Journal of Aerospace Engineering & Technology
Journal of Aerospace Engineering & Technology (JoAET) is an international eJournal focused towards the rapid publication of fundamental research papers on all areas of Aerospace Engineering & Technology. Focus and Scope Covers Aeroacoustics Aeroelasticity, Aerodynamics and Fluid Mechanics Dynamics and Control Flight Simulation and Mechanics Propulsion and Combustion Unmanned Air Vehicles (UAV*S) Avionics and Systems
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Numerical Investigation of the Effect of Downburst Wind on Buildings with Various Geometrical Shapes
A “Downburst” is an important weather phenomenon in which an airmass comes down with high velocity towards the ground from the cloud level during a thunderstorm. Thunderstorms occur frequently in the eastern and north-eastern part of India. Thunderstorms over Gangetic West Bengal and Assam is popularly known as ‘Kalbaishakhi’ and ‘Bardoisila’ respectively. Severe thunderstorms are known to cause detrimental impact on various facets of national activity like civil and defense operations, aviation, space vehicle launching, agriculture in addition to its damage potential to life and properties of human beings and animals. Extreme wind conditions during thunderstorm downburst also cause extensive damages to building structures. This happens when the aerodynamic loads due to high speed downburst wind significantly exceed the design loads of the building structure. Flow patterns and pressure distribution around building structures of different geometrical shapes under the influence of downburst through numerical simulation is the main subject of study in the present paper. Commercially available software ANSYS CFX 16 solvers have been used for the numerical simulation. The study shows that the flow pattern around the buildings and the pressure distribution on the building surfaces are significantly influenced by building shape. Keywords: Downburst, streamline pattern, pressure coefficient, building shape, macro flow dynamics Cite this Article Hirak Ranjan Das, Kalyan Kumar Das. Numerical Investigation of the Effect of Downburst Wind on Buildings with Various Geometrical Shapes. Journal of Aerospace Engineering & Technology. 2017; 7(2): 34–41p.
Novel Aluminium–SiCp–Fly Ash Hybrid Metal Matrix Composites: Synthesis and Properties
The current work is primarily focused on synthesis of Aluminium 5083 – Silicon carbide – Fly ash composites enroute stir casting and its effective characterization for mechanical properties and microstructure. The aluminium 5083 alloy is an alloy that retains exceptional strength and has extreme corrosion resistant characteristics which makes it a potential material for its usage in ship building and aircraft industry. Silicon carbide is a ceramic which has very high hardness values, followed by corrosion resistance and better performance requirements unique to itself. Fly ash is a byproduct of burning pulverized coal in thermal power plants which predominantly contains aluminous and silicate materials forming a cementious in the presence of water, the use of fly ash in composites causes lubricity in between the silicon carbide and aluminium matrix apart from enhancing the strength characteristics and hardness while reducing the percentage elongation of the specimens. The results clearly give a foresight into the synthesis of aluminium silicon carbide fly ash hybrid metal matrix composites for better properties which can lead to its use in automobile, marine and aerospace components. Keywords: Aluminium, silicon carbide, fly ash, hybrid, metal, matrix, composites, synthesis, properties Cite this Article N. Santhosh, U.N. Kempaiah, G.S. Sunil et al. Novel Aluminium–SiCp–Fly Ash Hybrid Metal Matrix Composites: Synthesis and Properties. Journal of Aerospace Engineering & Technology. 2017; 7(2): 26–33p.
Development of Aircraft Safety Program Model to Handle Human Factors Under Emergency Conditions
Under emergency conditions, due to lack of situational awareness, a pilot may get trapped or biased during the decision making process. The time constraint during emergency condition demands quick action for the safety of the aircraft, crew and passengers. In the present research, the aircraft is treated as a system and interactions among the components are studied using object-oriented modeling to detect abnormalities. The present aircraft safety program model (ASPM) detects bias and handles human factors by providing feasible safety steps. The experienced pilots’ heuristics which are quick workable solution requiring less or no analysis are provided to break the bias and decision trap leading to enhanced aircraft safety. According to System-Theoretic Accident Model and Processes (STAMP), the safety should be incorporated into the design of the system by emphasizing the interactions among the system-components and the necessary constraints that must be enforced. STAMP has been applied in the present research ASPM by using object-oriented modeling. Keywords: Aircraft safety program, bias, biosensors, Boeing 777, feasible safety step, heuristics, object-oriented modeling, sequence diagrams, speech recognition, STAMP Cite this Article Parminder Kaur Wadhwa, Paramjit Singh Bilga. Development of Aircraft Safety Program Model to Handle Human Factors Under Emergency Conditions. Journal of Aerospace Engineering & Technology. 2017; 7(2): 17–25p.
