In this paper, the technique of structure health monitoring was applied to detect damage occurrence in the stiffeners of wing structure. A wing structure of airfoil shape according to digital NACA 0015 was considered for modelling the aerodynamic wing shape. Finite element models of the wing structure were created included undamaged and damage wing structures using high order eight nodes and six nodes shell elements. The damaged wing models included damaged at the main spar at 20%, 40%,60% and 80% the distance than the root chord. A mathematical model was developed using high order shell elements and programmed via MATLAB. The load cases were predicted experimentally using wind tunnel test on a wood airfoil prototype such that the pressure distributions through upper and lower wing skins measured at different attack angles.
OPERATING EFFICIENCY STUDY OF AVIATION SECURITY SCREENERS USING THE EYE-TRACK...IAEME Publication
This paper describes studies related to the influence of the fatigue factor on the
oculomotor activity of aviation security screeners. Analysis of possible instrumental
diagnostic methods of the functional status of aviation security screeners was
conducted and the Eye-tracking technology was selected as the one with the greatest
advantages. Overview of the experience in the application of the Eye-tracking
technology when diagnosing the functional status of aviation security screeners is
presented. In this paper for the first time as follows from experimental studies using
the Eye-tracking technology potential fatigue markers of aviation security screeners
with the most accurate changes were identified consistent with earlier studies pursued
by other authors. As the result of solving the problem of the statistical hypothesis
testing it is found that such oculomotor reactions as the blink frequency, the blink
duration average and the pupils diameter average can be used for diagnosing the
functional status of aviation security screeners whereas the saccade frequency did not
change for certain in the period of studies pursued and is not potentially useful for
monitoring. It was demonstrated that the Sugeno fuzzy model based on the subtractive
clustering and ANFIS-learning does better approximate the dependence between
oculomotor activity indicators of aviation security screeners and the prohibited items
detection efficiency in comparison with other models. Model fidelity by the Root-
Mean-Square Error criterion on the learning sample is 0,0348 and on the test sample
is 0,0858 as the case may be. Scientific and theoretical value of this paper involves
developing scientific knowledge related to the influence of the fatigue factor on the
oculomotor activity of aviation security screeners in the course of the working activity
Light Aircraft Landing Gear Strut Group 6 ReportRobert Tanner
The document analyzes materials for the landing gear strut of a Cessna TTX light aircraft. It translates design requirements into constraints and objectives, screens materials based on compressive strength and corrosion resistance, ranks materials based on indices that minimize weight and maximize buckling resistance and fatigue endurance. Magnesium alloy is selected as it is lightweight, inexpensive, and easier to manufacture than aluminum alloys, though composites are increasingly common in aircraft.
Stress and fatigue analysis of landing gear axle of a trainer aircrafteSAT Journals
Abstract The undercarriage or landing gear of an aircraft is the structure that supports an aircraft on the ground and allows it to taxi, takeoff and land. Among the various parts of landing gear, axle is the most critical component where the loads (landing and ground loads) act on the axle first, then transferred to the structure. In this study stress and fatigue analysis of the axle is performed to meet the strength and life requirements. The modeling of the axle is done using UniGraphics (UG) software. Stress analysis is carried out using MSC Patran (pre-processing and post-processing)/Nastran (solver) for different landing loads (spin up, spring back, maximum vertical and drift) and ground handling loads (braking, taxing and turning). Stress analysis was carried out by both classical and FEM approaches and by comparing the results it was obvious that they were in correlation with one another. Fatigue analysis was also carried out for the axle using landing spectrum and ground handling spectrum to estimate the fatigue life. By the iteration process, the requirement of 10000 landings was satisfied. Keywords: Static, Fatigue, Axle, Fatigue life, UniGraphics, MSC Patran, MSC Nastran
IRJET- Numerical Analysis of Nose Landing Gear SystemIRJET Journal
This document presents a numerical analysis of the nose landing gear system of an aircraft using finite element analysis. It begins with an abstract that outlines the objective to determine stress behavior and displacement of the nose gear during landing. It then describes the modeling process where the nose gear was modeled in CAD software and imported into finite element analysis software for meshing and application of loads and constraints. Key steps of the finite element analysis are described including discretization, deriving element equations, assembling global equations, applying loads/boundaries, and solving for results. Results of the finite element analysis such as stress contours, displacement contours, and natural frequencies are presented and discussed.
Fatigue fracture of a main landing gear swinging leverin a civil aircraftPramodKawade
The left main landing gear of an aircraft collapsed during takeoff due to fatigue fracture of the swinging lever after 26,139 flights. Fractography analysis revealed the fracture initiated from the surface of the lever near the most stressed region as identified by FEA stress analysis. Microstructural examination found an abnormal amount of silicon at the origin site which led to stress concentrations. AFGROW fatigue analysis using the FEA stress data predicted a fatigue life of 20,000 cycles, consistent with the actual life, indicating the failure occurred due to exceeding the fatigue life of the lever.
Design analysis of bumper beam subjected to offset impact loading for automot...IAEME Publication
This document discusses the design analysis of bumper beams subjected to offset impact loading for automotive applications. It aims to increase understanding of phenomena during offset impacts and validate modeling of bumper beam crash performance. Finite element analysis was conducted in ANSYS-LS DYNA to simulate impact on bumper beam-longitudinal systems made of different aluminum alloys (AA6060-T1, AA7003-T1, AA7003-T79). The results showed AA7003-T79 experienced the least deformation and minimized energy transfer, suggesting it is the best material for manufacturing bumper beam longitudinal systems.
As the Manager of Accident Prevention at Westinghouse Electric, Lewis Barbe, a safety engineer, received the National Safety Council Award for establishing a world safety record.
Car-pedestrian accidents account for a considerable number of automobile accidents in industrialized countries. Head injury continues to be more concerned in Automobile impacts.
Because the head is the most seriously injured part in many collisions including in pedestrian automobile collisions. Head injuries are the most common cause of pedestrian deaths in car to pedestrian collisions.
OPERATING EFFICIENCY STUDY OF AVIATION SECURITY SCREENERS USING THE EYE-TRACK...IAEME Publication
This paper describes studies related to the influence of the fatigue factor on the
oculomotor activity of aviation security screeners. Analysis of possible instrumental
diagnostic methods of the functional status of aviation security screeners was
conducted and the Eye-tracking technology was selected as the one with the greatest
advantages. Overview of the experience in the application of the Eye-tracking
technology when diagnosing the functional status of aviation security screeners is
presented. In this paper for the first time as follows from experimental studies using
the Eye-tracking technology potential fatigue markers of aviation security screeners
with the most accurate changes were identified consistent with earlier studies pursued
by other authors. As the result of solving the problem of the statistical hypothesis
testing it is found that such oculomotor reactions as the blink frequency, the blink
duration average and the pupils diameter average can be used for diagnosing the
functional status of aviation security screeners whereas the saccade frequency did not
change for certain in the period of studies pursued and is not potentially useful for
monitoring. It was demonstrated that the Sugeno fuzzy model based on the subtractive
clustering and ANFIS-learning does better approximate the dependence between
oculomotor activity indicators of aviation security screeners and the prohibited items
detection efficiency in comparison with other models. Model fidelity by the Root-
Mean-Square Error criterion on the learning sample is 0,0348 and on the test sample
is 0,0858 as the case may be. Scientific and theoretical value of this paper involves
developing scientific knowledge related to the influence of the fatigue factor on the
oculomotor activity of aviation security screeners in the course of the working activity
Light Aircraft Landing Gear Strut Group 6 ReportRobert Tanner
The document analyzes materials for the landing gear strut of a Cessna TTX light aircraft. It translates design requirements into constraints and objectives, screens materials based on compressive strength and corrosion resistance, ranks materials based on indices that minimize weight and maximize buckling resistance and fatigue endurance. Magnesium alloy is selected as it is lightweight, inexpensive, and easier to manufacture than aluminum alloys, though composites are increasingly common in aircraft.
Stress and fatigue analysis of landing gear axle of a trainer aircrafteSAT Journals
Abstract The undercarriage or landing gear of an aircraft is the structure that supports an aircraft on the ground and allows it to taxi, takeoff and land. Among the various parts of landing gear, axle is the most critical component where the loads (landing and ground loads) act on the axle first, then transferred to the structure. In this study stress and fatigue analysis of the axle is performed to meet the strength and life requirements. The modeling of the axle is done using UniGraphics (UG) software. Stress analysis is carried out using MSC Patran (pre-processing and post-processing)/Nastran (solver) for different landing loads (spin up, spring back, maximum vertical and drift) and ground handling loads (braking, taxing and turning). Stress analysis was carried out by both classical and FEM approaches and by comparing the results it was obvious that they were in correlation with one another. Fatigue analysis was also carried out for the axle using landing spectrum and ground handling spectrum to estimate the fatigue life. By the iteration process, the requirement of 10000 landings was satisfied. Keywords: Static, Fatigue, Axle, Fatigue life, UniGraphics, MSC Patran, MSC Nastran
IRJET- Numerical Analysis of Nose Landing Gear SystemIRJET Journal
This document presents a numerical analysis of the nose landing gear system of an aircraft using finite element analysis. It begins with an abstract that outlines the objective to determine stress behavior and displacement of the nose gear during landing. It then describes the modeling process where the nose gear was modeled in CAD software and imported into finite element analysis software for meshing and application of loads and constraints. Key steps of the finite element analysis are described including discretization, deriving element equations, assembling global equations, applying loads/boundaries, and solving for results. Results of the finite element analysis such as stress contours, displacement contours, and natural frequencies are presented and discussed.
Fatigue fracture of a main landing gear swinging leverin a civil aircraftPramodKawade
The left main landing gear of an aircraft collapsed during takeoff due to fatigue fracture of the swinging lever after 26,139 flights. Fractography analysis revealed the fracture initiated from the surface of the lever near the most stressed region as identified by FEA stress analysis. Microstructural examination found an abnormal amount of silicon at the origin site which led to stress concentrations. AFGROW fatigue analysis using the FEA stress data predicted a fatigue life of 20,000 cycles, consistent with the actual life, indicating the failure occurred due to exceeding the fatigue life of the lever.
Design analysis of bumper beam subjected to offset impact loading for automot...IAEME Publication
This document discusses the design analysis of bumper beams subjected to offset impact loading for automotive applications. It aims to increase understanding of phenomena during offset impacts and validate modeling of bumper beam crash performance. Finite element analysis was conducted in ANSYS-LS DYNA to simulate impact on bumper beam-longitudinal systems made of different aluminum alloys (AA6060-T1, AA7003-T1, AA7003-T79). The results showed AA7003-T79 experienced the least deformation and minimized energy transfer, suggesting it is the best material for manufacturing bumper beam longitudinal systems.
As the Manager of Accident Prevention at Westinghouse Electric, Lewis Barbe, a safety engineer, received the National Safety Council Award for establishing a world safety record.
Car-pedestrian accidents account for a considerable number of automobile accidents in industrialized countries. Head injury continues to be more concerned in Automobile impacts.
Because the head is the most seriously injured part in many collisions including in pedestrian automobile collisions. Head injuries are the most common cause of pedestrian deaths in car to pedestrian collisions.
IRJET- Particle Swarm Intelligence based Dynamics Economic Dispatch with Dail...IRJET Journal
This document presents a structural and modal analysis of the wing of a subsonic aircraft using ANSYS Workbench. The study analyzes the wing structure made of two materials, aluminum alloy and titanium alloy, under a pressure load of 500 Pa to determine which is best suited. A 3D model of the wing is created based on the NACA 4412 airfoil dimensions and meshed. Boundary conditions fixing one end and applying pressure are applied. For each material, the total deformation, equivalent stress, maximum principle stress, and equivalent strain are determined from the static structural analysis and compared to select the best material for withstanding the loads in wing design.
Study of Aircraft Wing with Emphasis on Vibration CharacteristicsIJERA Editor
It is essential that the structural stability of the aircraft wings is a major consideration in the design of the aircraft. Many studies are being carried out for the design of the wings across the globe by the researches to strengthen the aircraft wings for steady and sturdy structures for dynamic conditions. The design of the aircraft wing using NACA standards is been discussed in this work. The wing analysis is carried out by using computer numerical analysis tool, viz., CAD/CAE and CFD. The necessary inputs for carrying out the structural analysis with emphasis on the vibration are obtained by CFD analysis. The deformation of the wing structures are investigated with respect to the standard airflow velocity. The velocity of air at the inlet is taken as 122 m/s (438 km/h), considering service ceiling of 7625 m at moderate temperature. The modal analysis is considered to analyse the wing to determine the natural frequency for vibration characteristics of the wing structure. The study of the effect of the stresses and deformations of the wing structure on the vibration characteristics of the wing is carried out to understand the effect of stress on natural frequency of the aircraft wing structure. Hence it is possible to correlate the effect of wind pressure on the vibration of the wing structure for particular design of the wing (NACA). The CFD results revealed that the pressure on the upper surface of the wing for all the wing section planes (butt planes-BL) is less, about -4.97e3N/mm2, as compared to the pressure on the lower surface, about 1.08e4 N/mm2, which satisfy the theory of lift generation. The pre-stressed modal analysis shows the correlation of the stress, deformation and the corresponding mode of vibration. It is found that the maximum deformation of 17.164 mm is corresponding to the modal frequency of 179.65 Hz which can be considered as design frequency of the wing structure. However the fundamental natural frequency of the wing structure is 10.352 Hz for the deformation of 11.383 mm.
