Download to read offline
![It is my privilege to present the print version of the [Volume 6 Issue 3] of our Journal of Aerospace
Engineering and Technology (JoAET), 2016. The intension of JoAET is to create an atmosphere that
stimulatesvision,researchandgrowth intheareaofAerospaceEngineering.
Timely publication, honest communication, comprehensive editing and trust with authors and
readers have been the hallmark of our journals. STM Journals provide a platform for scholarly
research articles to be published in journals of international standards. STM journals strive to publish
qualitypaperinrecordtime,makingitaleaderinserviceandbusiness offerings.
The aim and scope of STM Journals is to provide an academic medium and an important reference
for the advancement and dissemination of research results that support high level learning, teaching
andresearchinalltheScientific,TechnicalandMedicaldomains.
Finally, I express my sincere gratitude to our Editorial/ Reviewer board, Authors and publication
team for their continued support and invaluable contributions and suggestions in the form of
authoring writeups/reviewing and providing constructive comments for the advancement of the
journals.With regards to their due continuous support and co-operation, we have been able to publish
qualityResearch/Reviewsfindingsfor our customersbase.
Ihopeyouwillenjoyreadingthisissue andwewelcomeyourfeedbackonanyaspectof theJournal.
Dr.ArchanaMehrotra
ManagingDirector
STM Journals
Director's Desk
STM JOURNALS](https://image.slidesharecdn.com/aerospacevol6issue3-170214100848/75/Aerospace-Engineering-Technology-vol-6-issue-3-8-2048.jpg)
![JoAET (2016) 5-15 © STM Journals 2016. All Rights Reserved Page 5
Journal of Aerospace Engineering & Technology
ISSN: 2231-038X(online), ISSN: 2348-7887(print)
Volume 6, Issue 3
www.stmjournals.com
Flush Air Data System (FADS) Validation in a
Subsonic Wind Tunnel
Vidya S.B., M. Jayakumar*, Finitha K.C., Remesh N., Jayantha Dhaoya,
Abdul Samad A.K., Ravikumar C., Shyam Mohan N.
Department of Space, Vikram Sarabhai Space Centre, Trivandrum, Kerala, India
Abstract
Flush air data sensing system (FADS) makes use of surface pressure measurements from the
nose cap of the vehicle for deriving the air data parameters of the vehicle such as angle of
attack, angle of sideslip, Mach number, etc. The overall FADS system including pressure
transducers, tubing, port geometry, FADS algorithm, and electronics along with the
mechanical and electrical integration scheme is successfully tested in a subsonic wind tunnel
facility. The tests are carried out in a low speed wind tunnel at wind speed of 65 m/s
(Mach=0.2). For each blow-down, angle of sideslip (beta) is set at one value and angle of
attack (alpha) is varied. Air data measurements (alpha, beta, Mach number) in each blow-
down is analyzed and compared with the set conditions. For first developmental flights, the
demanded accuracies from FADS are of the order of +/–2° in alpha and beta. Details of the
FADS system, the embedded algorithm and the various interfaces are explained. The tests
conducted and the performance obtained by comparing with the set conditions is presented in
this paper. The experimental result establishes that the accuracies demanded are provided by
the system.
Keywords: FADS, subsonic, angle of attack, wind tunnel
INTRODUCTION
The knowledge of air data parameters like,
angle of attack, Mach number, etc. with
sufficient accuracy in real time is required for
flight control of an aerospace vehicle. These
parameters are normally obtained from the air
data system of the vehicle. This data is mainly
used by the control and guidance system for
manoeuvring the flight in a profile for limiting
the vehicle loads and thermal environment and
also for keeping the vehicle trajectory within
the desired flight envelope.
Different types of air data systems have been
developed, such as those based on laser
velocity meter systems, onboard inertial
measurement unit (IMU) based systems, and
intrusive boom type instruments like pitot tube
and mechanical vanes. However, for
hypersonic flying vehicles, most of the above
systems cannot be used as protruding systems
are not permitted due to the high energy nature
of the flow. Hence in hypersonic flying
vehicles, flush air data sensing system (FADS)
is used. FADS essentially makes use of surface
pressure measurements from orifices flushed
with the surface of the vehicle [1–6]. In most
cases these orifices are located on the nose
cone of the hypersonic vehicle. For deriving
the air data parameters from the surface
pressures, an aerodynamic model is used. This
aerodynamic model captures the salient
features of the flow, and is valid over a large
Mach number range from hypersonic to
subsonic. FADS system has been successfully
demonstrated in the space shuttle [7, 8], and
also through a number of aircraft flight tests
[9–11].