Development and Testing of Anti Hijacking System for Civil Aircraft
A proof of concept system is developed and demonstrated to prevent hijacking attempt of aircraft. The system is mainly based on Raspberry Pi PC and the control program is written in the scripting language Python. The system will disable manual control of the aircraft, if a particular condition is met persistently beyond the predefined time limit. The condition to be met is simultaneous detection two authorised RFID tags for more than a predefined time period of 10 seconds. The system is seen to be operated till the time period of 10 seconds and becomes inoperative and is seen to take control of aircraft by triggering auto pilot beyond 10 seconds. The system will not allow any manual input such as disabling the system since this can result in vulnerability. As a part of the literature survey is carried out to get details of other anti-aircraft hijacking systems explored in the past. As seen in the literature survey, all the proposed mechanism has a drawback of either operating from the cabin or a possibility to disable the system manually. Two RFID sensors and tags, two servos and one joy stick were used in this work. The system is developed by developing the individual systems first followed by the integration of them later. The system is shown to work based on the concept described above. Keywords: Anti hijacking system, RFID, Raspberry Pi, GUI, Python code Cite this Article Somashekar V, Anupkumar R, Gaurav S et al. Development and Testing of Anti Hijacking System for Civil Aircraft. Journal of Aerospace Engineering and Technology. 2017; 7(2): 1–8p.
Innovative Approaches to Improve Electrochemical Machining Performance
New developments in material science have invented high-strength temperature-resistant (HSTR) materials with many extraordinary qualities. Now a day's these advanced and smart materials such as nickel-based super alloys, stainless steel and tool steel are the demands of automotive, aerospace, electronics, medical devices and communication industries for production of more durable and reliable products. Machining of these materials is a challenge and traditional manufacturing techniques are often found unfit for the purpose. One needs to use non-traditional or advanced manufacturing techniques in general and advanced machining processes in particular. ECM provides the alternative to traditional or conventional machining processes without a direct contact between the tool and the workpiece, with high material removal rates, irrespective of diverse mechanical properties of the workpiece. This review paper deals with the research on electrochemical machining (ECM) process which is carried out to improve the electrochemical machining performance and to study current developments in ECM. Different approaches to improve the dimensional control and process performance of ECM are reviewed. Keywords: Electrochemical machining, machining performance, surface roughness, metal removal rate, dimensional control Cite this Article Pawar Avinash M, Chavan ST, Chavan Sachin S et al. Innovative Approaches to Improve Electrochemical Machining Performance. Journal of Aerospace Engineering & Technology. 2017; 7(2): 9–16p.
Comparison of Simulations Results of Fuzzy Logic, Neural Network and Conventional Scheme Based Controller for SAF in Constant Frequency Aircraft System
SRF control strategy for finding reference currents for active power filters have been optimized using artificial neural network, fuzzy logic control and their performances have been evaluated. The acute analysis of comparison of the compensation capability based on THD and speedwell be done, and recommendations will be given for the choice of technique to be used. The simulated results using MATLAB model are shown, and they will undoubtedly prove the importance of the proposed control technique of aircraft shunt active power filter. Keywords: Aircraft electrical system, shunt active filter (APF), synchronous reference frame strategy, ANN, THD Cite this Article Saifullah Khalid. Comparison of Simulations Results of Fuzzy Logic, Neural Network and Conventional Scheme Based Controller for SAF in Constant Frequency Aircraft System. Journal of Aerospace Engineering and Technology. 2017; 7(1): 1–9p.
Aerodynamics and Kinematics Modeling of a Double Articulated Flapping Wing System through the Rigid Body Approach
The current model for kinematics and aerodynamics of a flapping wing system with double articulation is introduced by using strip theory approach based on blade element theory, which is complex. This research helped to formulate the model for kinematics and aerodynamics of a flapping wing system with double articulation using the rigid body approach and also use the model for the selection of motor, battery and the other electronic components to create an efficient an optimized design. Keywords: Double articulation, flapping wing, aerodynamics, kinematics, rigid-body approach, design, development Cite this Article Nandujith PJ, Prasad MS. Aerodynamics and Kinematics Modeling of a Double Articulated Flapping Wing System through the Rigid Body Approach. Journal of Aerospace Engineering & Technology. 2017; 7(1): 13–27p.