Modal, Fatigue and Fracture Analysis of Wing Fuselage Lug Joint Bracket for a...IRJET Journal
This document summarizes a study on the modal, fatigue, and fracture analysis of a wing fuselage lug joint bracket for a transport aircraft. Finite element analysis was conducted in ANSYS to determine the modal frequencies and stress distributions. The first six natural frequencies were identified. Fatigue analysis using the Goodman diagram estimated the fatigue life to be 1 million cycles, qualifying it as a high cycle fatigue case. Fracture mechanics analysis identified maximum stresses near rivet holes and predicted crack initiation. The finite element analysis results for stresses, frequencies, and fatigue life were validated using analytical methods. The study aimed to understand the dynamic behavior and improve the structural integrity of the wing attachment point.
A Study on Damage Tolerance Evaluation of the Vertical Tail with the Z stiffe...IRJET Journal
This document discusses damage tolerance evaluation of the vertical tail with a stiffened panel on a transport aircraft. It begins with an introduction to aircraft structures and importance of vertical tails. Then it describes the stiffened panel that will be analyzed which makes up part of the vertical tail. Finite element analysis is performed to identify stress concentrations on the panel. A crack is initiated at the location of maximum stress and crack growth analysis is performed to evaluate the panel's damage tolerance capabilities. Stress intensity factors at the crack tip are calculated using the modified virtual crack closure integral method and compared to fracture toughness to assess crack growth.
Bend twist coupling effect on the Performance of the Wing of an Unmanned Aeri...IRJET Journal
This document discusses the design and analysis of a composite wing for an unmanned aerial vehicle (UAV) to minimize weight while maintaining stiffness and strength. Two wing models are created - one with all isotropic materials and one with composite materials. The composite wing is designed with glass-epoxy ribs and carbon-epoxy spars to take advantage of intrinsic bend-twist coupling effects. The wing models are analyzed in ANSYS to compare the performance of composite and isotropic materials. The results show that a composite wing can achieve lower weight without compromising structural performance.
FE Based Crash Simulation of Belly Landing of a Light Transport AircraftRSIS International
Crash survivability is one of the key features to be
attended during the design of an airworthy aircraft. Belly/crash
landing is the most common phenomenon to be considered in
developing a crashworthy product. That makes it essential to
have redundant structure to enhance the safety of occupants and
also limit the damage to easily repairable state in case of such
event. Even from the certification point of view, it is necessary to
investigate this event by test/analysis. Recent development of
advance computing and their capability to simulate such
phenomenon to acceptable accuracy under given conditions
conveniently replace the need for test which is otherwise costly.
At the same time, one has to be cautious while selecting the
modeling parameters to simulate the condition near to reality.
Taking advantage of this feature an effort is made to simulate the
belly landing and its consequences on the structure complying to
the guidelines of the federal aviation regulations. This paper
presents the methodology adopted to successfully simulate the
belly landing phenomenon for a light transport aircraft flying
prototype.
FATIGUE ASSESSMENT OF DATA ACQUISITION SYSTEM UNDER RANDOM VIBRATION LOAD FOR...IAEME Publication
This paper targets the reliability of Data Acquisition System through Fatigue
assessment under Random Vibration conditions. The fixed wing aircraft generate the
random vibrations during the entire sortie and are imposed on the avionics systems
installed on the platform. The limits defined as per MIL-STD-810D are superimposed
for assessment of Fatigue. Fatigue assessment of Data Acquisition System procedure
is presented and each step of the procedure is explained. A finite element model of the
system is built in ANSYS software Version R15.0 after generating a 3D CAD model in
SOLIDEDGE Software Version ST 7.0. The model is evaluated for stresses generated
on imposing Random Vibration loading for One Hour each in X, Y and Z axes. The
natural frequencies in all three axes were determined. The fatigue life assessment has
been done for Cumulative damage using Miner’s damage rule. The study of fatigue
assessment results in that Data Acquisition System has residual life and it can sustain
random vibration loading of further 15.18 hrs
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
The papers for publication in The International Journal of Engineering& Science are selected through rigorous peer reviews to ensure originality, timeliness, relevance, and readability.
Structural Analysis and Optimization for Spar Beam of an AircraftIRJET Journal
This document summarizes a study analyzing and optimizing the structural design of a tapered spar beam for an aircraft wing. The study involved creating a geometric model of the spar beam, applying loads and boundary conditions representative of flight loading, conducting a finite element analysis to determine stresses and displacements, and performing topological optimization to reduce weight. Key results were stresses of up to 38 MPa at the fixed end of the beam, displacements of up to 3.1 mm at the free end, and a 40% reduction in web weight achieved through topological optimization while maintaining structural integrity. The optimized design demonstrated potential to strengthen the spar beam structure while reducing material usage and weight.
The document discusses design modifications and enhancements to the adaptability of mooring structures for medium-sized aerostats. It proposes three main modifications:
1) Mounting a bearing at the top of the mooring tower to eliminate twisting moments and reduce stresses.
2) Making the air bag frame adjustable to provide constant cushioned support to the balloon and keep it horizontal.
3) Fastening length pieces to allow the same structure to moor balloons of different sizes. Finite element analysis demonstrates that the modifications significantly reduce stresses on the structure.
Coupled Euler Lagrangian Approach Using Abaqus /Explicit in the Bird Strike A...SIMULIA
Bird impact damage in complex aircraft structure has been investigated using explicit transient dynamic analysis by Abaqus/Explicit in order to fully employ its large library of elements, material models and the ability of implementing user defined materials. The numerical procedure has been applied on the very detailed large airplane secondary structure consisting of sandwich, composite and metallic structural items that have been modeled with 3D, shell and continuum shell elements, coupled with appropriate kinematic constraints. Bird has been modeled using Coupled Euler Lagrangian approach, in order to avoid the numerical difficulties connected with the mesh. The impact has been applied in the area that is the most probably subjected to the impact damage during the exploitation. The application point and velocity vector have been varied and the comparisons between total, kinetic, internal and damage energies have been performed. Various failure modes, such as CFRP face layer rupture, failure of composite matrix, damage initiation / evolution in the Nomex core and elastoplastic failure of a metallic structure have been investigated. Besides, general contact has been applied as to efficiently capture the contact between impactor and structure, as well as large deformations of the different structural components. Visualization of failure modes has been performed and damaged area compared to the available references. Compared to the classic Lagrangian modeling of the bird, the analysis has proven to be more stable, and the results, such as and damage areas, physically more realistic.
CFD Analysis of Delta Winged Aircraft – A ReviewIRJET Journal
This document reviews computational fluid dynamics (CFD) analysis that has been conducted on delta wing aircraft and airfoils with surface modifications like dimples. Several studies are summarized that used CFD to analyze how dimples affect lift and drag on airfoils at various angles of attack. Dimples function similarly to vortex generators by creating vortices that delay flow separation and reduce pressure drag. Researchers have found that dimples can increase an aircraft's aerodynamic performance characteristics and maneuverability by reducing drag and stall. The document reviews multiple studies that analyzed different dimple shapes and configurations on symmetric and asymmetric airfoil profiles.
This is seminar report of ageing of aircraft.this useful for those student who want to give seminar on designing area of aircraft.In this report you will find brief introduction of ageing of aircraft.
Landing gear Failure analysis of an aircraftRohit Katarya
The document analyzes potential failures of aircraft landing gear components. It discusses the main eight components of landing gear, including locks, retraction systems, brakes, wheels, and struts. Failure mechanisms like fatigue cracking, stress corrosion cracking, and dynamic failure during landing are examined. The materials used for landing gear like high-strength steels, titanium, aluminum, and magnesium alloys are also summarized. Non-destructive testing and new techniques for early fatigue detection are reviewed as ways to improve landing gear safety and maintenance.
Static and Dynamic Analysis of Floor Beam (Cross beam) of AircraftIRJET Journal
This document summarizes a study analyzing the static and dynamic behavior of floor beams used in aircraft. Floor beams experience bending stresses and support the weight of the aircraft. The researchers modeled a floor beam in CATIA and analyzed it in ANSYS to study stresses under different loads. They also analyzed a carbon fiber reinforced plastic floor beam. Modal analysis determined the beam's natural frequencies under vibration to ensure it can withstand operating conditions. The study aims to optimize floor beam design and materials to reduce weight while maintaining strength.
A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehi...Designage Solutions
A brief study of flight dynamics and different types of simulation and analysis are presented here.
Find case studies in my next PPT.- http://www.slideshare.net/HarshadaGurav/flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
Damage tolerance evaluation of wing in presence of large landing gear cutout ...eSAT Journals
Abstract Aircraft is symbol of a high performance mechanical structure, which has the ability to fly with a very high structural safety record. Aircraft experiences variable loading in service. Rarely an aircraft will fail due to a static overload during its service life. For the continued airworthiness of an aircraft during its entire economic service life, fatigue and damage tolerance design, analysis, testing and service experience correlation play a pivotal role. The present study includes the stress analysis and damage tolerance evaluation of the wing through a stiffened panel of the bottom skin with a landing gear cutout. Wing bottom skin experiences tensile stress field during flight. Cutouts required for fuel access and landing gear opening and retraction in the bottom skin will introduce stress concentration. Fatigue cracks will initiate from high tensile stress locations. An integral stiffened panel consisting a landing gear cutout is considered for the analysis. Stress analysis will identify the maximum tensile stress location in the panel. In a metallic structure fatigue manifests itself in the form of a crack which propagates. If the crack in a critical location goes unnoticed it could lead to a catastrophic failure of the airframe. A critical condition will occur when the stress intensity factor (SIF) at the crack tip becomes equal to fracture toughness of the material. SIF calculations will be carried out for a crack with incremental crack lengths using MVCCI method. Analytical evaluation of the crack arrest capability of the stiffening members ahead of the crack tip will be carried out. Index Terms: Key Aircraft, Design, wing, landing gear cutout, stress analysis, FEM, damage tolerance, integral stiffened panel.
Damage tolerance evaluation of wing in presence of large landing gear cutout ...eSAT Publishing House
The document discusses stress analysis and damage tolerance evaluation of the wing of an aircraft through finite element modeling of a stiffened panel with a large landing gear cutout. The analysis identifies the maximum stress location where fatigue cracks are likely to initiate and calculates stress intensity factors as crack lengths increase to determine the crack arrest capability of stiffening members. The study aims to evaluate the structural safety and damage tolerance of the wing in the presence of the landing gear cutout.
The structural analysis is an important tool that allows the research for weight reduction, the choose of the best materials and to satisfy specifications and requirements. In an aircraft’s design, several analyzes are made to prove that this aircraft will stand the set of maneuvers that it was designed to accomplish. This work will consider the preliminar project of an aircraft seeking to check the behavior of the wing under certain loading conditions in the flight envelope.To get to this load set, it has been done all the process of specification of an aircraft, such as mission definition, calculation of weight and c.g. envelope, definition of the geometric characteristics of the aircraft, the airfoil choice, preliminary performance equations, aerodynamic coefficients and the aircraft’s balancing for the equilibrium condition, but such things will not be considered in this article. For the structural analysis of the wing will be considered an arbitrary flight condition, disregarding the effect of gusts loads. With the acquisition of the items mentioned, the main forces acting on the wing structure and their equations will be calculated. The use of finite element method will enable the application of loads obtained just as the development of a method of calculation, along with the construction of a three-dimensional model that represents a chosen condition. The results will be discussed in order to explain the influence of the applied loads in the structural behavior of the wing principal structure.
structures technology for future aerospace systemszengfm2000
This document provides an overview of structures technology for future aerospace systems. It discusses six key component technologies: 1) smart materials and structures that can sense and respond to stimuli, 2) multifunctional materials and structures that integrate functions like sensors and antennas, 3) affordable composite structures using improved manufacturing, 4) extreme environment structures, 5) flexible load-bearing structures, and 6) computational simulation methods. The technologies aim to improve performance, reduce costs, and enable new vehicle concepts. Challenges include qualifying smart materials for operational environments and developing maintenance procedures.