The FADS system used in this test is
configured using nine pressure ports located
on the nose cone of the vehicle. Five of these
ports are in the vertical meridian and
remaining four arranged horizontally as shown
in Figure 1. The system comprises of a set of
highly accurate pressure sensors along with the
pneumatic tubings to take care of re-entry
heating and an electronic module with
embedded FADS algorithm [12].](https://image.slidesharecdn.com/aerospacevol6issue3-170214100848/75/Aerospace-Engineering-Technology-vol-6-issue-3-11-2048.jpg)
![JoAET (2016) 16-23 © STM Journals 2016. All Rights Reserved Page 16
Journal of Aerospace Engineering & Technology
ISSN: 2231-038X(online), ISSN: 2348-7887(print)
Volume 6, Issue 3
www.stmjournals.com
A Report on Numerical Investigation of Wings: with and
without Telescopic Wing
Somashekar V.*, Kruthika K.C., Pavithra S., Priyanka R., Shreerangamma T.L.
Department of Aeronautical Engineering, Acharya Institute of Technology,
Bangalore, Karnataka, India
Abstract
The telescopic wing has generated lots of interest in telescopic wing weight, geometry,
complexity, structure, retractable/extendable mechanisms and aerodynamic performance etc.
The problem is to develop telescopic wing for Piper PA-28 Cherokee is a one of the
light aircraft built by Piper aircraft and designed for flight training, air taxi, and personal
use. The key design parameters for the telescopic wing aircraft as mentioned are lift force
generated (lift coefficient) to reduce the take-off and landing distances, to decrease fuel
consumption during take-off and landing and to increase static stability of the aircraft during
take-off and landing phase at the same time in flight maneuvers remains same. The design
process is based upon the above parameters. After numerical computation of the above
parameters, the same will be checked with the values obtained from the theoretical
calculations. Since the telescopic wing aircraft to go through a cycle from take-off to ascend
to cruise to descent to landing on the runway it is necessary to check the design process at
every stage of computation. The proposed solutions are lift and draft coefficients,
aerodynamic forces at different angles of attack. In the present work, it is proposed to study
the telescopic wing aerodynamic analysis using CFD software. The various steps involved in
this work are geometric modeling using CATIA V5R17, meshing using ICEM CFD, and
solution and post-processing through FLUENT. The lift and drag coefficients were compared
for all the simulations with experimental results. The objective of the work has been achieved
successfully for both takeoff and landing of the aircraft with increased level of stability and
performance of the aircraft.
Keywords: Telescopic Wing, Computational Fluid Dynamics, Take-off and Landing,
Maneuvers, Aerodynamic Characteristics
INTRODUCTION
The only high performance aircraft that can
take-off and land on snow, water, and hard
surface! Unique designs of Multipurpose
Landing Gear, Telescopic Wing, and
Interconnected Propeller system provide
increased utility, performance, and safety.
The GENESIS is a twin engine; six-seat
'triphibious' aircraft designed for
unprecedented speed, utility, safety, and
ruggedness. The landing gear enables the
aircraft to take-off and land in water, snow,
hard surface, and sod or undeveloped runways
without changing gear components and is
completely retractable.
All three of the aircraft landing configurations
are selectable by the pilot while in flight. The
new telescopic wing design gives the aircraft a
fast cruise speed of 280 mph while
maintaining Short Take Off and Landing
(STOL) characteristics for short and rough
field conditions on undeveloped and
developed airstrips (stall speed 63 mph). The
range is also increased to over 2,000 miles.