Design and Fabrication of a Piezo Actuated Flapping Mechanism for a Micro Aerial Vehicle
The main purpose of this work was to spear head research and development in Micro Aerial Vehicles (MAVs) especially in the development small flapping wing systems which can greatly be used for defense as well as surveillance purposes. This project focused on the development of a flapping wing mechanism with a wing span of just 3 cm using a piezoelectric bimorph actuator. Keywords: Micro Aerial Vehicles, MAV, Piezoelectric, Bimorph, Actuator, Flapping wing system Cite this Article Nandujith P.J., Vasantha Kumari K.G., Sushanth S., Blesson K., M.S. Prasad N. Raghu. Design and Fabrication of a Piezo Actuated Flapping Mechanism for a Micro Aerial Vehicle. Journal of Aerospace Engineering and Technology. 2017; 7(1): 28–33p.
Establishment and Development of Titanium Welding Facility
Titanium and most titanium compounds are promptly weld capable, utilizing a few welding forms. Legitimately made welds in the as-welded condition are malleable and, in many situations, are as consumption safe as base metal. Titanium is perceived for its high quality to-weight proportion. It is a light, solid metal with low thickness. Titanium welding isn't care for typical welding because of its temperament of material. To decide the different parameter and testing technique for welding which will give best weld quality with ideal welding parameter for titanium. Keywords: Titanium, Welding, Strength-to-weight ratio, Aerospace Application Cite this Article Milan Lakhani, Piyush Gopani. Establishment and Development of Titanium Welding Facility. Journal of Aerospace Engineering and Technology. 2017; 7(1): 10–12p.
Design and Analysis of Shear Fitting Used in Fin and Fuselage Attachment of a Basic Trainer Aircraft
Design of an airplane is complex as it has six degrees of freedom once it is set to fly; hence dealing with forces during flight becomes crucial. The structure of the plane should also withstand great ‘g’ force during the flight of the aircraft. The wing generates lift as the plane moves in the air, which counteracts the weight of the plane. The empennage structure will provide stability to the aircraft. Hence, the attachments for wing and empennage connected to fuselage should be strong enough. Fin, which is a fixed surface used to transfer the loads, is attached to the fuselage structure through fin-fuselage attachment. The bending moment and shear loads from the fin are transferred to the fuselage through the attachments joints. Shear attachment design is carried out based on various types of failure incurred in the lug analysis and followed by analysis of the shear attachment. Finally, the results are compared with the classical calculations and analysis of the shear attachment. Keywords: Airplane, aircraft wing, shear attachment design, calculations and analysis, finfuselage attachment Cite this Article Abhilash KS, Rakesh R, Vinayaka MS et al. Design and Analysis of Shear Fitting Used in Fin and Fuselage Attachment of a Basic Trainer Aircraft. Journal of Aerospace Engineering & Technology. 2017; 7(1): 36–40p.
Academia–Industry–Research and Development Laboratories: A Need for Collaboration
The aerospace manufacturing schemes are facing several challenges and threats from the emerging new areas. Future markets will favour the manufacturers who demonstrate responsible behaviour with regard to innovative Research and Development processes and practices by meeting the international standards. Systems engineering is becoming a key area with the trend driven by system complexities and the need for optimal integration. There is a growing risk that the present tools will soon be outdated and inadequate for the future. Future engineering will play a lead role in identifying innovatively proven processes, products and solutions. The transition to sustainable manufacturing is done in the context of increasingly complex manufacturing processes and connected enterprises.
Numerical Analysis over a Low Reynolds Number 3D Wing
<!--[if gte mso 9]><xml> <o:OfficeDocumentSettings> <o:RelyOnVML /> <o:AllowPNG /> </o:OfficeDocumentSettings> </xml><![endif]--> 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 120 AOA. Keywords: Computational fluid dynamics, low aspect ratio wings, low Reynolds number Cite this Article Somashekar V. Numerical Analysis over a Low Reynolds Number 3D Wing. 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Application of Magnus Effect in Case of a Soccer Ball
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 Cite this Article Ved Prakash. Application of Magnus Effect in Case of a Soccer Ball. Journal of Aerospace Engineering and Technology. 2016; 6(3): 1–4p.