Submission Deadline: 30th September 2022
Acceptance Notification: Within Three Days’ time period
Online Publication: Within 24 Hrs. time Period
Expected Date of Dispatch of Printed Journal: 5th October 2022
MODELING AND ANALYSIS OF SURFACE ROUGHNESS AND WHITE LATER THICKNESS IN WIRE-...IAEME Publication
White layer thickness (WLT) formed and surface roughness in wire electric discharge turning (WEDT) of tungsten carbide composite has been made to model through response surface methodology (RSM). A Taguchi’s standard Design of experiments involving five input variables with three levels has been employed to establish a mathematical model between input parameters and responses. Percentage of cobalt content, spindle speed, Pulse on-time, wire feed and pulse off-time were changed during the experimental tests based on the Taguchi’s orthogonal array L27 (3^13). Analysis of variance (ANOVA) revealed that the mathematical models obtained can adequately describe performance within the parameters of the factors considered. There was a good agreement between the experimental and predicted values in this study.
More Related Content
Similar to DETECTION OF DAMAGE IN STIFFENERS OF AIRCRAFT WING STRUCTURE BASED ON INDUCED SKIN STRAINS AND LATERAL DEFLECTIONS
IRJET- Particle Swarm Intelligence based Dynamics Economic Dispatch with Dail...IRJET Journal
This document presents a structural and modal analysis of the wing of a subsonic aircraft using ANSYS Workbench. The study analyzes the wing structure made of two materials, aluminum alloy and titanium alloy, under a pressure load of 500 Pa to determine which is best suited. A 3D model of the wing is created based on the NACA 4412 airfoil dimensions and meshed. Boundary conditions fixing one end and applying pressure are applied. For each material, the total deformation, equivalent stress, maximum principle stress, and equivalent strain are determined from the static structural analysis and compared to select the best material for withstanding the loads in wing design.
Study of Aircraft Wing with Emphasis on Vibration CharacteristicsIJERA Editor
It is essential that the structural stability of the aircraft wings is a major consideration in the design of the aircraft. Many studies are being carried out for the design of the wings across the globe by the researches to strengthen the aircraft wings for steady and sturdy structures for dynamic conditions. The design of the aircraft wing using NACA standards is been discussed in this work. The wing analysis is carried out by using computer numerical analysis tool, viz., CAD/CAE and CFD. The necessary inputs for carrying out the structural analysis with emphasis on the vibration are obtained by CFD analysis. The deformation of the wing structures are investigated with respect to the standard airflow velocity. The velocity of air at the inlet is taken as 122 m/s (438 km/h), considering service ceiling of 7625 m at moderate temperature. The modal analysis is considered to analyse the wing to determine the natural frequency for vibration characteristics of the wing structure. The study of the effect of the stresses and deformations of the wing structure on the vibration characteristics of the wing is carried out to understand the effect of stress on natural frequency of the aircraft wing structure. Hence it is possible to correlate the effect of wind pressure on the vibration of the wing structure for particular design of the wing (NACA). The CFD results revealed that the pressure on the upper surface of the wing for all the wing section planes (butt planes-BL) is less, about -4.97e3N/mm2, as compared to the pressure on the lower surface, about 1.08e4 N/mm2, which satisfy the theory of lift generation. The pre-stressed modal analysis shows the correlation of the stress, deformation and the corresponding mode of vibration. It is found that the maximum deformation of 17.164 mm is corresponding to the modal frequency of 179.65 Hz which can be considered as design frequency of the wing structure. However the fundamental natural frequency of the wing structure is 10.352 Hz for the deformation of 11.383 mm.
Modal, Fatigue and Fracture Analysis of Wing Fuselage Lug Joint Bracket for a...IRJET Journal
This document summarizes a study on the modal, fatigue, and fracture analysis of a wing fuselage lug joint bracket for a transport aircraft. Finite element analysis was conducted in ANSYS to determine the modal frequencies and stress distributions. The first six natural frequencies were identified. Fatigue analysis using the Goodman diagram estimated the fatigue life to be 1 million cycles, qualifying it as a high cycle fatigue case. Fracture mechanics analysis identified maximum stresses near rivet holes and predicted crack initiation. The finite element analysis results for stresses, frequencies, and fatigue life were validated using analytical methods. The study aimed to understand the dynamic behavior and improve the structural integrity of the wing attachment point.
A Study on Damage Tolerance Evaluation of the Vertical Tail with the Z stiffe...IRJET Journal
This document discusses damage tolerance evaluation of the vertical tail with a stiffened panel on a transport aircraft. It begins with an introduction to aircraft structures and importance of vertical tails. Then it describes the stiffened panel that will be analyzed which makes up part of the vertical tail. Finite element analysis is performed to identify stress concentrations on the panel. A crack is initiated at the location of maximum stress and crack growth analysis is performed to evaluate the panel's damage tolerance capabilities. Stress intensity factors at the crack tip are calculated using the modified virtual crack closure integral method and compared to fracture toughness to assess crack growth.
Bend twist coupling effect on the Performance of the Wing of an Unmanned Aeri...IRJET Journal
This document discusses the design and analysis of a composite wing for an unmanned aerial vehicle (UAV) to minimize weight while maintaining stiffness and strength. Two wing models are created - one with all isotropic materials and one with composite materials. The composite wing is designed with glass-epoxy ribs and carbon-epoxy spars to take advantage of intrinsic bend-twist coupling effects. The wing models are analyzed in ANSYS to compare the performance of composite and isotropic materials. The results show that a composite wing can achieve lower weight without compromising structural performance.
FE Based Crash Simulation of Belly Landing of a Light Transport AircraftRSIS International
Crash survivability is one of the key features to be
attended during the design of an airworthy aircraft. Belly/crash
landing is the most common phenomenon to be considered in
developing a crashworthy product. That makes it essential to
have redundant structure to enhance the safety of occupants and
also limit the damage to easily repairable state in case of such
event. Even from the certification point of view, it is necessary to
investigate this event by test/analysis. Recent development of
advance computing and their capability to simulate such
phenomenon to acceptable accuracy under given conditions
conveniently replace the need for test which is otherwise costly.
At the same time, one has to be cautious while selecting the
modeling parameters to simulate the condition near to reality.
Taking advantage of this feature an effort is made to simulate the
belly landing and its consequences on the structure complying to
the guidelines of the federal aviation regulations. This paper
presents the methodology adopted to successfully simulate the
belly landing phenomenon for a light transport aircraft flying
prototype.
FATIGUE ASSESSMENT OF DATA ACQUISITION SYSTEM UNDER RANDOM VIBRATION LOAD FOR...IAEME Publication
This paper targets the reliability of Data Acquisition System through Fatigue
assessment under Random Vibration conditions. The fixed wing aircraft generate the
random vibrations during the entire sortie and are imposed on the avionics systems
installed on the platform. The limits defined as per MIL-STD-810D are superimposed
for assessment of Fatigue. Fatigue assessment of Data Acquisition System procedure
is presented and each step of the procedure is explained. A finite element model of the
system is built in ANSYS software Version R15.0 after generating a 3D CAD model in
SOLIDEDGE Software Version ST 7.0. The model is evaluated for stresses generated
on imposing Random Vibration loading for One Hour each in X, Y and Z axes. The
natural frequencies in all three axes were determined. The fatigue life assessment has
been done for Cumulative damage using Miner’s damage rule. The study of fatigue
assessment results in that Data Acquisition System has residual life and it can sustain
random vibration loading of further 15.18 hrs
The International Journal of Engineering & Science is aimed at providing a platform for researchers, engineers, scientists, or educators to publish their original research results, to exchange new ideas, to disseminate information in innovative designs, engineering experiences and technological skills. It is also the Journal's objective to promote engineering and technology education. All papers submitted to the Journal will be blind peer-reviewed. Only original articles will be published.
The papers for publication in The International Journal of Engineering& Science are selected through rigorous peer reviews to ensure originality, timeliness, relevance, and readability.
Structural Analysis and Optimization for Spar Beam of an AircraftIRJET Journal
This document summarizes a study analyzing and optimizing the structural design of a tapered spar beam for an aircraft wing. The study involved creating a geometric model of the spar beam, applying loads and boundary conditions representative of flight loading, conducting a finite element analysis to determine stresses and displacements, and performing topological optimization to reduce weight. Key results were stresses of up to 38 MPa at the fixed end of the beam, displacements of up to 3.1 mm at the free end, and a 40% reduction in web weight achieved through topological optimization while maintaining structural integrity. The optimized design demonstrated potential to strengthen the spar beam structure while reducing material usage and weight.
The document discusses design modifications and enhancements to the adaptability of mooring structures for medium-sized aerostats. It proposes three main modifications:
1) Mounting a bearing at the top of the mooring tower to eliminate twisting moments and reduce stresses.
2) Making the air bag frame adjustable to provide constant cushioned support to the balloon and keep it horizontal.
3) Fastening length pieces to allow the same structure to moor balloons of different sizes. Finite element analysis demonstrates that the modifications significantly reduce stresses on the structure.
Coupled Euler Lagrangian Approach Using Abaqus /Explicit in the Bird Strike A...SIMULIA
Bird impact damage in complex aircraft structure has been investigated using explicit transient dynamic analysis by Abaqus/Explicit in order to fully employ its large library of elements, material models and the ability of implementing user defined materials. The numerical procedure has been applied on the very detailed large airplane secondary structure consisting of sandwich, composite and metallic structural items that have been modeled with 3D, shell and continuum shell elements, coupled with appropriate kinematic constraints. Bird has been modeled using Coupled Euler Lagrangian approach, in order to avoid the numerical difficulties connected with the mesh. The impact has been applied in the area that is the most probably subjected to the impact damage during the exploitation. The application point and velocity vector have been varied and the comparisons between total, kinetic, internal and damage energies have been performed. Various failure modes, such as CFRP face layer rupture, failure of composite matrix, damage initiation / evolution in the Nomex core and elastoplastic failure of a metallic structure have been investigated. Besides, general contact has been applied as to efficiently capture the contact between impactor and structure, as well as large deformations of the different structural components. Visualization of failure modes has been performed and damaged area compared to the available references. Compared to the classic Lagrangian modeling of the bird, the analysis has proven to be more stable, and the results, such as and damage areas, physically more realistic.
CFD Analysis of Delta Winged Aircraft – A ReviewIRJET Journal
This document reviews computational fluid dynamics (CFD) analysis that has been conducted on delta wing aircraft and airfoils with surface modifications like dimples. Several studies are summarized that used CFD to analyze how dimples affect lift and drag on airfoils at various angles of attack. Dimples function similarly to vortex generators by creating vortices that delay flow separation and reduce pressure drag. Researchers have found that dimples can increase an aircraft's aerodynamic performance characteristics and maneuverability by reducing drag and stall. The document reviews multiple studies that analyzed different dimple shapes and configurations on symmetric and asymmetric airfoil profiles.
This is seminar report of ageing of aircraft.this useful for those student who want to give seminar on designing area of aircraft.In this report you will find brief introduction of ageing of aircraft.
Landing gear Failure analysis of an aircraftRohit Katarya
The document analyzes potential failures of aircraft landing gear components. It discusses the main eight components of landing gear, including locks, retraction systems, brakes, wheels, and struts. Failure mechanisms like fatigue cracking, stress corrosion cracking, and dynamic failure during landing are examined. The materials used for landing gear like high-strength steels, titanium, aluminum, and magnesium alloys are also summarized. Non-destructive testing and new techniques for early fatigue detection are reviewed as ways to improve landing gear safety and maintenance.
Static and Dynamic Analysis of Floor Beam (Cross beam) of AircraftIRJET Journal
This document summarizes a study analyzing the static and dynamic behavior of floor beams used in aircraft. Floor beams experience bending stresses and support the weight of the aircraft. The researchers modeled a floor beam in CATIA and analyzed it in ANSYS to study stresses under different loads. They also analyzed a carbon fiber reinforced plastic floor beam. Modal analysis determined the beam's natural frequencies under vibration to ensure it can withstand operating conditions. The study aims to optimize floor beam design and materials to reduce weight while maintaining strength.
A Review of Flight Dynamics and Numerical Analysis of an Unmanned Aerial Vehi...Designage Solutions
A brief study of flight dynamics and different types of simulation and analysis are presented here.