The durable structure gives the aircraft
aerobatic capabilities and a useful load of
2,400 lbs (1091 kgs). The innovative
propulsion system of the aircraft links both
propellers to both engines so power is still
provided to both propellers during an engine
failure, which greatly increases safety. Patents
have been issued and construction is beginning
on the prototype aircraft. Preparations are
being made for production under FAR Part 23
certification. Investors are being sought to
expedite construction of the aircraft [1].](https://image.slidesharecdn.com/aerospacevol6issue3-170214100848/75/Aerospace-Engineering-Technology-vol-6-issue-3-12-2048.jpg)
![JoAET (2016) 24-28 © STM Journals 2016. All Rights Reserved Page 24
Journal of Aerospace Engineering & Technology
ISSN: 2231-038X(online), ISSN: 2348-7887(print)
Volume 6, Issue 3
www.stmjournals.com
Material Selection for Mechanical Structures of
Space Borne Payloads
Shubham Vrujlal Rupani1,
*, Piyush Gopani2
1
Department of Mechanical Engineering, Atmiya Institute of Technology and Science,
Rajkot, Gujarat, India
2
Department of Mechatronics Engineering, G. H. Patel College of Engineering and Technology,
V.V. Nagar, Gujarat, India
Abstract
Space borne payloads consist of several structures to fulfill its functions in space operation.
Among these structures, mechanical structure serves as a backbone of whole payload. Hence
mechanical structure needs to have very high rigidity and strength. For space applications,
materials to be used in mechanical structures need to be selected very carefully. Every gram
of added weight increases few liters of fuel consumption and hence costs extra money for
launching of payloads. Hence material used in space borne mechanical structure needs to be
very light. Now days composite materials are replacing metallic materials due to having
superior mechanical properties with lesser weight. Although manufacturing of all the
components of structure is not possible with composite materials. Hence compromised choice
of light weight metal needs to be selected. This paper gives insight about materials selection
consideration for space borne mechanical structures.
Keywords: Mechanical structure, space borne payload, material selection, space application
INTRODUCTION
Choice of material to be used in space
application is constrained by several
parameters. For higher efficiency of launch
vehicles, materials should be very light with
required strength and stiffness for functional
requirements. Material selection process for
space application requires consideration of
almost 21 different parameters.
These parameters are: (1) vacuum, (2) atomic
oxygen, (3) ultraviolet radiation/solar
exposure, (4) thermal environment, (5) thermal
cycling induced micro-cracking, (6)
micrometeoroid and debris, (7) weightlessness
and microgravity, (8) space plasma and
spacecraft electrical charging and discharging,
(9) contamination, (10) environmental
synergistic effect, (11) off gassing/toxicity,
(12) bacterial and fungus growth, (13)
flammability, (14) chemical (corrosion), (15)
stress corrosion, (16) fluid compatibility, (17)
galvanic compatibility, (18) moisture
absorption and desorption, (19) lightning
strike, (20) electromagnetic interface and (21)
planetary environment [1]. These many
affecting parameters make selection process
very complicated. Hence all the parameters
cannot be considered at once. Only critical
parameters which affect the most for particular
application are considered.
DISCUSSION
For structural application, primary functional
requirement is to sustain imposed loads of
overall structure. Hence, primary requirements
to withstand loads with acceptable stress
values need to be evaluated. For structural
members like outer casing or truss structure,
deflection of members needs to be smallest
possible. Hence young’s modulus of materials
used in these structural members needs to be
very high.
In space environment, payloads are subjected
to wide range of temperature variations.