Flush Air Data System(FADS) Validation in a Subsonic Wind Tunnel
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 Cite this Article Vidya SB, Jayakumar M, Finitha KC et al. Flush Air Data System (FADS) Validation in a Subsonic Wind Tunnel. Journal of Aerospace Engineering and Technology. 2016; 6(3): 5–15p.
Material Selection for Mechanical Structures of Space Borne Payloads
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 Cite this Article Shubham Vrujlal Rupani, Piyush Gopani. Material Selection for Mechanical Structures of Space Borne Payloads. Journal of Aerospace Engineering and Technology. 2016; 6(3): 24–28p.
A Report on Numerical Investigation of Wings: with and without Telescopic Wing
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 Cite this Article Somashekar V, Kruthika K C, Pavithra S et al. A Report on Numerical Investigation of Wings: with and without Telescopic Wing. Journal of Aerospace Engineering and Technology. 2016; 6(3): 16–23p.
High Lift to Drag Ratio for 3D Printed Airfoil for UAV’s: An Experimental and Computational Study
Airfoils play a pivotal role in the performance of aerodynamically designed bodies. Lift to Drag ratio is one of the primary parameters based on which the efficiency of airfoil’s are characterized. UAV’s are gaining acceptance around the world for the wide range of operations that can be remotely controlled. The primary objective of current work is to narrow in on an airfoil which is capable of producing high lift to drag ratio with a high aspect ratio at low Reynolds number which in turn helps in reducing the operational cost involved for UAV’s. In order to authenticate the sanctity of the results obtained from computational analysis using XFOIL software package, the experimental results for pressure distribution and L/D ratio obtained for NACA series airfoils (0012 and 6412) from wind tunnel calibrated for the required set of values are compared with the results obtained from XFOIL software package, the comparison made satisfy the convergence criteria. Further, from the critical evaluation of the computational data obtained for various series of airfoils, it is evident that S 7075 (Selig series) airfoils produces maximum L/D ratio at low Reynolds number. Based upon this critical evaluation, S 7075 series airfoil is narrowed down for 3D Printing and the experiment is carried out for validating results with the computational analysis. Keywords: Airfoil, lift to drag ratio,UAV, reynolds number, performance, CFD, 3D printing Cite this Article Kushal et al. High Lift to Drag Ratio for 3D Printed Airfoil for UAV’s: An Experimental and Computational Study. Journal of Aerospace Engineering and Technology. 2016; 6(2):
Experimentation of Flame Stabilization Using Flat Plate Gutter Made of Porous Material for Afterburner Applications
Present experimental study is focused on the flat plate gutter made of different porous materials is to stabilize the flames for afterburner applications. The porous materials used for the gutters as a flame holder are Silicon Carbide (SiC), Zirconium Oxide (ZrO2) and Aluminium Oxide (Al2O3). The porous material flat plate gutters with different orientation angles of 0°, 30°, 45°, 60° and 90° to the main stream flow. The flat plate shaped gutters made of porous materials are expected to produce strong recirculation zone in the downstream, which enhances the mixing process and increases the flame stabilization. Non-reactive flow studies are carried out and the recirculation zone area for each porous materials at five different orientations of the gutter are obtained experimentally. The experiments are conducted in the combustor test rig and the flat plate gutters are fitted in the combustor test rig with the help of plug type fixture. Air is fed through a radial blower with constant flow velocity of 4.5 m/s. The parameter of interest in the non-reactive flow studies are the recirculation zone length and wake width behind the gutter. The plots are drawn for the velocity fluctuations along the length of the combustor for different porous materials. It is observed that, due to irregular pores in the porous materials, the velocity fluctuations are higher immediately behind the gutter and gradually reduces in the downstream up to the exit plane. It is also observed that the recirculation zone length and wake width differs for different porous materials at different gutter orientation angles. The recirculation zone area is obtained by recirculation zone length and wake width and the maximum recirculation zone area is obtained at an angle 90° for all the three porous materials. Keywords: Flat plate gutter, combustor test rig, porous materials, recirculation zone area, gutter orientation angles, flow velocity Cite this Article Parammasivam et al. Experimentation of Flame Stabilization Using Flat Plate Gutter Made of Porous Material for Afterburner Applications. Journal of Aerospace Engineering and Technology. 2016; 6(2): 71–76p.