Find case studies in my next PPT.- http://www.slideshare.net/HarshadaGurav/flight-dynamics-and-numerical-analysis-of-an-unmanned-aerial-vehicle-uav
Damage tolerance evaluation of wing in presence of large landing gear cutout ...eSAT Journals
Abstract Aircraft is symbol of a high performance mechanical structure, which has the ability to fly with a very high structural safety record. Aircraft experiences variable loading in service. Rarely an aircraft will fail due to a static overload during its service life. For the continued airworthiness of an aircraft during its entire economic service life, fatigue and damage tolerance design, analysis, testing and service experience correlation play a pivotal role. The present study includes the stress analysis and damage tolerance evaluation of the wing through a stiffened panel of the bottom skin with a landing gear cutout. Wing bottom skin experiences tensile stress field during flight. Cutouts required for fuel access and landing gear opening and retraction in the bottom skin will introduce stress concentration. Fatigue cracks will initiate from high tensile stress locations. An integral stiffened panel consisting a landing gear cutout is considered for the analysis. Stress analysis will identify the maximum tensile stress location in the panel. In a metallic structure fatigue manifests itself in the form of a crack which propagates. If the crack in a critical location goes unnoticed it could lead to a catastrophic failure of the airframe. A critical condition will occur when the stress intensity factor (SIF) at the crack tip becomes equal to fracture toughness of the material. SIF calculations will be carried out for a crack with incremental crack lengths using MVCCI method. Analytical evaluation of the crack arrest capability of the stiffening members ahead of the crack tip will be carried out. Index Terms: Key Aircraft, Design, wing, landing gear cutout, stress analysis, FEM, damage tolerance, integral stiffened panel.
Damage tolerance evaluation of wing in presence of large landing gear cutout ...eSAT Publishing House
The document discusses stress analysis and damage tolerance evaluation of the wing of an aircraft through finite element modeling of a stiffened panel with a large landing gear cutout. The analysis identifies the maximum stress location where fatigue cracks are likely to initiate and calculates stress intensity factors as crack lengths increase to determine the crack arrest capability of stiffening members. The study aims to evaluate the structural safety and damage tolerance of the wing in the presence of the landing gear cutout.
The structural analysis is an important tool that allows the research for weight reduction, the choose of the best materials and to satisfy specifications and requirements. In an aircraft’s design, several analyzes are made to prove that this aircraft will stand the set of maneuvers that it was designed to accomplish. This work will consider the preliminar project of an aircraft seeking to check the behavior of the wing under certain loading conditions in the flight envelope.To get to this load set, it has been done all the process of specification of an aircraft, such as mission definition, calculation of weight and c.g. envelope, definition of the geometric characteristics of the aircraft, the airfoil choice, preliminary performance equations, aerodynamic coefficients and the aircraft’s balancing for the equilibrium condition, but such things will not be considered in this article. For the structural analysis of the wing will be considered an arbitrary flight condition, disregarding the effect of gusts loads. With the acquisition of the items mentioned, the main forces acting on the wing structure and their equations will be calculated. The use of finite element method will enable the application of loads obtained just as the development of a method of calculation, along with the construction of a three-dimensional model that represents a chosen condition. The results will be discussed in order to explain the influence of the applied loads in the structural behavior of the wing principal structure.
structures technology for future aerospace systemszengfm2000
This document provides an overview of structures technology for future aerospace systems. It discusses six key component technologies: 1) smart materials and structures that can sense and respond to stimuli, 2) multifunctional materials and structures that integrate functions like sensors and antennas, 3) affordable composite structures using improved manufacturing, 4) extreme environment structures, 5) flexible load-bearing structures, and 6) computational simulation methods. The technologies aim to improve performance, reduce costs, and enable new vehicle concepts. Challenges include qualifying smart materials for operational environments and developing maintenance procedures.
Similar to DETECTION OF DAMAGE IN STIFFENERS OF AIRCRAFT WING STRUCTURE BASED ON INDUCED SKIN STRAINS AND LATERAL DEFLECTIONS (20)
Submission Deadline: 30th September 2022
Acceptance Notification: Within Three Days’ time period
Online Publication: Within 24 Hrs. time Period
Expected Date of Dispatch of Printed Journal: 5th October 2022
MODELING AND ANALYSIS OF SURFACE ROUGHNESS AND WHITE LATER THICKNESS IN WIRE-...IAEME Publication
White layer thickness (WLT) formed and surface roughness in wire electric discharge turning (WEDT) of tungsten carbide composite has been made to model through response surface methodology (RSM). A Taguchi’s standard Design of experiments involving five input variables with three levels has been employed to establish a mathematical model between input parameters and responses. Percentage of cobalt content, spindle speed, Pulse on-time, wire feed and pulse off-time were changed during the experimental tests based on the Taguchi’s orthogonal array L27 (3^13). Analysis of variance (ANOVA) revealed that the mathematical models obtained can adequately describe performance within the parameters of the factors considered. There was a good agreement between the experimental and predicted values in this study.
A STUDY ON THE REASONS FOR TRANSGENDER TO BECOME ENTREPRENEURSIAEME Publication
The study explores the reasons for a transgender to become entrepreneurs. In this study transgender entrepreneur was taken as independent variable and reasons to become as dependent variable. Data were collected through a structured questionnaire containing a five point Likert Scale. The study examined the data of 30 transgender entrepreneurs in Salem Municipal Corporation of Tamil Nadu State, India. Simple Random sampling technique was used. Garrett Ranking Technique (Percentile Position, Mean Scores) was used as the analysis for the present study to identify the top 13 stimulus factors for establishment of trans entrepreneurial venture. Economic advancement of a nation is governed upon the upshot of a resolute entrepreneurial doings. The conception of entrepreneurship has stretched and materialized to the socially deflated uncharted sections of transgender community. Presently transgenders have smashed their stereotypes and are making recent headlines of achievements in various fields of our Indian society. The trans-community is gradually being observed in a new light and has been trying to achieve prospective growth in entrepreneurship. The findings of the research revealed that the optimistic changes are taking place to change affirmative societal outlook of the transgender for entrepreneurial ventureship. It also laid emphasis on other transgenders to renovate their traditional living. The paper also highlights that legislators, supervisory body should endorse an impartial canons and reforms in Tamil Nadu Transgender Welfare Board Association.
BROAD UNEXPOSED SKILLS OF TRANSGENDER ENTREPRENEURSIAEME Publication
Since ages gender difference is always a debatable theme whether caused by nature, evolution or environment. The birth of a transgender is dreadful not only for the child but also for their parents. The pain of living in the wrong physique and treated as second class victimized citizen is outrageous and fully harboured with vicious baseless negative scruples. For so long, social exclusion had perpetuated inequality and deprivation experiencing ingrained malign stigma and besieged victims of crime or violence across their life spans. They are pushed into the murky way of life with a source of eternal disgust, bereft sexual potency and perennial fear. Although they are highly visible but very little is known about them. The common public needs to comprehend the ravaged arrogance on these insensitive souls and assist in integrating them into the mainstream by offering equal opportunity, treat with humanity and respect their dignity. Entrepreneurship in the current age is endorsing the gender fairness movement. Unstable careers and economic inadequacy had inclined one of the gender variant people called Transgender to become entrepreneurs. These tiny budding entrepreneurs resulted in economic transition by means of employment, free from the clutches of stereotype jobs, raised standard of living and handful of financial empowerment. Besides all these inhibitions, they were able to witness a platform for skill set development that ignited them to enter into entrepreneurial domain. This paper epitomizes skill sets involved in trans-entrepreneurs of Thoothukudi Municipal Corporation of Tamil Nadu State and is a groundbreaking determination to sightsee various skills incorporated and the impact on entrepreneurship.
DETERMINANTS AFFECTING THE USER'S INTENTION TO USE MOBILE BANKING APPLICATIONSIAEME Publication
The banking and financial services industries are experiencing increased technology penetration. Among them, the banking industry has made technological advancements to better serve the general populace. The economy focused on transforming the banking sector's system into a cashless, paperless, and faceless one. The researcher wants to evaluate the user's intention for utilising a mobile banking application. The study also examines the variables affecting the user's behaviour intention when selecting specific applications for financial transactions. The researcher employed a well-structured questionnaire and a descriptive study methodology to gather the respondents' primary data utilising the snowball sampling technique. The study includes variables like performance expectations, effort expectations, social impact, enabling circumstances, and perceived risk. Each of the aforementioned variables has a major impact on how users utilise mobile banking applications. The outcome will assist the service provider in comprehending the user's history with mobile banking applications.
ANALYSE THE USER PREDILECTION ON GPAY AND PHONEPE FOR DIGITAL TRANSACTIONSIAEME Publication
Technology upgradation in banking sector took the economy to view that payment mode towards online transactions using mobile applications. This system enabled connectivity between banks, Merchant and user in a convenient mode. there are various applications used for online transactions such as Google pay, Paytm, freecharge, mobikiwi, oxygen, phonepe and so on and it also includes mobile banking applications. The study aimed at evaluating the predilection of the user in adopting digital transaction. The study is descriptive in nature. The researcher used random sample techniques to collect the data. The findings reveal that mobile applications differ with the quality of service rendered by Gpay and Phonepe. The researcher suggest the Phonepe application should focus on implementing the application should be user friendly interface and Gpay on motivating the users to feel the importance of request for money and modes of payments in the application.
VOICE BASED ATM FOR VISUALLY IMPAIRED USING ARDUINOIAEME Publication
The prototype of a voice-based ATM for visually impaired using Arduino is to help people who are blind. This uses RFID cards which contain users fingerprint encrypted on it and interacts with the users through voice commands. ATM operates when sensor detects the presence of one person in the cabin. After scanning the RFID card, it will ask to select the mode like –normal or blind. User can select the respective mode through voice input, if blind mode is selected the balance check or cash withdraw can be done through voice input. Normal mode procedure is same as the existing ATM.
IMPACT OF EMOTIONAL INTELLIGENCE ON HUMAN RESOURCE MANAGEMENT PRACTICES AMONG...IAEME Publication
There is increasing acceptability of emotional intelligence as a major factor in personality assessment and effective human resource management. Emotional intelligence as the ability to build capacity, empathize, co-operate, motivate and develop others cannot be divorced from both effective performance and human resource management systems. The human person is crucial in defining organizational leadership and fortunes in terms of challenges and opportunities and walking across both multinational and bilateral relationships. The growing complexity of the business world requires a great deal of self-confidence, integrity, communication, conflict and diversity management to keep the global enterprise within the paths of productivity and sustainability. Using the exploratory research design and 255 participants the result of this original study indicates strong positive correlation between emotional intelligence and effective human resource management. The paper offers suggestions on further studies between emotional intelligence and human capital development and recommends for conflict management as an integral part of effective human resource management.
VISUALISING AGING PARENTS & THEIR CLOSE CARERS LIFE JOURNEY IN AGING ECONOMYIAEME Publication
Our life journey, in general, is closely defined by the way we understand the meaning of why we coexist and deal with its challenges. As we develop the "inspiration economy", we could say that nearly all of the challenges we have faced are opportunities that help us to discover the rest of our journey. In this note paper, we explore how being faced with the opportunity of being a close carer for an aging parent with dementia brought intangible discoveries that changed our insight of the meaning of the rest of our life journey.
A STUDY ON THE IMPACT OF ORGANIZATIONAL CULTURE ON THE EFFECTIVENESS OF PERFO...IAEME Publication
The main objective of this study is to analyze the impact of aspects of Organizational Culture on the Effectiveness of the Performance Management System (PMS) in the Health Care Organization at Thanjavur. Organizational Culture and PMS play a crucial role in present-day organizations in achieving their objectives. PMS needs employees’ cooperation to achieve its intended objectives. Employees' cooperation depends upon the organization’s culture. The present study uses exploratory research to examine the relationship between the Organization's culture and the Effectiveness of the Performance Management System. The study uses a Structured Questionnaire to collect the primary data. For this study, Thirty-six non-clinical employees were selected from twelve randomly selected Health Care organizations at Thanjavur. Thirty-two fully completed questionnaires were received.
Living in 21st century in itself reminds all of us the necessity of police and its administration. As more and more we are entering into the modern society and culture, the more we require the services of the so called ‘Khaki Worthy’ men i.e., the police personnel. Whether we talk of Indian police or the other nation’s police, they all have the same recognition as they have in India. But as already mentioned, their services and requirements are different after the like 26th November, 2008 incidents, where they without saving their own lives has sacrificed themselves without any hitch and without caring about their respective family members and wards. In other words, they are like our heroes and mentors who can guide us from the darkness of fear, militancy, corruption and other dark sides of life and so on. Now the question arises, if Gandhi would have been alive today, what would have been his reaction/opinion to the police and its functioning? Would he have some thing different in his mind now what he had been in his mind before the partition or would he be going to start some Satyagraha in the form of some improvement in the functioning of the police administration? Really these questions or rather night mares can come to any one’s mind, when there is too much confusion is prevailing in our minds, when there is too much corruption in the society and when the polices working is also in the questioning because of one or the other case throughout the India. It is matter of great concern that we have to thing over our administration and our practical approach because the police personals are also like us, they are part and parcel of our society and among one of us, so why we all are pin pointing towards them.