Particularly in lower earth orbit, temperature
changes from –123 to 120°C. Hence thermal
expansion of material selected has to be within
acceptable limits. Comparison of various
materials for weight, tensile strength and
modulus has been given in Figure 1.](https://image.slidesharecdn.com/aerospacevol6issue3-170214100848/75/Aerospace-Engineering-Technology-vol-6-issue-3-13-2048.jpg)
More Related Content
Aerospace Engineering & Technology vol 6 issue 3
- 1. Journal of Aerospace Engineering &Technology (JoAET) September–December 2016 SJIF: 3.8 ISSN 2231-038X (Online) ISSN 2348-7887 (Print) www.stmjournals.com STM JOURNALS Scientific Technical Medical
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- 4. Gargi Asha Jha Manager(Publications) PUBLICATION MANAGEMENT TEAM Internal Members External Members Bimlesh Lochab Assistant Professor Department of Chemistry School of Natural Sciences, Shiv Nadar University Gautam Buddha Nagar, Uttar Pradesh, India Dr. Rajiv Prakash Professor and Coordinator School of Materials Science and Technology Indian Institute of Technology (BHU), Varanasi Uttar Pradesh, India Dr. Rakesh Kumar Assistant Professor Department of Applied Chemistry BIT Mesra, Patna, Bihar, India Prof. S. Ramaprabhu Alternative Energy and Nanotechnology Technology Laboratory, Department of Physics Indian Institute of Technology, Chennai Tamil Nadu, India Himani Pandey Isha Chandra Senior Associate Editors Dr. Yog Raj Sood Dean (Planning and Development) Professor, Department of Electrical Engineering National Institute of Technology, Hamirpur Himachal Pradesh, India Prof. Chris Cannings Professor, School of Mathematics and Statistics University of Sheffield, Sheffield United Kingdom Dr. D. K. Vijaykumar MS, MCh (Surgical Oncology), Professor and Head Department of Surgical Oncology Amrita Institute of Medical Sciences and Research Centre Ponekkara, Cochin, Kerala, India Dr. Durgadas Naik Associate Professor (Microbiology) Management and Science University, University Drive, Seksyen13 Selangor, Malaysia Prof. José María Luna Ariza Department of Computer Sciences and Numerical Analysis Campus of Rabanales University of Córdoba, Spain Dr. Khaiser Nikam Professor, Library and Information Science Department of Library and Information Science University of Mysore Mysore, India Quaisher J Hossain Senior Editor Group Managing Editor Dr. Archana Mehrotra Managing Director CELNET, Delhi, India Meenakshi Tripathi Shivani Sharma Chairman Mr. Puneet Mehrotra Director Shambhavi Mishra Associate Editors Sugandha Mishra
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- 7. Editorial Board Dr. ParammasivamKanjikovil Mahali Anna University , Madras, India. Prof. Kalyan Prasad Sinhamahapatra Head, Department of Aerospace Engineering, IIT Kharagpur, India. Dr. Yuwaraj Marotrao Ghugal Department of Applied Mechanics, Govt. College of Engineering Station Road, Osmanpura, Aurangabad, India. Dr. Vijayaraja Kengaiah Prof. Head, Aeronautical Engg. Dept., P.B. College of Engg., Chennai, India. Prof. Murthy RL C Department of Aerospace Engineering, Indian Institute of Science, Bangalore, India. Dr. Subba Raju P.V Prof. & Chairman, Aeronautical & Mechanical Engineering Division, Institute of Aeronautical Engineering, Dundigal, Hyderabad, India. Dr. Ashok K Singh Department of Aerospace Engineering, Defence Institute of Advanced Technology, Girinagar, Pune, India. Dr. Amarjeet Singh Department of Computer Applications, Institute of Environment and Management, Lucknow, Uttar Pradesh, India. Dr. Tiauw Hiong Go Nanyang Technological University, Singapore. Dr. Ravishekar Kannan Computational Fluid Dynamics (CFD), Research Corporation, United States. Dr. Ravindranath Nayak Head, Aerospace Electronics & Systems Division, National Aerospace Laboratories (NAL), CSIR Airport Rd, Kodihalli, Bangalore India. Dr. M. R. Nayak Head, Aerospace Electronics & Systems Division, and Advisor to Director National Aerospace Laboratories, India.