Aircraft anti-icing system is one of the key components without which aircraft icing related problems cannot be solved. Considering the long history of aircraft building technologies the involvement of anti-icing system has a remarkable influence over it. Basically there exist two types of aircraft anti-icing systems namely, the first one is electro-thermal anti-icing system the second one is bleed air anti-icing system. For propellers electro-thermal anti-icing system is used and for fixed wing planes the bleed air anti-icing system is used to prevent icing on the wings. Apart from these two anti-icing systems there exist several other anti-icing systems for the prevention of ice formation. It should be noted that anti-icing and de-icing are two different systems with different purposes. A short study of different aircraft anti-icing systems has been carried out for better understanding. The paper shows various aspects and methods of anti-icing systems used. Keywords: Aircraft Anti-Icing, bay model, de-Icing, bleed-air, electro-thermal ice protection system, electro-expulsive separation system, ultrasound actuator Cite this Article Bhavik D. Lathigara, Vinal G. Virani. A Study on Aircraft Anti-Icing Systems. Journal of Aerospace Engineering and Technology. 2016; 6(2): 9–15p.
ARINC 429 is a data transfer standard for aircraft avionics which is also known as the Mark 33 DITS Specification (Digital Information Transfer System). It makes use of self-clocking and self-synchronizing techniques. ARINC-429 bus interface is used as a controlling function. It is a two-wire point-to-point serial data bus for control communications in Avionics. The bus operates at the speed of 100kb/sec; the ARINC429 is developed to provide interchangeability and interoperability of line replaceable units (LRUs) in commercial aircraft. File transfer of ARINC 429 protocol is bit oriented, handshake between the transmitter and receiver units is necessary at the initial condition. Predefined codes are sent from the source initiates communication with the receiver to determine compatibility between the units required for successful transmission. FPGA implementation of bus protocol can be done, for this purpose SRAM memory is used to sort the data into the buffer and make use of the information whenever needed. In order to enhance the security during transmission converters and key can be used. It is one of the modern techniques used in aircrafts and military. Keywords: ARNIC429, LRU, independent transmitter and receiver Cite this Article J. Joshua Bapu, I.J. Divya Prasanna, M. Sheela Merlin. VHDL Design of ARINC 429 Bus Protocol. Journal of Aerospace Engineering and Technology. 2016; 6(2): 21–27p.
Finite Element Analysis Using 2D Plane Stress Elements for Thick Beam
Displacements and stresses are calculated for the cantilever model using two-dimensional plane stress finite element analysis (FEA) procedure. The cantilever models are developed using nine-noded Lagrangian (LAG-9) elements with application of boundary and loading conditions. The discretization, formulation of an element, constitution of element, application of load and various boundary conditions by FEA. Analyzing finite element system and computation of its results, namely stresses and displacements are programmed using MATLAB®. The two-dimensional plane stress elements use nine-noded isoparametric displacement-based finite elements. The calculated displacements and stresses are validated against the equivalent FEA model in ADINA®, general purpose finite element analysis software. Keywords: Cantilever beam, bilinear interpolation method, bending and shear stress, displacement Cite this Article Poonamrani B. Patil, Ajay G. Dahake. Finite Element Analysis Using 2D Plane Stress Elements for Thick Beam. Journal of Aerospace Engineering and Technology. 2016; 6(2): 1–8p.