A STUDY ON TALENT MANAGEMENT AND ITS IMPACT ON EMPLOYEE RETENTION IN SELECTED...IAEME Publication
The goal of this study was to see how talent management affected employee retention in the selected IT organizations in Chennai. The fundamental issue was the difficulty to attract, hire, and retain talented personnel who perform well and the gap between supply and demand of talent acquisition and retaining them within the firms. The study's main goals were to determine the impact of talent management on employee retention in IT companies in Chennai, investigate talent management strategies that IT companies could use to improve talent acquisition, performance management, career planning and formulate retention strategies that the IT firms could use. The respondents were given a structured close-ended questionnaire with the 5 Point Likert Scale as part of the study's quantitative research design. The target population consisted of 289 IT professionals. The questionnaires were distributed and collected by the researcher directly. The Statistical Package for Social Sciences (SPSS) was used to collect and analyse the questionnaire responses. Hypotheses that were formulated for the various areas of the study were tested using a variety of statistical tests. The key findings of the study suggested that talent management had an impact on employee retention. The studies also found that there is a clear link between the implementation of talent management and retention measures. Management should provide enough training and development for employees, clarify job responsibilities, provide adequate remuneration packages, and recognise employees for exceptional performance.
ATTRITION IN THE IT INDUSTRY DURING COVID-19 PANDEMIC: LINKING EMOTIONAL INTE...IAEME Publication
Globally, Millions of dollars were spent by the organizations for employing skilled Information Technology (IT) professionals. It is costly to replace unskilled employees with IT professionals possessing technical skills and competencies that aid in interconnecting the business processes. The organization’s employment tactics were forced to alter by globalization along with technological innovations as they consistently diminish to remain lean, outsource to concentrate on core competencies along with restructuring/reallocate personnel to gather efficiency. As other jobs, organizations or professions have become reasonably more appropriate in a shifting employment landscape, the above alterations trigger both involuntary as well as voluntary turnover. The employee view on jobs is also afflicted by the COVID-19 pandemic along with the employee-driven labour market. So, having effective strategies is necessary to tackle the withdrawal rate of employees. By associating Emotional Intelligence (EI) along with Talent Management (TM) in the IT industry, the rise in attrition rate was analyzed in this study. Only 303 respondents were collected out of 350 participants to whom questionnaires were distributed. From the employees of IT organizations located in Bangalore (India), the data were congregated. A simple random sampling methodology was employed to congregate data as of the respondents. Generating the hypothesis along with testing is eventuated. The effect of EI and TM along with regression analysis between TM and EI was analyzed. The outcomes indicated that employee and Organizational Performance (OP) were elevated by effective EI along with TM.
INFLUENCE OF TALENT MANAGEMENT PRACTICES ON ORGANIZATIONAL PERFORMANCE A STUD...IAEME Publication
By implementing talent management strategy, organizations would have the option to retain their skilled professionals while additionally working on their overall performance. It is the course of appropriately utilizing the ideal individuals, setting them up for future top positions, exploring and dealing with their performance, and holding them back from leaving the organization. It is employee performance that determines the success of every organization. The firm quickly obtains an upper hand over its rivals in the event that its employees having particular skills that cannot be duplicated by the competitors. Thus, firms are centred on creating successful talent management practices and processes to deal with the unique human resources. Firms are additionally endeavouring to keep their top/key staff since on the off chance that they leave; the whole store of information leaves the firm's hands. The study's objective was to determine the impact of talent management on organizational performance among the selected IT organizations in Chennai. The study recommends that talent management limitedly affects performance. On the off chance that this talent is appropriately management and implemented properly, organizations might benefit as much as possible from their maintained assets to support development and productivity, both monetarily and non-monetarily.
A STUDY OF VARIOUS TYPES OF LOANS OF SELECTED PUBLIC AND PRIVATE SECTOR BANKS...IAEME Publication
Banking regulations act of India, 1949 defines banking as “acceptance of deposits for the purpose of lending or investment from the public, repayment on demand or otherwise and withdrawable through cheques, drafts order or otherwise”, the major participants of the Indian financial system are commercial banks, the financial institution encompassing term lending institutions. Investments institutions, specialized financial institution and the state level development banks, non banking financial companies (NBFC) and other market intermediaries such has the stock brokers and money lenders are among the oldest of the certain variants of NBFC and the oldest market participants. The asset quality of banks is one of the most important indicators of their financial health. The Indian banking sector has been facing severe problems of increasing Non- Performing Assets (NPAs). The NPAs growth directly and indirectly affects the quality of assets and profitability of banks. It also shows the efficiency of banks credit risk management and the recovery effectiveness. NPA do not generate any income, whereas, the bank is required to make provisions for such as assets that why is a double edge weapon. This paper outlines the concept of quality of bank loans of different types like Housing, Agriculture and MSME loans in state Haryana of selected public and private sector banks. This study is highlighting problems associated with the role of commercial bank in financing Small and Medium Scale Enterprises (SME). The overall objective of the research was to assess the effect of the financing provisions existing for the setting up and operations of MSMEs in the country and to generate recommendations for more robust financing mechanisms for successful operation of the MSMEs, in turn understanding the impact of MSME loans on financial institutions due to NPA. There are many research conducted on the topic of Non- Performing Assets (NPA) Management, concerning particular bank, comparative study of public and private banks etc. In this paper the researcher is considering the aggregate data of selected public sector and private sector banks and attempts to compare the NPA of Housing, Agriculture and MSME loans in state Haryana of public and private sector banks. The tools used in the study are average and Anova test and variance. The findings reveal that NPA is common problem for both public and private sector banks and is associated with all types of loans either that is housing loans, agriculture loans and loans to SMES. NPAs of both public and private sector banks show the increasing trend. In 2010-11 GNPA of public and private sector were at same level it was 2% but after 2010-11 it increased in many fold and at present there is GNPA in some more than 15%. It shows the dark area of Indian banking sector.
EXPERIMENTAL STUDY OF MECHANICAL AND TRIBOLOGICAL RELATION OF NYLON/BaSO4 POL...IAEME Publication
An experiment conducted in this study found that BaSO4 changed Nylon 6's mechanical properties. By changing the weight ratios, BaSO4 was used to make Nylon 6. This Researcher looked into how hard Nylon-6/BaSO4 composites are and how well they wear. Experiments were done based on Taguchi design L9. Nylon-6/BaSO4 composites can be tested for their hardness number using a Rockwell hardness testing apparatus. On Nylon/BaSO4, the wear behavior was measured by a wear monitor, pinon-disc friction by varying reinforcement, sliding speed, and sliding distance, and the microstructure of the crack surfaces was observed by SEM. This study provides significant contributions to ultimate strength by increasing BaSO4 content up to 16% in the composites, and sliding speed contributes 72.45% to the wear rate
ROLE OF SOCIAL ENTREPRENEURSHIP IN RURAL DEVELOPMENT OF INDIA - PROBLEMS AND ...IAEME Publication
The majority of the population in India lives in villages. The village is the back bone of the country. Village or rural industries play an important role in the national economy, particularly in the rural development. Developing the rural economy is one of the key indicators towards a country’s success. Whether it be the need to look after the welfare of the farmers or invest in rural infrastructure, Governments have to ensure that rural development isn’t compromised. The economic development of our country largely depends on the progress of rural areas and the standard of living of rural masses. Village or rural industries play an important role in the national economy, particularly in the rural development. Rural entrepreneurship is based on stimulating local entrepreneurial talent and the subsequent growth of indigenous enterprises. It recognizes opportunity in the rural areas and accelerates a unique blend of resources either inside or outside of agriculture. Rural entrepreneurship brings an economic value to the rural sector by creating new methods of production, new markets, new products and generate employment opportunities thereby ensuring continuous rural development. Social Entrepreneurship has the direct and primary objective of serving the society along with the earning profits. So, social entrepreneurship is different from the economic entrepreneurship as its basic objective is not to earn profits but for providing innovative solutions to meet the society needs which are not taken care by majority of the entrepreneurs as they are in the business for profit making as a sole objective. So, the Social Entrepreneurs have the huge growth potential particularly in the developing countries like India where we have huge societal disparities in terms of the financial positions of the population. Still 22 percent of the Indian population is below the poverty line and also there is disparity among the rural & urban population in terms of families living under BPL. 25.7 percent of the rural population & 13.7 percent of the urban population is under BPL which clearly shows the disparity of the poor people in the rural and urban areas. The need to develop social entrepreneurship in agriculture is dictated by a large number of social problems. Such problems include low living standards, unemployment, and social tension. The reasons that led to the emergence of the practice of social entrepreneurship are the above factors. The research problem lays upon disclosing the importance of role of social entrepreneurship in rural development of India. The paper the tendencies of social entrepreneurship in India, to present successful examples of such business for providing recommendations how to improve situation in rural areas in terms of social entrepreneurship development. Indian government has made some steps towards development of social enterprises, social entrepreneurship, and social in- novation, but a lot remains to be improved.
OPTIMAL RECONFIGURATION OF POWER DISTRIBUTION RADIAL NETWORK USING HYBRID MET...IAEME Publication
Distribution system is a critical link between the electric power distributor and the consumers. Most of the distribution networks commonly used by the electric utility is the radial distribution network. However in this type of network, it has technical issues such as enormous power losses which affect the quality of the supply. Nowadays, the introduction of Distributed Generation (DG) units in the system help improve and support the voltage profile of the network as well as the performance of the system components through power loss mitigation. In this study network reconfiguration was done using two meta-heuristic algorithms Particle Swarm Optimization and Gravitational Search Algorithm (PSO-GSA) to enhance power quality and voltage profile in the system when simultaneously applied with the DG units. Backward/Forward Sweep Method was used in the load flow analysis and simulated using the MATLAB program. Five cases were considered in the Reconfiguration based on the contribution of DG units. The proposed method was tested using IEEE 33 bus system. Based on the results, there was a voltage profile improvement in the system from 0.9038 p.u. to 0.9594 p.u.. The integration of DG in the network also reduced power losses from 210.98 kW to 69.3963 kW. Simulated results are drawn to show the performance of each case.
APPLICATION OF FRUGAL APPROACH FOR PRODUCTIVITY IMPROVEMENT - A CASE STUDY OF...IAEME Publication
Manufacturing industries have witnessed an outburst in productivity. For productivity improvement manufacturing industries are taking various initiatives by using lean tools and techniques. However, in different manufacturing industries, frugal approach is applied in product design and services as a tool for improvement. Frugal approach contributed to prove less is more and seems indirectly contributing to improve productivity. Hence, there is need to understand status of frugal approach application in manufacturing industries. All manufacturing industries are trying hard and putting continuous efforts for competitive existence. For productivity improvements, manufacturing industries are coming up with different effective and efficient solutions in manufacturing processes and operations. To overcome current challenges, manufacturing industries have started using frugal approach in product design and services. For this study, methodology adopted with both primary and secondary sources of data. For primary source interview and observation technique is used and for secondary source review has done based on available literatures in website, printed magazines, manual etc. An attempt has made for understanding application of frugal approach with the study of manufacturing industry project. Manufacturing industry selected for this project study is Mahindra and Mahindra Ltd. This paper will help researcher to find the connections between the two concepts productivity improvement and frugal approach. This paper will help to understand significance of frugal approach for productivity improvement in manufacturing industry. This will also help to understand current scenario of frugal approach in manufacturing industry. In manufacturing industries various process are involved to deliver the final product. In the process of converting input in to output through manufacturing process productivity plays very critical role. Hence this study will help to evolve status of frugal approach in productivity improvement programme. The notion of frugal can be viewed as an approach towards productivity improvement in manufacturing industries.
A MULTIPLE – CHANNEL QUEUING MODELS ON FUZZY ENVIRONMENTIAEME Publication
In this paper, we investigated a queuing model of fuzzy environment-based a multiple channel queuing model (M/M/C) ( /FCFS) and study its performance under realistic conditions. It applies a nonagonal fuzzy number to analyse the relevant performance of a multiple channel queuing model (M/M/C) ( /FCFS). Based on the sub interval average ranking method for nonagonal fuzzy number, we convert fuzzy number to crisp one. Numerical results reveal that the efficiency of this method. Intuitively, the fuzzy environment adapts well to a multiple channel queuing models (M/M/C) ( /FCFS) are very well.
Using recycled concrete aggregates (RCA) for pavements is crucial to achieving sustainability. Implementing RCA for new pavement can minimize carbon footprint, conserve natural resources, reduce harmful emissions, and lower life cycle costs. Compared to natural aggregate (NA), RCA pavement has fewer comprehensive studies and sustainability assessments.
KuberTENes Birthday Bash Guadalajara - K8sGPT first impressionsVictor Morales
K8sGPT is a tool that analyzes and diagnoses Kubernetes clusters. This presentation was used to share the requirements and dependencies to deploy K8sGPT in a local environment.
TIME DIVISION MULTIPLEXING TECHNIQUE FOR COMMUNICATION SYSTEMHODECEDSIET
Time Division Multiplexing (TDM) is a method of transmitting multiple signals over a single communication channel by dividing the signal into many segments, each having a very short duration of time. These time slots are then allocated to different data streams, allowing multiple signals to share the same transmission medium efficiently. TDM is widely used in telecommunications and data communication systems.
