Airplane Wing Research Articles

Numerical and analytical analysis of wing spar made with different composite material

Composite materials and are generally utilized in airplane industries due to their predominant weariness attributes, more noteworthy weakness resilience and huge strength to-weight proportion when compared with their metal partners. This paper focuses on analysis of airplane wing made with aluminum and composites. The fundamental load bearing members in the wing are known as spars. Aircraft wing spar made with aluminum and composites is used for simulation and analysis. The numerical investigation was done by utilizing Structural Mechanics module in ANSYS. Airplane wing spar made with aluminum and composites is analyzed for various parameters, by differing the point load at its free end. The outcomes are compared and validated with numerical examination. The main purpose of the performing analysis is to choose the suitable material for the construction of the wing spar so that the weight of aircraft wing can be reduced. The results of the analysis show that carbon epoxy performs better than aluminum when the same load is applied.

Production Process of D-Nose Panel Components for A-350 Airplane Wings, PT Dirgantara Indonesia

Airplanes are one of the most frequently used forms of transportation globally. The aircraft's ability to mobilize between continents and its near-sound speed makes it an excellent cross-country travel choice. This paper discussed the production process of D-nose panel components for A-350 airplane wing in PT. Dirgantara Indonesia. PT. Dirgantara Indonesia (Persero) or commonly referred to as PTDI, is one of the aircraft companies in Asia with core competencies in aircraft design and development, aircraft structure manufacturing, aircraft production, and aircraft services for civil and military from light and medium aircraft. The main components of the aircraft consist of the engine, propeller (power plant), fuselage, wing, tail (empennage) and landing gear. The components that make up the wing of the aircraft consist of a fuel tank, wing flap, spar, aileron, skin, ribs, stringer, wingtip, as well as external parts such as the D-nose panel. The process from beginning to end of the D-nose panel component requires several stages. Finally, this process also checks data from existing component documents and ends with the final stamp as a sign that the entire process for making the D-nose panel component has been completed.

Failure Analysis in a Multilayerd Glass Fiber Reinforced Polyester Composite Plates under Flexural Loading

The usage of laminated glass fiber reinforced polyester composites in aerospace applications helps to reduce overall weight of the aerospace structures. The flexural strength of the laminated glass fiber reinforced composites becomes more important when they are employing for aeroplane wings. In this work, a laminated glass fiber polyester composite with two distinct sets of six different woven lamina stacking sequences is manufactured via hand layup technique. The effect of stacking sequence over the total ply failure load are investigated through universal testing machine. Finally, the progressive failure of the lamina in composites is also examined using ANSYS software.

Investigation of Aeroelastic Energy Extraction from Cantilever Structures under Sustained Oscillations

The present article is focused on a detailed computationalinvestigation of energy production capacity of various lightweight materials that are employed with piezoelectric vibration energy harvesters (PVEHs) subjected to various aeroelastic effects. Piezoelectric transducers are primarily employed to capture vibrational energy, which yields predictable and locally storable electrical energy. Higher energy extraction is possible under larger deflections of the structures when they are employed with PVEHs. In order to estimate the largest possible deflection of the structures, the response of them under external perturbations is estimated. An airplane wing consists of tapered planform, an advanced wind turbine blade, and the rectangular wings of an unmanned aerial vehicle (UAV) are considered for the vibrational analysis as the feasibility of achieving larger deflection is high compared with other aerodynamic surfaces. The stated elastic structures are modelled with different lightweight materials such as aluminium alloy, glass fibre-reinforced polymer (GFRP), titanium alloy, carbon fibre-reinforced polymer (CFRP), and Kevlar fibre-reinforced polymer (KFRP). Advanced partly coupled computational simulations are carried out with computational fluid dynamics (CFDs), and structural and vibrational effects to investigate the energy harvesting potential from the perturbations. Based on the outcomes of vibrational analysis, the raw transformable power production capacity of different lightweight materials that are employed with a cantilevered PVEH is estimated. The most suitable combination of material and associated aeroelastic effect which yields a significant amount of raw energy in each application is proposed and discussed with findings.