- 8. It is myprivilege to present the print version of the [Volume 6 Issue 3] of our Journal of Aerospace Engineering and Technology (JoAET), 2016. The intension of JoAET is to create an atmosphere that stimulatesvision,researchandgrowth intheareaofAerospaceEngineering. Timely publication, honest communication, comprehensive editing and trust with authors and readers have been the hallmark of our journals. STM Journals provide a platform for scholarly research articles to be published in journals of international standards. STM journals strive to publish qualitypaperinrecordtime,makingitaleaderinserviceandbusiness offerings. The aim and scope of STM Journals is to provide an academic medium and an important reference for the advancement and dissemination of research results that support high level learning, teaching andresearchinalltheScientific,TechnicalandMedicaldomains. Finally, I express my sincere gratitude to our Editorial/ Reviewer board, Authors and publication team for their continued support and invaluable contributions and suggestions in the form of authoring writeups/reviewing and providing constructive comments for the advancement of the journals.With regards to their due continuous support and co-operation, we have been able to publish qualityResearch/Reviewsfindingsfor our customersbase. Ihopeyouwillenjoyreadingthisissue andwewelcomeyourfeedbackonanyaspectof theJournal. Dr.ArchanaMehrotra ManagingDirector STM Journals Director's Desk STM JOURNALS
- 9. 1. Application ofMagnus Effect in Case of a Soccer Ball Ved Prakash 1 2. Flush Air Data System (FADS) Validation in a Subsonic Wind Tunnel Vidya S.B., M. Jayakumar, Finitha K.C., Remesh N., Jayantha Dhaoya, Abdul Samad A.K., Ravikumar C., Shyam Mohan N. 5 3. A Report on Numerical Investigation of Wings: with and without Telescopic Wing Somashekar V., Kruthika K.C., Pavithra S., Priyanka R., Shreerangamma T.L. 16 4. Material Selection for Mechanical Structures of Space Borne Payloads Shubham Vrujlal Rupani, Piyush Gopani 24 5. Numerical Analysis over a Low Reynolds Number 3D Wing Somashekar V. 29 ContentsJournal of Aerospace Engineering & Technology
- 10. JoAET (2016) 1-4© STM Journals 2016. All Rights Reserved Page 1 Journal of Aerospace Engineering & Technology ISSN: 2231-038X(online), ISSN: 2348-7887(print) Volume 6, Issue 3 www.stmjournals.com Application of Magnus Effect in Case of a Soccer Ball Ved Prakash* Department of Mechanical Engineering, Kalinga Institute of Industrial Technology, Bhubaneswar, Odisha, India Abstract This paper discusses the different areas of research conducted on the Magnus effect on a soccer ball and the different methodologies used. The different methodologies used have been arranged in a tabular format for easier viewing and referring. The methodologies have been described so that the reader can understand the various contributions of the author and the considerations and assumptions taken by the author in their respective work. The tabular format helps in easy comparison of the various methods used by the various authors in their contributions. Thus, the areas of further research can be easily pointed out from the work already done in this field and the methodologies that can be used to delve further into this effect in case of soccer balls have also been briefly discussed after the review of the literature. Keywords: Magnus effect, soccer ball, application, sports, review INTRODUCTION The Magnus effect named after German physicist Heinrich Gustav Magnus is the generation of a sidewise force acting on a cylindrical or spherical body immersed in a fluid, when there is a relative motion between the body and the fluid. This phenomenon is widely seen in various ball sports such as football, basketball, baseball, table tennis, cricket, etc. and also in artillery shells. The effect occurs when the spinning body creates a pressure difference by retarding the airflow on one side (the side turning in the same direction as direction of travel of body) and speeding up the airflow on the other side. This results in change in the path of trajectory followed by the body. German physicist Heinrich Gustav Magnus described the effect in 1852. However, in 1672, Isaac Newton had described it and correctly inferred the cause after observing tennis players in his Cambridge College. In 1742, Benjamin Robins, a British mathematician, ballistics researcher and military engineer, explained deviations in the trajectories of musket balls in terms of the Magnus effect. In case of a spinning bullet, it experiences sideways wind component due to its yawing motion and is also subjected to crosswind, which causes a Magnus Force to act on the bullet (acting perpendicular both to the motion of the bullet and combined sideways wind component). Although, the Magnus Force acting on the bullet is insignificant as compared to the aerodynamic drag, but it affects the stability of the bullet, which ultimately affects the amount of drag created and how the bullet behaves after impact along with other factors. Magnus effect in case of sports such as table tennis is easily observed due to the low mass and density of the ball. In case of cricket, Magnus effect does not help in swing bowling, but it does contribute to the dip and drift of the ball. The football used in the FIFA World Cup 2010 was criticized for the different Magnus effect from previous match balls. The ball used was said to have less Magnus effect and so it flew further, but with less controllable swerve. Magnus effect can also be as used as rotors in airplanes and ships. The Magnus rotors, generally known as Flettner rotor consists of a rotating cylinder with disc end plates which is spun along its long axis and as air passes at right angles across it, an aerodynamic force is generated due to Magnus effect.