### How TDM Works
1. **Time Slots Allocation**: The core principle of TDM is to assign distinct time slots to each signal. During each time slot, the respective signal is transmitted, and then the process repeats cyclically. For example, if there are four signals to be transmitted, the TDM cycle will divide time into four slots, each assigned to one signal.
2. **Synchronization**: Synchronization is crucial in TDM systems to ensure that the signals are correctly aligned with their respective time slots. Both the transmitter and receiver must be synchronized to avoid any overlap or loss of data. This synchronization is typically maintained by a clock signal that ensures time slots are accurately aligned.
3. **Frame Structure**: TDM data is organized into frames, where each frame consists of a set of time slots. Each frame is repeated at regular intervals, ensuring continuous transmission of data streams. The frame structure helps in managing the data streams and maintaining the synchronization between the transmitter and receiver.
4. **Multiplexer and Demultiplexer**: At the transmitting end, a multiplexer combines multiple input signals into a single composite signal by assigning each signal to a specific time slot. At the receiving end, a demultiplexer separates the composite signal back into individual signals based on their respective time slots.
### Types of TDM
1. **Synchronous TDM**: In synchronous TDM, time slots are pre-assigned to each signal, regardless of whether the signal has data to transmit or not. This can lead to inefficiencies if some time slots remain empty due to the absence of data.
2. **Asynchronous TDM (or Statistical TDM)**: Asynchronous TDM addresses the inefficiencies of synchronous TDM by allocating time slots dynamically based on the presence of data. Time slots are assigned only when there is data to transmit, which optimizes the use of the communication channel.
### Applications of TDM
- **Telecommunications**: TDM is extensively used in telecommunication systems, such as in T1 and E1 lines, where multiple telephone calls are transmitted over a single line by assigning each call to a specific time slot.
- **Digital Audio and Video Broadcasting**: TDM is used in broadcasting systems to transmit multiple audio or video streams over a single channel, ensuring efficient use of bandwidth.
- **Computer Networks**: TDM is used in network protocols and systems to manage the transmission of data from multiple sources over a single network medium.
### Advantages of TDM
- **Efficient Use of Bandwidth**: TDM all
Using recycled concrete aggregates (RCA) for pavements is crucial to achieving sustainability. Implementing RCA for new pavement can minimize carbon footprint, conserve natural resources, reduce harmful emissions, and lower life cycle costs. Compared to natural aggregate (NA), RCA pavement has fewer comprehensive studies and sustainability assessments.
Literature Review Basics and Understanding Reference Management.pptxDr Ramhari Poudyal
Three-day training on academic research focuses on analytical tools at United Technical College, supported by the University Grant Commission, Nepal. 24-26 May 2024
Batteries -Introduction – Types of Batteries – discharging and charging of battery - characteristics of battery –battery rating- various tests on battery- – Primary battery: silver button cell- Secondary battery :Ni-Cd battery-modern battery: lithium ion battery-maintenance of batteries-choices of batteries for electric vehicle applications.
Fuel Cells: Introduction- importance and classification of fuel cells - description, principle, components, applications of fuel cells: H2-O2 fuel cell, alkaline fuel cell, molten carbonate fuel cell and direct methanol fuel cells.
Redefining brain tumor segmentation: a cutting-edge convolutional neural netw...IJECEIAES
Medical image analysis has witnessed significant advancements with deep learning techniques. In the domain of brain tumor segmentation, the ability to
precisely delineate tumor boundaries from magnetic resonance imaging (MRI)
scans holds profound implications for diagnosis. This study presents an ensemble convolutional neural network (CNN) with transfer learning, integrating
the state-of-the-art Deeplabv3+ architecture with the ResNet18 backbone. The
model is rigorously trained and evaluated, exhibiting remarkable performance
metrics, including an impressive global accuracy of 99.286%, a high-class accuracy of 82.191%, a mean intersection over union (IoU) of 79.900%, a weighted
IoU of 98.620%, and a Boundary F1 (BF) score of 83.303%. Notably, a detailed comparative analysis with existing methods showcases the superiority of
our proposed model. These findings underscore the model’s competence in precise brain tumor localization, underscoring its potential to revolutionize medical
image analysis and enhance healthcare outcomes. This research paves the way
for future exploration and optimization of advanced CNN models in medical
imaging, emphasizing addressing false positives and resource efficiency.
Advanced control scheme of doubly fed induction generator for wind turbine us...IJECEIAES
This paper describes a speed control device for generating electrical energy on an electricity network based on the doubly fed induction generator (DFIG) used for wind power conversion systems. At first, a double-fed induction generator model was constructed. A control law is formulated to govern the flow of energy between the stator of a DFIG and the energy network using three types of controllers: proportional integral (PI), sliding mode controller (SMC) and second order sliding mode controller (SOSMC). Their different results in terms of power reference tracking, reaction to unexpected speed fluctuations, sensitivity to perturbations, and resilience against machine parameter alterations are compared. MATLAB/Simulink was used to conduct the simulations for the preceding study. Multiple simulations have shown very satisfying results, and the investigations demonstrate the efficacy and power-enhancing capabilities of the suggested control system.
Electric vehicle and photovoltaic advanced roles in enhancing the financial p...IJECEIAES
Climate change's impact on the planet forced the United Nations and governments to promote green energies and electric transportation. The deployments of photovoltaic (PV) and electric vehicle (EV) systems gained stronger momentum due to their numerous advantages over fossil fuel types. The advantages go beyond sustainability to reach financial support and stability. The work in this paper introduces the hybrid system between PV and EV to support industrial and commercial plants. This paper covers the theoretical framework of the proposed hybrid system including the required equation to complete the cost analysis when PV and EV are present. In addition, the proposed design diagram which sets the priorities and requirements of the system is presented. The proposed approach allows setup to advance their power stability, especially during power outages. The presented information supports researchers and plant owners to complete the necessary analysis while promoting the deployment of clean energy. The result of a case study that represents a dairy milk farmer supports the theoretical works and highlights its advanced benefits to existing plants. The short return on investment of the proposed approach supports the paper's novelty approach for the sustainable electrical system. In addition, the proposed system allows for an isolated power setup without the need for a transmission line which enhances the safety of the electrical network
Understanding Inductive Bias in Machine LearningSUTEJAS
This presentation explores the concept of inductive bias in machine learning. It explains how algorithms come with built-in assumptions and preferences that guide the learning process. You'll learn about the different types of inductive bias and how they can impact the performance and generalizability of machine learning models.
The presentation also covers the positive and negative aspects of inductive bias, along with strategies for mitigating potential drawbacks. We'll explore examples of how bias manifests in algorithms like neural networks and decision trees.
By understanding inductive bias, you can gain valuable insights into how machine learning models work and make informed decisions when building and deploying them.
A SYSTEMATIC RISK ASSESSMENT APPROACH FOR SECURING THE SMART IRRIGATION SYSTEMSIJNSA Journal
The smart irrigation system represents an innovative approach to optimize water usage in agricultural and landscaping practices. The integration of cutting-edge technologies, including sensors, actuators, and data analysis, empowers this system to provide accurate monitoring and control of irrigation processes by leveraging real-time environmental conditions. The main objective of a smart irrigation system is to optimize water efficiency, minimize expenses, and foster the adoption of sustainable water management methods. This paper conducts a systematic risk assessment by exploring the key components/assets and their functionalities in the smart irrigation system. The crucial role of sensors in gathering data on soil moisture, weather patterns, and plant well-being is emphasized in this system. These sensors enable intelligent decision-making in irrigation scheduling and water distribution, leading to enhanced water efficiency and sustainable water management practices. Actuators enable automated control of irrigation devices, ensuring precise and targeted water delivery to plants. Additionally, the paper addresses the potential threat and vulnerabilities associated with smart irrigation systems. It discusses limitations of the system, such as power constraints and computational capabilities, and calculates the potential security risks. The paper suggests possible risk treatment methods for effective secure system operation. In conclusion, the paper emphasizes the significant benefits of implementing smart irrigation systems, including improved water conservation, increased crop yield, and reduced environmental impact. Additionally, based on the security analysis conducted, the paper recommends the implementation of countermeasures and security approaches to address vulnerabilities and ensure the integrity and reliability of the system. By incorporating these measures, smart irrigation technology can revolutionize water management practices in agriculture, promoting sustainability, resource efficiency, and safeguarding against potential security threats.
CHINA’S GEO-ECONOMIC OUTREACH IN CENTRAL ASIAN COUNTRIES AND FUTURE PROSPECTjpsjournal1
The rivalry between prominent international actors for dominance over Central Asia's hydrocarbon
reserves and the ancient silk trade route, along with China's diplomatic endeavours in the area, has been
referred to as the "New Great Game." This research centres on the power struggle, considering
geopolitical, geostrategic, and geoeconomic variables. Topics including trade, political hegemony, oil
politics, and conventional and nontraditional security are all explored and explained by the researcher.
Using Mackinder's Heartland, Spykman Rimland, and Hegemonic Stability theories, examines China's role
in Central Asia. This study adheres to the empirical epistemological method and has taken care of
objectivity. This study analyze primary and secondary research documents critically to elaborate role of
china’s geo economic outreach in central Asian countries and its future prospect. China is thriving in trade,
pipeline politics, and winning states, according to this study, thanks to important instruments like the
Shanghai Cooperation Organisation and the Belt and Road Economic Initiative. According to this study,
China is seeing significant success in commerce, pipeline politics, and gaining influence on other
governments. This success may be attributed to the effective utilisation of key tools such as the Shanghai
Cooperation Organisation and the Belt and Road Economic Initiative.
Introduction- e - waste – definition - sources of e-waste– hazardous substances in e-waste - effects of e-waste on environment and human health- need for e-waste management– e-waste handling rules - waste minimization techniques for managing e-waste – recycling of e-waste - disposal treatment methods of e- waste – mechanism of extraction of precious metal from leaching solution-global Scenario of E-waste – E-waste in India- case studies.
2. Detection of Damage in Stiffeners of Aircraft Wing Structure Based On Induced Skin Strains and
Lateral Deflections
http://www.iaeme.com/IJMET/index.asp 111 editor@iaeme.com
in the structure due to variation in the strains and lateral deflections between different
damage locations.
Key Words: Wing structure, Structural health monitoring, finite element method,
structural analysis, airfoil pressure distributions, strain, stress, deflection, damage in
wing structure.
Cite this Article: Dr. Hatem Hadi Obeid, Detection of Damage in Stiffeners of
Aircraft Wing Structure Based On Induced Skin Strains and Lateral Deflections,
International Journal of Mechanical Engineering and Technology, 10(3), 2019, pp.
110-126.
http://www.iaeme.com/IJMET/issues.asp?JType=IJMET&VType=10&IType=3
1. INTRODUCTION
The Structural Health Monitoring of failures in aircraft and other flying equipment is very
important because its concerned with the safety of their users or the risks that may be
occurred due to falling on the ground. This analysis is applicable in wide range of engineering
fields spanning from mechanical, aerospace, military, building, to bridge and transportation
applications. Needs for prediction of failure in the aerospace structures are rapidly increasing
due to demands of enhance safety, reduce inspection time and cost but maintaining structural
function and uses. This field is also providing smart prognosis and diagnosis of failure
instantaneously. The deployment and development of structural health monitoring system is
required to ensuring the safe operation of any engineering structure or system. The execution
of the structural health monitoring is mainly considering the following processes: [1]
- Using sensors and instrumentation devices for sensing and tracing the interpretation of
an engineering system or structure under operational loads.
- Assessment the performance of the system or structure for any propagation of damages
or defects by the analysis of the measured values analytically or numerically.
- Indicating a notification or an alarm when the desired system parameters are exceeded.
The base on parameters or criteria that the structural health monitoring system executed
are varied depending on the nature of the system responses or performance. Although the
importance of structural health monitoring but their researches are relatively young if
compared to other engineering fields, thus most of the researches have been conducted at
universities or research and development centers of companies.
The applications of structural health monitoring in engineering fields included different
problems such detection of damage in steel structure, aerospace, concrete structures, precast
concrete, box girders in railroads, composite materials, dikes and pipelines of water and
wastewater. Also, evaluation bridge deflection; stress or strain analysis in petroleum pipes,
dam structures, or suspension bridge cables. In addition to more complicated problems such
as detection of impact effects in wind turbine blades and water leaks. The vibration of high-
rise reinforced structures such as towers can be evaluated and assessment.