Modelling Initial Design of Steel Portal Frame using ANN
<p class="Authors" style="margin-top: 0in; margin-right: .5in; margin-bottom: .0001pt; margin-left: .5in; text-align: justify; mso-element: frame; mso-element-frame-width: 0in; mso-element-frame-hspace: 0in; mso-element-frame-vspace: 0in; mso-element-wrap: auto; mso-element-anchor-vertical: margin; mso-element-anchor-horizontal: column; mso-element-left: left; mso-element-top: 0in; mso-height-rule: exactly;">Structural Engineering involves the understanding and modeling of natural phenomenon, material behavior and laws of mechanics, intuition, past experience or expertise and knowledge of analysis techniques. Especially in structural design, the difficulty in problem definition and the large number of constraints makes it difficult to program a machine for computerization of the total design process. The analysis of structure is performed based on the initial design and redesign of the structure is done using the results of this analysis. Various softwares available based on stiffness matrix method or finite element method is also required to be provided with the geometric properties of the sections initially. To reduce number of subsequent cycles for analysis and design a good initial design model is required as it is very difficult to interpret the correct cross section and reinforcement etc. Artificial neural network (ANN) is a correct tool as it can be learnt from available designs. It is observed from the literature review that ANN can be used effectively in structural optimization, initializing the design procedure of structural elements. In this research, an attempt is made to apply ANN for modeling the initial design of portal rigid steel frame. A dataset over certain range is developed for training and testing of ANNs. The results of the unseen problems by the network are compared with the dataset and prediction of initial design of frame by the network. Keywords: ANN, beam, column, steel, portal Cite this Article Upadhye et al. Modelling Initial Design of Steel Portal Frame using ANN. Journal of Aerospace Engineering and Technology. 2016; 6(2): 16–20p.
Investigation of a Possibly EF2 Tornado that had Occurred in the City of Shillong (India) on the 5th of April 2016
From the wide range of available literature it can be seen that HIW (High Intensity Winds) have a very significant effect on not only earth fixed structures but also on aviation structures aero planes or helicopters to be specific. Of the available HIW two important events have received wide attention namely Tornadoes and Downbursts. According the Glossary of Meteorology, a tornado is "A violently rotating column of air, pendant from a cumuliform cloud or underneath a cumuliform cloud, and often (but not always) visible as a funnel cloud." The United States has the most tornadoes of any country, as well as the strongest and most violent tornadoes. Other areas of the world that have frequent tornadoes include significant portions of Europe, South Africa, Bangladesh, parts of Argentina, Uruguay, and southern Brazil, New Zealand, and far eastern Asia. Bangladesh and the eastern parts of India are very exposed to destructive tornadoes causing higher deaths and injuries. Tornadoes happen mostly in eastern India, near Bangladesh during the pre Monsoon seasons (also called Kalbaishikhi or Bordoisila). Tornadoes are even recorded in northern Indian areas, including Delhi, Punjab and Rajasthan. In 2015, two tornadoes were recorded in India one in Rajasthan & other in Punjab. Both were weak ones, but they did significant damage. In this regard, a tornado had occurred in the city of Shillong on 5th of April 2016 in between 13.00–14.00 h. This paper attempts to highlight the field survey that was undertaken for studying the tornado and the possible rating of the tornado (EF2 has been arrived at). Keywords: Shillong, India, tornado, survey, monsoon Cite this Article Gogoi and Das. Investigation of a Possibly EF2 Tornado that had Occurred in the City of Shillong (India) on the 5th of April 2016. Journal of Aerospace Engineering and Technology. 2016; 6(2): 60–64p.
Damage Potential of Extreme Wind Events– Downburst and Tornado