- 11. JoAET (2016) 5-15© STM Journals 2016. All Rights Reserved Page 5 Journal of Aerospace Engineering & Technology ISSN: 2231-038X(online), ISSN: 2348-7887(print) Volume 6, Issue 3 www.stmjournals.com Flush Air Data System (FADS) Validation in a Subsonic Wind Tunnel Vidya S.B., M. Jayakumar*, Finitha K.C., Remesh N., Jayantha Dhaoya, Abdul Samad A.K., Ravikumar C., Shyam Mohan N. Department of Space, Vikram Sarabhai Space Centre, Trivandrum, Kerala, India Abstract Flush air data sensing system (FADS) makes use of surface pressure measurements from the nose cap of the vehicle for deriving the air data parameters of the vehicle such as angle of attack, angle of sideslip, Mach number, etc. The overall FADS system including pressure transducers, tubing, port geometry, FADS algorithm, and electronics along with the mechanical and electrical integration scheme is successfully tested in a subsonic wind tunnel facility. The tests are carried out in a low speed wind tunnel at wind speed of 65 m/s (Mach=0.2). For each blow-down, angle of sideslip (beta) is set at one value and angle of attack (alpha) is varied. Air data measurements (alpha, beta, Mach number) in each blow- down is analyzed and compared with the set conditions. For first developmental flights, the demanded accuracies from FADS are of the order of +/–2° in alpha and beta. Details of the FADS system, the embedded algorithm and the various interfaces are explained. The tests conducted and the performance obtained by comparing with the set conditions is presented in this paper. The experimental result establishes that the accuracies demanded are provided by the system. Keywords: FADS, subsonic, angle of attack, wind tunnel INTRODUCTION The knowledge of air data parameters like, angle of attack, Mach number, etc. with sufficient accuracy in real time is required for flight control of an aerospace vehicle. These parameters are normally obtained from the air data system of the vehicle. This data is mainly used by the control and guidance system for manoeuvring the flight in a profile for limiting the vehicle loads and thermal environment and also for keeping the vehicle trajectory within the desired flight envelope. Different types of air data systems have been developed, such as those based on laser velocity meter systems, onboard inertial measurement unit (IMU) based systems, and intrusive boom type instruments like pitot tube and mechanical vanes. However, for hypersonic flying vehicles, most of the above systems cannot be used as protruding systems are not permitted due to the high energy nature of the flow. Hence in hypersonic flying vehicles, flush air data sensing system (FADS) is used. FADS essentially makes use of surface pressure measurements from orifices flushed with the surface of the vehicle [1–6]. In most cases these orifices are located on the nose cone of the hypersonic vehicle. For deriving the air data parameters from the surface pressures, an aerodynamic model is used. This aerodynamic model captures the salient features of the flow, and is valid over a large Mach number range from hypersonic to subsonic. FADS system has been successfully demonstrated in the space shuttle [7, 8], and also through a number of aircraft flight tests [9–11]. The FADS system used in this test is configured using nine pressure ports located on the nose cone of the vehicle. Five of these ports are in the vertical meridian and remaining four arranged horizontally as shown in Figure 1. The system comprises of a set of highly accurate pressure sensors along with the pneumatic tubings to take care of re-entry heating and an electronic module with embedded FADS algorithm [12].