In this paper the structural health monitoring is applied for detection failure at the
stiffeners of aircraft wing structure. The performance of an aircraft structure can be
characterized by various factors, essentially the response (i.e. strain mapping, shape
determination etc.) due to applied loading that can be evaluated by health monitoring
technique [2]. Finite element method is powerful to be used to modelling the wing structure
for estimation the effects in the structures due to the applied loading. The most wing structural
stiffness comes from the interior stiffeners. The stiffeners included main, auxiliary spars and
ribs. Having stiffeners (spars and ribs) attaing structure increases the load resistance of the
3. Dr. Hatem Hadi Obeid
http://www.iaeme.com/IJMET/index.asp 112 editor@iaeme.com
structure without further increasing in the weight. To further reduce the weight, a certain
arrangement of stiffener on structure is being necessary to increase the rigidity with less
material. The construction of both stiffeners and outer skin gives the overall wing structural
stiffness. The response of wing structure into the loading depending mainly on the overall
stiffness of wing. Then the present of damage in any location in the stiffeners will be affecting
on the response of the wing to the applied loading.
2. FINITE ELEMENT MODELLING
2.1. Geometric Parameters:
In this work, a wing structure of a guided aircraft laboratory prototype was modelled via finite
element method. Different finite element models were created each represent a case of
damage in spar. The purpose of these finite element models is performing static analysis
under action of static load and obtain strains induced in the skins and the lateral deformation
at the tip of wing. Then the health monitoring technique is applied to estimate relations
between damage of stiffeners and the static induced strains and deformations. The geometry
configurations and dimensions are illustrated in figure (1), such that the wing consisting of
upper and lower skins, spars and ribs. The wing stiffeners are constructed as eight spars and
ten ribs connected for giving the wing structure the required stiffness. The four digits
symmetrical NACA 0015 airfoil was used as an aerodynamic shape for the considered wing.
The (00) number of the NACA indicating that it has no camber. The (15) number of the
NACA indicates that the airfoil has a “thickness to chord length ratio” of 15% as shown in
figure (2). The equation describing the geometric shape of a NACA 0015 foil is [4,5]:
(1)
x: is the location along chord from ranged (0 to 100%).
y(x) is the half thickness at any location x .
t: is maximum thickness of the wing as a fraction of the chord.
The chords of the wing structure were assigned as 1m and 0.4m at the root and tip
respectively with length 1.75m.
4. Detection of Damage in Stiffeners of Aircraft Wing Structure Based On Induced Skin Strains and
Lateral Deflections
http://www.iaeme.com/IJMET/index.asp 113 editor@iaeme.com
2.2. Mesh Generation of wing structure:
In order to study the effect of damage that occurred in the spars, finite elements models were
created for each damage case. The damage was assumed to be as a cut in the connection of the
main spar which is located at the maximum thickness of wing, such that it assumed that the
damage occurred at five locations in the spar nearest to the maximum wing thickness. High
order SHELL 8-node quadrilateral element and 6-nodes triangular element ware selected for
the generation finite element model of the wing structures. Figure (3) is shown the high order
SHELL 8-Node element parameters and degrees of freedom. The upper and lower skins were
discretized into ten divisions, to be generate one hundred shell elements at each skin. The
spars and ribs were discretized into ten divisions in order to connected with both and skins
element at the contracted nodes to maintain continuous element connections as shown in
figure (4). The thickness of all of skins, spars and ribs were assigned to 0.4 mm. Aluminum
2024 alloy -T3 was used as the material of all parts their mechanical properties are shown in
table (1). [7]
3. DEFINITION OF THE ELEMENT COORDINATE SYSTEMS [8,9,10]
For the typical shell elements as shown in Figure (3), the external faces (surfaces) of the
element are curved, while the thickness is generated by straight lines. Many coordinate sets
employed in the formulation of degenerated shell element. These coordinate systems are
described in the following sections.
3.1. Global Coordinate System - (Xi)
It is the global Cartesian coordinate system, used to describe the wing geometry in the space.
The coordinates and deflections of nodes can be described using this coordinates system. In
addition to describe the assembled global stiffness matrix and assembled force vector. The
following notation is used:
iX
(I=1,3) and X1 =X , X2=Y , X3=Z , iU
(I=1,3) and U1=U, U2 =V, U3=W
5. Dr. Hatem Hadi Obeid
http://www.iaeme.com/IJMET/index.asp 114 editor@iaeme.com
iX (i=1,3) is a unit vector in the iX direction.
This system is used to define global stiffness matrix and applied force vector and in the
structure geometry, as well as nodal coordinate and displacements are referred to this system.
3.2. Nodal Coordinate System (V1f , V2f , V3f )
This system type can be established at each nodal point as shown in Figure (3) with origin
located at reference surface (shell mid-surface), V3f is a vector formulated from nodal
coordinate of shell surfaces at node f,
bot
f
top
ff3 XXV
,
T
botfff
T
topffff3 ZYXZYXV
2
The unit vector f3V can normalize from the vectorV3f, thus:
Tz
f3
y
f3
x
f3
f
f3
f3 VVV
h
V
V
3
2/12
f3
2
f2
2
f1f ΔXΔXΔXh 4
1,2,3iXXΔX bot
if
top
ifif 5
The vector 3fV is the direction of “normal” at the node f, which is not necessarily
perpendicular to the mid-surface at f.
The vector V2f is normal to plane of vectors V1f and V3f: V2f = V1f V3f .
The mathematical characteristic of vector V1f is perpendicular to V3f and parallel to the
global X – Z plane, thus:
x
3f
z
1f
y
1f
z
3f
x
1f V-V,0.0V,VV
Or, if the vector is in the Y-direction
0.0VV z
3f
x
3f
x
3f
z
1f
y
1f
z
3f
x
1f V-V,0.0V,VV
3.3. Curvilinear Coordinate System ( )
The description of this system is established by the definition of three coordinates, each one
has its characteristic as shown in Figure (3). The coordinate is an intrinsic coordinate
through thickness direction. coordinate is defined as a function of 3fV , the -direction is
considered normal to the shell mid-surface. It is assumed that the curvilinear coordinate varies
between (-1 and +1), which represent the top and bottom surfaces of the element respectively.
The two other coordinates are ηξ, which are curvilinear coordinate in the middle plane of the
shell element and are also assumed to vary between (-1 and +1) which represent the faces of
the element.
3.4. Local Coordinate System (
''''
i Z,Y,XorX )
This system is a cartesian coordinate system defined at the sampling points wherein stresses
and strains are to be calculated. The direction
'
Z is taken perpendicular to the mid-surface (
constant ),
''
YandX tangent it as shown in Figure (3). The vectors
'
1V ,
'
2V ,
'
3V
define
'''
ZandY,X direction of mid-surface respectively, and it should be noted that,
6. Detection of Damage in Stiffeners of Aircraft Wing Structure Based On Induced Skin Strains and
Lateral Deflections
http://www.iaeme.com/IJMET/index.asp 115 editor@iaeme.com
ξ
z
ξ
y
ξ
x
ξ
,
η
z
η
y
η
x
η
,
ξ
z
ξ
y
ξ
x
ξV1
,
ξ
z
ξ
y
ξ
x
ηξV3
x
η
Z
η
Y
η
X
6
[T] = '
1V ,
'
2V ,
'
3V 7
'
1V ,
'
2V ,
'
3V
: unit vectors on
'''
ZandY,X .
3.5. Geometry of Elements [10]
To obtain the formulation of the coordinates of any point within the element, it is simpler to
divide the general formulation of coordinate in two parts. The first part is to establish the term
of formulation, which represents the intercept of the “normal” with the mid-surface. If there is
a node (f) at the “normal” at =0 surface and this “normal” has a top and bottom nodes at
=+1 and =-1 surfaces respectively, the coordinates of node (f) can be obtained as follows:
2
1
bot
'
ftop
'
f
'
f
XXX
, bot
f
f
f
top
f
f
f
f
f
f
Z
Y
X
Z
Y
X
2
1
Z
Y
X
8
Since node (f) is in the mid-surface (at =0 surface), the two dimensional interpolation
function ,N f
can be applied from Table (2) , to obtain relationship between the Cartesian
point and the curvilinear coordinate as follows:
if
n
1f
fi X,NX
9
The second part is to establish the second term of the general formulation, which defines
the position of the point along this “normal”. But to establish that, it is necessary to define
arbitrary point (p) on the “normal” at node (f), therefore the vector V3f which represents the
thickness of the shell hf, can be written ass:
botf
f
f
topf
f
f
f3f
Z
Y
X
Z
Y
X
Vh
10
The distance between the arbitrary point (p) and the node f (at mid-surface) can be written as follows:
Unit Distance = 2
ζh f
11
7. Dr. Hatem Hadi Obeid
http://www.iaeme.com/IJMET/index.asp 116 editor@iaeme.com
Since the
i
f3f Vh
means the coordinates of the arbitrary point, the equation (11) can be rewritten with
the application of the two-dimensional interpolation function ηξ,Nf from Table () so that:
i
f3
n
1f
fi
V
2
ζ
ηξ,NX
12
The general formulation of the coordinate defines the geometry of the shell element which
represents the rotations between the coordinate ( ζηξ ) and coordinates (X, Y, Z). It is
obtained by the summation of the previous two parts (equation (8) & equation (12)) so that:
botif
n
1f
ftopif
n
1f
fi X
2
ζ1
),(NX
2
ζ1
),(NX
13
z
f3
y
f3
x
f3
f
n
1f
f
mid
n
1f
f
V
V
V
2
hζ
),(N
Z
Y
X
),(N
Z
Y
X
iX
is the elemental Cartesian coordinate, ( XX1 , YX2 , ZX3
), n: is the number of
nodes per element, hf is the element thickness at node f, i.e. the respective “normal” length,
Xif is the Cartesian coordinate of nodal point f, and ),(N f
is the two dimensional
interpolation functions. (ζ =constant) at nodal point f.
3.6. Displacement Field [10]
Each node of the high order element has five degrees of freedom representing the
displacement along local coordinates. It is assumed that the strains in the directions to the
mid-surface is assumed to be negligible. The deflections through the element mid surface can
be defined by the three displacements (u,v,w), and two rotations of the nodal vector V3f about
orthogonal directions normal to it. One of the two orthogonal directions is represented by unit
vector f1V and the corresponding rotation ( f1α ). The other directions is f2V and the
corresponding rotation is ( f2α ), and it is the displacements ( f2f1 δ,δ ) of a point at unit distance
(h) from node f on the “normal” resulted from the two rotations ( f1α , f2 ) are calculated as
follows:
h
δ
α f1
f1
or f1f1 αhδ 14
h
δ
α f2
f2
or f2f2 αhδ
where 2
h
h f
, f1δ is the displacement in the direction of f1V , f2δ is the displacement
in the negative direction of f2V . Equation (13) can be written as follows:
f2
f1
f2
f1
α
α
h
δ
δ
15
The global displacement can be found from:
i
'
οff
n
1f
mid
i
οffi
uNuNu
16
8. Detection of Damage in Stiffeners of Aircraft Wing Structure Based On Induced Skin Strains and
Lateral Deflections
http://www.iaeme.com/IJMET/index.asp 117 editor@iaeme.com
iu : the nodal displacement through element thickness.
i
fu : nodal displacement through
Cartesian coordinate.
i
'
fu :nodal displacement through “normal” of the cross product of
rotations f1 and f2 .
Since;
'
f2
'
f1
i
οf δδu 17
where the corresponding displacement components (
'
f1 ,
'
f2 ) of
'
fu can be calculated as
follows:
i
f1f1
f'
f1 V
2
h
and
i
f1f1
f'
f1 V
2
h
18
Since the global displacement can be found as shown before in equation (16) as the
simulation of the mid-surface nodal displacement (
i
fu ) and the relative displacements are
caused by the rotations of the normal (
i'
fu ), then the element displacement field can be
expressed by:
)αVαV(
2
h.ζ
uu f2
i
f2f1
i
f1
fi
οfif
19
f2
f1
z
f2
z
f1
y
f2
y
f1
x
f2
x
f1
f
n
1f
f
f
f
fn
1f
f
α
α
VV
VV
VV
2
hζ
ηξ,N
w
v
u
ηξ,N
w
v
u
20
The contribution to the global displacement from a given node f in the general form and
for complete element is:
f
Sζη,ξ,Nu
n
1f
fi
21
f2
f1
f
f
f
z
f2
f
f
z
f1
f
ff
y
f2
f
f
y
f1
f
ff
x
f2
f
f
x
f1
f
ff
α
α
w
v
u
V
2
hζ
NV
2
hζ
NN00
V
2
hζ
NV
2
hζ
N0N0
V
2
hζ
NV
2
hζ
N00N
w
v
u
22
Nf is the shape function matrix of the degenerated shell element.
Sf is transformation matrix of the displacement vector at node f of shell element
T
f2f1fff ,,w,v,u .
3.7. State of Stress [10]
The stress and strain components for the shell assumption of zero local stress through shell
mid-surface along
'
Z -direction ( 0'
z ) and using Hooks law enables the stresses vector to
be reduced to following five stress components,
ο
zy
zx
yx
y
x
εεD
η
η
η
ζ
ζ
ζ
''
''
''
'
'
23
is the initial strain vector.