Thunderstorms have always impressed humans and cumulonimbus cloud is one of the most visually striking and photogenic natural phenomena. Unfortunately, the thunderstorms are associated with hazardous weather. Severe thunderstorms are responsible for large amount of wind induced damage around the globe. Unlike large and continental cyclones, severe local storms intensify very rapidly and dissipate after causing damage. Lightning causes many fires around the world each year and leads to severe loss of human life and properties. The worst severe local storm is the tornado, which is characterized by fast rotating column of rising air, which originates on or near the ground where the air swirls and converges at very high speed. Another important event in the thunderstorms is the “Downburst”. Downburst is an anti-tornadic storm characterized by descending air. Downbursts occur when a column of descending air reaches the ground and bursts out violently. This downward air motion causes high wind shear close to the ground unlike a synoptic or atmospheric boundary layer (ABL) wind, where the wind speed is very high much higher above the earth's surface. It is believed that downburst is generated when the moist buoyant air moving upward can no longer be sustained above and subsides into downdraft. Such storms are popularly referred to as ‘Nor’westers or Kalbaishakhi and Bordoisilla in North-eastern part of India. These storms are due to mesoscale convective systems which develop in the pre-monsoon season (March to May) over the Gangetic West Bengal and North-eastern part of India. In this work, an attempt has been made to simulate both the wind events physically and numerically to estimate the wind profiles and macro flow dynamics for building safer earth fixed structures. Keywords: ABL, thunderstorm, tornado, downburst, continental cyclone Cite this Article Das et al. Damage Potential of Extreme Wind Events– Downburst And Tornado. Journal of Aerospace Engineering and Technology. 2016; 6(2):
Comparative Study of Turbulence Models for the Simulation of Three-Dimensional Transonic Flow around Airfoils
The analysis of three dimensional transonic flows was carried out on the well-known ONERA M6 airfoil. In this paper three turbulence models i.e. Spalart-Allmaras, <!--[if gte msEquation 12]><m:oMath><m:r>k</m:r><m:r>-</m:r><m:r>ω</m:r></m:oMath><![endif]--> <span style="font-size: 11.0pt; line-height: 107%; font-family: "Calibri","sans-serif"; mso-ascii-theme-font: minor-latin; mso-fareast-font-family: Calibri; mso-fareast-theme-font: minor-latin; mso-hansi-theme-font: minor-latin; mso-bidi-font-family: "Times New Roman"; mso-bidi-theme-font: minor-bidi; position: relative; top: 3.0pt; mso-text-raise: -3.0pt; mso-ansi-language: EN-IN; mso-fareast-language: EN-US; mso-bidi-language: AR-SA;" lang="EN-IN"> shear stress transport (SST) and <!--[if gte msEquation 12]><m:oMath><m:r>k</m:r><m:r>-</m:r><m:r>ε</m:r></m:oMath><![endif]--> <span style="font-size: 11.0pt; line-height: 107%; font-family: "Calibri","sans-serif"; mso-ascii-theme-font: minor-latin; mso-fareast-font-family: Calibri; mso-fareast-theme-font: minor-latin; mso-hansi-theme-font: minor-latin; mso-bidi-font-family: "Times New Roman"; mso-bidi-theme-font: minor-bidi; position: relative; top: 3.0pt; mso-text-raise: -3.0pt; mso-ansi-language: EN-IN; mso-fareast-language: EN-US; mso-bidi-language: AR-SA;" lang="EN-IN"> Realizable were compared for transonic flows and validated through comparison with the experimental measurements and CFD results obtained from NASA ONERA M6 study for the selected wing. The discretization of the computational domain was done using an unstructured mesh, taking care of refinement of the grid near the airfoil in order to enclose the boundary layer approach. The results indicated that Spalart-Allmaras turbulence model showed close agreement with the experimental and CFD results conducted by NASA, followed by<!--[if gte msEquation 12]><m:oMath><m:r> </m:r><m:r>k</m:r><m:r>-</m:r><m:r>ε</m:r></m:oMath><![endif]--> <span style="font-size: 11.0pt; line-height: 107%; font-family: "Calibri","sans-serif"; mso-ascii-theme-font: minor-latin; mso-fareast-font-family: Calibri; mso-fareast-theme-font: minor-latin; mso-hansi-theme-font: minor-latin; mso-bidi-font-family: "Times New Roman"; mso-bidi-theme-font: minor-bidi; position: relative; top: 3.0pt; mso-text-raise: -3.0pt; mso-ansi-language: EN-IN; mso-fareast-language: EN-US; mso-bidi-language: AR-SA;" lang="EN-IN"> realizable and <!--[if gte msEquation 12]><m:oMath><m:r>k</m:r><m:r>-</m:r><m:r>ω</m:r></m:oMath><![endif]--> <span style="font-size: 11.0pt; line-height: 107%; font-family: "Calibri","sans-serif"; mso-ascii-theme-font: minor-latin; mso-fareast-font-family: Calibri; mso-fareast-theme-font: minor-latin; mso-hansi-theme-font: minor-latin; mso-bidi-font-family: "Times New Roman"; mso-bidi-theme-font: minor-bidi; position: relative; top: 3.0pt; mso-text-raise: -3.0pt; mso-ansi-language: EN-IN; mso-fareast-language: EN-US; mso-bidi-language: AR-SA;" lang="EN-IN"> SST turbulence models. Keywords: Turbulence models, transonic flow, ONERA M6 Cite this Article Ankan Dash. Comparative Study of Turbulence Models for the Simulation of Three-Dimensional Transonic Flow Around Airfoils. Journal of Aerospace Engineering and Technology. 2016; 6(2): 47–59p.