- 12. JoAET (2016) 16-23© STM Journals 2016. All Rights Reserved Page 16 Journal of Aerospace Engineering & Technology ISSN: 2231-038X(online), ISSN: 2348-7887(print) Volume 6, Issue 3 www.stmjournals.com A Report on Numerical Investigation of Wings: with and without Telescopic Wing Somashekar V.*, Kruthika K.C., Pavithra S., Priyanka R., Shreerangamma T.L. Department of Aeronautical Engineering, Acharya Institute of Technology, Bangalore, Karnataka, India Abstract The telescopic wing has generated lots of interest in telescopic wing weight, geometry, complexity, structure, retractable/extendable mechanisms and aerodynamic performance etc. The problem is to develop telescopic wing for Piper PA-28 Cherokee is a one of the light aircraft built by Piper aircraft and designed for flight training, air taxi, and personal use. The key design parameters for the telescopic wing aircraft as mentioned are lift force generated (lift coefficient) to reduce the take-off and landing distances, to decrease fuel consumption during take-off and landing and to increase static stability of the aircraft during take-off and landing phase at the same time in flight maneuvers remains same. The design process is based upon the above parameters. After numerical computation of the above parameters, the same will be checked with the values obtained from the theoretical calculations. Since the telescopic wing aircraft to go through a cycle from take-off to ascend to cruise to descent to landing on the runway it is necessary to check the design process at every stage of computation. The proposed solutions are lift and draft coefficients, aerodynamic forces at different angles of attack. In the present work, it is proposed to study the telescopic wing aerodynamic analysis using CFD software. The various steps involved in this work are geometric modeling using CATIA V5R17, meshing using ICEM CFD, and solution and post-processing through FLUENT. The lift and drag coefficients were compared for all the simulations with experimental results. The objective of the work has been achieved successfully for both takeoff and landing of the aircraft with increased level of stability and performance of the aircraft. Keywords: Telescopic Wing, Computational Fluid Dynamics, Take-off and Landing, Maneuvers, Aerodynamic Characteristics INTRODUCTION The only high performance aircraft that can take-off and land on snow, water, and hard surface! Unique designs of Multipurpose Landing Gear, Telescopic Wing, and Interconnected Propeller system provide increased utility, performance, and safety. The GENESIS is a twin engine; six-seat 'triphibious' aircraft designed for unprecedented speed, utility, safety, and ruggedness. The landing gear enables the aircraft to take-off and land in water, snow, hard surface, and sod or undeveloped runways without changing gear components and is completely retractable. All three of the aircraft landing configurations are selectable by the pilot while in flight. The new telescopic wing design gives the aircraft a fast cruise speed of 280 mph while maintaining Short Take Off and Landing (STOL) characteristics for short and rough field conditions on undeveloped and developed airstrips (stall speed 63 mph). The range is also increased to over 2,000 miles. The durable structure gives the aircraft aerobatic capabilities and a useful load of 2,400 lbs (1091 kgs). The innovative propulsion system of the aircraft links both propellers to both engines so power is still provided to both propellers during an engine failure, which greatly increases safety. Patents have been issued and construction is beginning on the prototype aircraft. Preparations are being made for production under FAR Part 23 certification. Investors are being sought to expedite construction of the aircraft [1].
- 13. JoAET (2016) 24-28© STM Journals 2016. All Rights Reserved Page 24 Journal of Aerospace Engineering & Technology ISSN: 2231-038X(online), ISSN: 2348-7887(print) Volume 6, Issue 3 www.stmjournals.com Material Selection for Mechanical Structures of Space Borne Payloads Shubham Vrujlal Rupani1, *, Piyush Gopani2 1 Department of Mechanical Engineering, Atmiya Institute of Technology and Science, Rajkot, Gujarat, India 2 Department of Mechatronics Engineering, G. H. Patel College of Engineering and Technology, V.V. Nagar, Gujarat, India Abstract Space borne payloads consist of several structures to fulfill its functions in space operation. Among these structures, mechanical structure serves as a backbone of whole payload. Hence mechanical structure needs to have very high rigidity and strength. For space applications, materials to be used in mechanical structures need to be selected very carefully. Every gram of added weight increases few liters of fuel consumption and hence costs extra money for launching of payloads. Hence material used in space borne mechanical structure needs to be very light. Now days composite materials are replacing metallic materials due to having superior mechanical properties with lesser weight. Although manufacturing of all the components of structure is not possible with composite materials. Hence compromised choice of light weight metal needs to be selected. This paper gives insight about materials selection consideration for space borne mechanical structures. Keywords: Mechanical structure, space borne payload, material selection, space application INTRODUCTION Choice of material to be used in space application is constrained by several parameters. For higher efficiency of launch vehicles, materials should be very light with required strength and stiffness for functional requirements. Material selection process for space application requires consideration of almost 21 different parameters. These parameters are: (1) vacuum, (2) atomic oxygen, (3) ultraviolet radiation/solar exposure, (4) thermal environment, (5) thermal cycling induced micro-cracking, (6) micrometeoroid and debris, (7) weightlessness and microgravity, (8) space plasma and spacecraft electrical charging and discharging, (9) contamination, (10) environmental synergistic effect, (11) off gassing/toxicity, (12) bacterial and fungus growth, (13) flammability, (14) chemical (corrosion), (15) stress corrosion, (16) fluid compatibility, (17) galvanic compatibility, (18) moisture absorption and desorption, (19) lightning strike, (20) electromagnetic interface and (21) planetary environment [1]. These many affecting parameters make selection process very complicated. Hence all the parameters cannot be considered at once. Only critical parameters which affect the most for particular application are considered. DISCUSSION For structural application, primary functional requirement is to sustain imposed loads of overall structure. Hence, primary requirements to withstand loads with acceptable stress values need to be evaluated. For structural members like outer casing or truss structure, deflection of members needs to be smallest possible. Hence young’s modulus of materials used in these structural members needs to be very high. In space environment, payloads are subjected to wide range of temperature variations. Particularly in lower earth orbit, temperature changes from –123 to 120°C. Hence thermal expansion of material selected has to be within acceptable limits. Comparison of various materials for weight, tensile strength and modulus has been given in Figure 1.