9. Dr. Hatem Hadi Obeid
http://www.iaeme.com/IJMET/index.asp 118 editor@iaeme.com
is the strain vector.
[D] is the elasticity matrix given by,
GK0000
0GK000
00G00
0001ν
000ν1
ν1
E
D
2
1
2
24
G: modulus rigidity, E: modulus of elasticity, : Poisson’s ratio,
K1, K2 is the shear correction factors.
3.8. State of Strains [10]
The normal strain in the '
Z -direction (
'
z ) is neglected. Therefore, the general vector of green
strains it will be reduced to the following five components,
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
zy
zx
yx
y
x
y
w
z
v
x
w
z
u
x
v
y
u
y
v
x
u
ε
ε
ε
''
''
''
'
'
25
The local derivatives above of the displacement components
'''
wandv,u in the local
coordinates system (
'
1X ) can be obtained as:
z
w
z
v
z
u
y
w
y
v
y
u
x
w
x
v
x
u
z
w
z
v
z
u
y
w
y
v
y
u
x
w
x
v
x
u
T
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
'
26
[] is the transformation matrix given by,
'''
'''
'''
z
z
y
z
x
z
z
y
y
y
x
y
z
x
y
x
x
x
][
27
ζ
w
ζ
v
ζ
u
η
w
η
v
η
u
ξ
w
ξ
v
ξ
u
J
z
w
z
v
z
u
y
w
y
v
y
u
x
w
x
v
x
u
1
28
ζ
z
ζ
y
ζ
x
η
z
η
y
η
x
ξ
z
ξ
y
ξ
x
[J]
[J] is Jacobian matrix 29
10. Detection of Damage in Stiffeners of Aircraft Wing Structure Based On Induced Skin Strains and
Lateral Deflections
http://www.iaeme.com/IJMET/index.asp 119 editor@iaeme.com
The transpose of the Jacobian matrix results from equation (12) can be expressed as
follow:
n
1f
f,,f
z
f3
y
f3
x
f3
f
f
z
f3
y
f3
x
f3
f
f,,f
f
f
f
T
0NN
V
V
V
2
h
N00
V
V
V
2
h
0NN
Z
Y
X
]J[
30
n is the number of node per element,
hf is the element thickness at node f, and
,N
N;
,N
N f
,f
f
,f
31
are the derivatives of the global displacements referred to the curvilinear coordinates are
obtained from equation (18), such as
u
. . .etc.
n
1f
2f,f
x
f2
f
1f,f
x
f1
f
f,f NV
2
h
NV
2
h
uN
u
32
The strain matrix B can be formulated from equations (21), (29) and (31) as:
B 33
where,
T
21
α,α,w,v,uδ 34
[B]=
)VgVd(-)VgV(da0c
)VeVg(-)VeV(gbc0
)VdVe(-)VdV(e0ab
Ve-Ve0b0
Vd-Vd00a
x2iz2ix1iz1iii
z2iy1iz1iy1iii
y1ix2iy1ix1iii
x2iy1ii
x2ix1i
i
iiii
iiii
iiii
ii
ii
35
η,NJζ,NJa i
*
12i
*
11i η,NJζ,NJb i
*
22i
*
21i η,NJζ,NJc i
*
32i
*
31i
)NJz(a
2
hd i
*
31
,
i
i
i )NJz(b
2
he i
*
23
,
i
i
i )NJz(c
2
h i
*
23
,
i
i
i g
Consequently, it is used in the calculation of the stiffness matrix [K] using the mid-
coordinate rule. Hence [K] can be defined as follows:
ηdξdζζη,ξ,J[D][B][B][K]
1
1
1
1
1
1
T
d
36
Then K can be written as summing up the contribution of each layer at the gauss points,
dηdξ
h
Δh2
ζη,ξ,J]][B[D][B[K]
1
1
1
1
nL
1j
j
jj
T
j
37
[K] : stiffness matrix, [D] : elasticity matrix, [Bj]: strain-displacement matrix.
),,(J
is the determinant of the Jacobian matrix for layer ( j ).
jh
is the thickness of the jth layer.
nL is the total number of layers.
In the same way, the internal force vector {
e
f } can be determined as follows:
dVJ}{]B[}f{
v
Te
38
11. Dr. Hatem Hadi Obeid
http://www.iaeme.com/IJMET/index.asp 120 editor@iaeme.com
dηdξ
h
Δh2
ζ)η,J(ξ(}{ζ][B}{f
nL
1j
1
1
1
1
j
j
T
j
e
39
}{ j
: is current stress vector,
}f{ e
: is the internal force vector.
It should be noted that, it is essential in nonlinear analysis to determine the internal force
vector (or equivalent nodal forces) at the end of each iteration. The transformation to the local
coordinates system ( ''
YX ) using the following relation:
][S][D[S]][D s
T'
s 40
lm
ml
mllmlm
lmlm
lmml
000
000
0022
00
00
[S] 22
22
22
41
3.7. Boundary conditions
The wing is clamped through the root chord such that all the degrees of freedom of the
regarded nodes are fixed to be zeros. While all other nodes are freely to be of three
translations and three rotations along the corresponding local coordinates.
3.8. EXPERIMENTAL PREDICTION OF PRESSURE DISTRIBUTION:
In order to predict the load that applied on the wing structure, a prototype for the airfoil was
manufactured using wood material according to the digital naca number 0015. Then the
prototype was amounted in the wind tunnel section as shown in figure (5). Its required to
measure the pressure distribution through the airfoil, thus twelve manometers were used for
this purpose. The wind tunnel is flowing air at 50 m/s over the airfoil. The airfoil was
mounted with different attack angles (0 to 10 degrees). Figures (6),(7) showed the pressure
distributions through upper and lower skins with different attack angles. The net pressure
distribution is equal to the difference between the pressures through upper and lower skins.
The pressure distribution was measured for each attack angle which is represent the effect of
aerodynamic lifting of the wing.
12. Detection of Damage in Stiffeners of Aircraft Wing Structure Based On Induced Skin Strains and
Lateral Deflections
http://www.iaeme.com/IJMET/index.asp 121 editor@iaeme.com
3.9. STATIC ANALYSIS [10]
Static analysis solution has been included the calculation of the effects of the applied load
under steady loading conditions on a structure. The pressure distributions through upper and
lower skins were applied as normal pressures on the elements. The static analysis is governing
by the following equilibrium equation:
FqK 42
The above equilibrium equation is solved by jacobi iterative method to obtain the
displacement [q] vector.
4. RESULTS AND DISCUSION
Naman Jain [11,12] was created a Finite element code to solve shell structure under action of
static loads. In this work, a development was achieved for using Naman Jain code to generate
stiffened shell structure using quadrilateral eight nodes shell element and triangular six nodes
shell element. Jacobi iterative method was used to solve equation (42) to obtain the
deformations along global coordinates. Then the deformations transformed using equation
(41) to the local coordinates. The local deformations were transformed into global coordinates
x,y and z directions. The strains were estimated through local coordinates and substituted in
the stress strain relations to obtain elemental stresses through local coordinates. The first run
included the healthy structure that did not subjected into damage. Figure (8) showed the safe
strains induced in the lower skin along the intersection of the skins and main spar. Its noted
that the strains in the healthy wing were decreased gradually in the rejoins moved away than
the wing chord. The same behavior was noted in the strains induced in the upper and lower
skins. Figure (9) showed the safe lateral deformations induced in the lower skin along the
intersection of the skins and main spar. The lateral deformations of both the lower and upper
skins at the intersection of skins with main spar were approximately coincident. Also, the
lateral deformations were increased gradually in the rejoins moved away than the wing chord.
A similar behavior was noted in the study of Salu Kumar Das and Sandipan Roy [13]. The
second run included the static solution of the finite element model subjected to damage at the
main spar at the location apart 20% than the chord. The damage simulated as a cut in the
element connection of the spar and skins. The strain distributions are illustrated in figure
(10), where noted that a climax is initiated in the distribution at the location of the damage. In
addition to variation in the shape of the distribution of the strains in the rejoin between the
damage and the end tip of the wing. Figure (11) showed the distribution of the lateral
13. Dr. Hatem Hadi Obeid
http://www.iaeme.com/IJMET/index.asp 122 editor@iaeme.com
deformations of the lower skin at the intersection of the main spar with skins. The distribution
indicated that there are two shapes, the first shape in the rejoin between the chord and the
damage where the distribution was gradually increased. The second shape is between the
damage and the end tip of the wing, where the distribution appeared to be semi gradually
comparative with the first region. This is behavior due to the present of damage at the location
20% than the chord. In which the stiffness if reduced rapidly at that location. So, this behavior
can be used as a key to detect the damage location. The other runs were executed for the finite
element models that included the damages at the locations apart than the chord by 40%, 60%
and 80%. The behavior of the strain distribution indicates a decreasing towards the end tip of
the wing such that initiated a sudden climax at the location of the damage as shown in figures
(12, 14, and 16). The behavior of the lateral deformations indicated variations the shape of the
curve, such that the curve appeared to be gradually increased the region between the chord
and the damage. Semi to rapid increasing in the lateral deformation occurred in region
between the damage and the end tip of wing as shown in figures (13, 15, and 17).
14. Detection of Damage in Stiffeners of Aircraft Wing Structure Based On Induced Skin Strains and
Lateral Deflections
http://www.iaeme.com/IJMET/index.asp 123 editor@iaeme.com
15. Dr. Hatem Hadi Obeid
http://www.iaeme.com/IJMET/index.asp 124 editor@iaeme.com
16. Detection of Damage in Stiffeners of Aircraft Wing Structure Based On Induced Skin Strains and
Lateral Deflections
http://www.iaeme.com/IJMET/index.asp 125 editor@iaeme.com
CONFLICT OF INTERESTS
Declare that there is no “conflict of interests” regarding the publication of this paper.
ACKNOWLEDGMENTS
My thankful for the assistance from the staff of post graduate laboratory at Department of
Mechanical Engineering ,College of Engineering, Babylon University ,Iraq.
DATA AVAILABILITY
All data concerned with the fixation and performing the test of pressure distributions
through wing in wind tunnel are available in the author and can be obtained via mailing.
The codes of the finite element analysis can be obtained after publication of the research
and can be contacting with author for this purpose.
REFERENCES
[1] Structural Health Monitoring for Civil Structures: From the Lab to the Field, Piervincenzo
Rizzo, Yi Qing Ni, and Jinying Zhu Volume 2010, Article ID 165132.
17. Dr. Hatem Hadi Obeid
http://www.iaeme.com/IJMET/index.asp 126 editor@iaeme.com
[2] Experimental modal analysis and dynamic strain fiber Bragg gratings for structural health
monitoring of composite antenna sub-reflector, Aikaterini Panopoulou, S. Fransen's,
Vicente Gomez-Molinero, Vassilis Kostopoulos
[3] E.N. Jacobs, K.E. Ward, & R.M. Pinkerton. NACA Report No. 460, "The characteristics
of 78 related airfoil sections from tests in the variable-density wind tunnel". NACA, 1933.
[4] Fundamentals of aerodynamics", John D. Anderson,Jr, third ed, chap 4
[5] Moran, Jack (2003). An introduction to theoretical and computational aerodynamics.
Dover. p. 7. ISBN 0-486-42879-6.
[6] Payne, Greg (8 Jul 1994), NACA 6, 7, and 8 series, archived from the original on April
27, 2009
[7] An experimental investigation into the high velocity penetration resistance of CFRP and
CFRP/aluminium laminates, Ming-ming Xu, Guang-yan Huang, Yong-xiang Dong, Shun-
shan Feng, Composite Structures, Volume 188, 15 March 2018, Pages 450-460.
[8] The Finite Element Method Using MATLAB, Second Edition 2nd Edition, Young W.
Kwon, Hyochoong Bang,
[9] Programing the Finite Element Method with Matlab, Jack Chessa, 3rd October 2002
[10] William Weaver, Jr. and Paul R. Johnston,"Finite Element Programs for Structural
Analysis", Standford University, Printice-Hall Inc, N. J., 1984.
[11] MATLAB Code for Structural Analysis of 2-D Structures Subjected to Static and Self-
Weight Loading Conditions, Naman Jain, International Journal of Trend in Research and
Development, Volume 4, 2017.
[12] EFFECT OF HIGHER ORDER ELEMENT ON NUMERICAL INSTABILITY IN
TOPOLOGICAL OPTIMIZATION OF LINEAR STATIC LOADING STRUCTURE, N
AMAN JAIN, Journal of Theoretical and Applied Mechanics, Sofia, Vol.48 No.3 (2018)
pp. 78-94.
[13] Finite element analysis of aircraft wing using carbon fiber reinforced polymer and glass
fiber reinforced polymer, Salu Kumar Das , Sandipan Roy, 2nd International conference
on Advances in Mechanical Engineering (ICAME 2018), IOP Conf. Series: Materials
Science and Engineering 402 (2018) 012077.