate r
is obtained as
r = 0.0033S-0.0004S-0.0002S-0.000079____ S 4 + 0.1913S + 0.0705S+ 0.0069S +0.0001
(32)
-70
-60
-50
-40
-30
-20
Ma
gn
itu
de
(d
B)
10-3
10-2
10-1
100
101
90
135
180
Ph
as
e (
de
g)
Bode Diagram
Frequency (rad/sec) Figure 5- Fourth order model
By neglecting the roll mode the following
transfer function can be obtained and fourth
order model is reduced to second order model.
r = 0.0033S -0.00015__
S+ 0.1213S +0.00304 (33)
-70
-60
-50
-40
-30
-20
Ma
gn
itu
de
(d
B)
10-3
10-2
10-1
100
101
90
135
180
Ph
as
e (
de
g)
bode dig of second order
Frequency (rad/sec)
Figure 6 Second order model
further by neglecting the sway coupling effect
on yaw rate ,resulting transfer function is
reduced to first order model
r = 0.049__
1+ 17.78S (34)
-55
-50
-45
-40
-35
-30
-25
Ma
gn
itu
de
(d
B)
10-3
10-2
10-1
100
90
135
180
bode dig first order model
Ph
as
e (
de
g)
Bode Diagram
Frequency (rad/sec)
Figure 7 First order model
Bode plots representing frequency domain yaw
response and comprising magnitude and phase
plots for above mentioned transfer functions are
drawn wrt fourth, second, first order model.
Plots for fourth and second order models are
almost similar except the presence of humps in
the fourth order model plot. However the first
order model plot is significantly different than
ELK Asia Pacific Journals Special Issue Proc. Of the Int. Conf: ARIMPIE-2015
24
the first order plot in the magnitude and phase.
Based on the observation of above figures, it can
be concluded that the effects of model reduction
from fourth order to second order is not
significant ;namely the coupling effects of roll
mode on yaw motion is negligible. However
simplification of second order model to first
order model poses serious challenges and throws
implication of neglecting effect of sway couple
on yaw rate which is a very significant aspect
and hence cannot be undermined.
Hence it is justified to use second order Nomoto
model to represent the behaviour of fourth order
model.
7. CONCLUSION
The first order model is relatively simple,
doesnt have ill conditioning problem and applied for small rudder angle yaw dynamics, it
requires identification of only two parameters
hence it is the first choice for autopilot design,
Second order Nomoto model is employed where
overshoot phenomenon due to large rudder angle
turning manoeuvre is to be studied. Since the
second order Nomoto model includes the
coupling effect from sway to yaw mode, it
introduces a zero and high frequency pole into
the transfer function which contribute in the
overshoot tendency. However the ill
conditioning problem with the second order
model due to near cancellation of zero and pole
prevail over the improvements gained in the
modelling potential. An approach that retains the
zero and at the s
Recommended