- 14. JoAET (2016) 29-34© STM Journals 2016. All Rights Reserved Page 29 Journal of Aerospace Engineering & Technology ISSN: 2231-038X (online), ISSN: 2348-7887(print) Volume 6, Issue 3 www.stmjournals.com Numerical Analysis over a Low Reynolds Number 3D Wing Somashekar V.* Department of Aeronautical Engineering, Acharya Institute of Technology, Bengaluru, Karnataka, India Abstract A micro air vehicle (MAV) is defined as class of unmanned air vehicle (UAV) having a linear dimension of less than 15 cm and a mass of less than 100 g with flight speeds of 6 to 12 m/sec. MAVs fall within a Reynolds number (Re) range of 50,000 and 120,000, in which many causes of unsteady aerodynamic effects are not fully understood. The research field of low Reynolds number aerodynamics is currently an active one, with many defence organizations, universities, and corporations working towards a better understanding of the physical processes of this aerodynamic regime. In the present work, it is proposed to study the unsteady aerodynamic analysis of 3D wing using CFD software. The various steps involved in this work are geometric modelling using CATIA, meshing using ICEM CFD, and solution and post processing through FLUENT. The finite control volume analysis has been carried out to predict aerodynamic characteristics such as lift coefficients and drag coefficients. The lift and drag coefficients were compared for all the simulations with experimental results. It was observed that for the 3D wing, lift and drag both compared well for the midrange angle of attack from –5 to 12° AOA. Keywords: Computational fluid dynamics, low aspect ratio wings, low Reynolds number INTRODUCTION Micro air vehicles (MAVs) have attracted significant attention since mid-1990 for both civilian and military applications. Micro air vehicle (MAV) is defined here as a small, portable flying vehicle which is designed for performing useful work. The desire for portable, low altitude aerial surveillance has driven the development of aircraft on the scale of small birds. Vehicles in this class of small- scale aircraft are known as micro air vehicles or MAVs and have great potential for applications in surveillance and monitoring tasks in areas either too remote or too dangerous to send human agents. Equipped with small video cameras and transmitters, MAVs can image targets that would otherwise remain inaccessible. MAVs are also capable of carrying an array of sensors to obtain additional information including, for example, airborne chemical or radiation levels. MAVs are by definition small aircrafts which fly at relatively low speeds. Such flight characteristics will result in flow regimes with Reynolds numbers. Another aerodynamic signature of MAV is wings with small aspect ratio; in most cases the chord is roughly equal to the wingspan. This combination of low Reynolds number flight and low aspect ratio wings results in a flow regime totally alien to conventional aircraft. In order for required MAV capabilities to be realized, several areas will need more focused attention. The absence of sophisticated computational analysis methods, lack of commercially available micro electromechanical sensors, and the difficulties associated with accurate experimental work at this scale, have all restricted research. From a system and manufacturing standpoint, technological advances in micro fabrication techniques and in the miniaturization of electronics in the last decade made mechanical MAVs feasible. Key research challenges include unsteady aerodynamics at low Reynolds number, low aspect ratio wings, stability and control issues
- 15. Journal of Aerospace Engineering &Technology (JoAET) September–December 2016 SJIF: 3.8 ISSN 2231-038X (Online) ISSN 2348-7887 (Print) www.stmjournals.com STM JOURNALS Scientific Technical Medical