High amplitude time reversal focusing of sound and vibration

Time reversal (TR) is a signal processing technique that can be used to focus high amplitude sound or vibration at a desired location. TR focusing can be done with sources placed far from the desired focal location and the technique excels in complex environments. The impulse response between each source and the desired focal location must be obtained prior to the focusing and the environment must remain relatively unchanged for successful focusing. Multiple scattering or reverberation of waves off of many reflecting surfaces in the environment can actually be used advantageously by exploiting those reflections as additional image sources. This talk will provide an introduction to TR and then focus on the use of TR to provide high amplitude focusing of sound and vibration. Applications of high amplitude TR include lithotripsy of kidney stones, histotripsy of lesions, and locating cracks and defects in structures such as in human teeth, spent nuclear fuel storage casks, airplane wings, and automotive bearing caps. Recently, high amplitude TR of airborne sound has been studied in a reverberation chamber to generate a focused difference frequency and to study the nonlinear acoustics of the peak sound levels of 200 dB that have been attained.

Numerical and experimental investigation to design a novel morphing airfoil for performance optimization

Optimizing flying objects' wing performance has attracted a significant attention in the last few decades. In this article, some of the main mechanisms for changing the geometry of the wing were investigated and a new mechanism is proposed to improve the aerodynamic performance of the airplane wing. The designs have been simulated and analyzed from both aerodynamic and control points of view. In aerodynamic simulations using CFD methods, two airfoils of NACA series 6 with specifications 65-212 and 65-2012 were modeled. The results indicated that both airfoils used have a better performance compared to others in a certain range of the angle of attack. Subsequently, a new mechanism is proposed to change the wing geometry to optimize its structure. In the proposed mechanism, the structures of airfoils and wings consist of two fixed and moving parts, which can change their geometry with the help of a control circuit. The fixed part has a grooved track, and as the moving part moves in the direction of the grooves, the curvature of the upper and lower parts of the wing changes. The design control circuit includes an angle sensor, a micro controller, and a servomotor. The CFD results are entered into the micro controller as code. At any moment, the micro controller receives the angle data from the angle sensor and by comparing them with the CFD data, and issuing a command to the servomotor, it situates the wing curvature in the optimal state at all times. The built mechanism was tested at an attack angle of 0° and 25°. The results showed that the different parts of the mechanism work with very high precision and put the geometric shape of the wing in an optimal state in a completely intelligent way. It should be noted that the average error in test for t/c and Xt/c was 15.3% and 9%, respectively.

A Regional Approach to Aviation Accident Analysis in Hawaii

BACKGROUND: The geographical circumstances, such as mountains and ocean, and specific aviation operations, especially sightseeing, make the state of Hawaii stand out in aviation. These conditions support a regional approach to aviation accident analysis.METHODS:Accident reports of aviation accidents collected from the online National Transportation Safety Board database were used to study a 10-yr time period between 2008 and 2017.RESULTS: There was a significantly higher proportion of fatal accidents during night, dawn, and dusk (6 out of 13) than during daytime (13 out of 74). In addition, a significantly higher proportion of accidents occurred in diminished light conditions among fixed wing airplanes (11 out of 48) as opposed to other aircraft (2 out of 39), and among twin-engine aircraft (6 out of 12) as opposed to single-engine aircraft (7 out of 74). Out of seven weight-shift control aviation accidents, four were reported to be fatal; the latter all took place during instruction.DISCUSSION: Light conditions are the main environmental concern in Hawaiian aviation that particularly affect twin-engine fixed wing aircraft and warrant specific attention in advanced training exercises. Helicopter operations have not exhibited a diminished safety record since the 1990s, showing a lasting effect of a previous safety intervention. A relatively high number of fatal weight-shift control aircraft accidents requires further research in other parts of the United States.de Voogt AJ, Brause J. A regional approach to aviation accident analysis in Hawaii. Aerosp Med Hum Perform. 2023; 94(3):131-134.

Towards nonconservative conditions for equilibrium stability. Applications to switching systems with control delay

The objective of the paper is to give a unitary approach to nonconservative conditions of the equilibrium stability. The focus is on a real world system defined by a switched linear mathematical model having control delay. A control synthesis based on predictive state feedback is first applied to compensate the actuator delay. This results in a closed loop switching system free of delay. Then, a theorem giving conservative sufficient conditions of global uniform exponential stability for a switched system is proved. Next, a theorem expressing necessary and sufficient stability conditions is cited, in which the differences compared to the proved theorem are highlighted, but whose mechanism could not be applied in practice. Finally, it is shown how the problem of nonconservativeness can be solved starting from an important theorem given in the literature that uses the idea of homogeneous polynomial Lyapunov functions originating in the Hilbert’s famous 17th Problem. The paper investigates the complexity of the method in terms of numerical computation volume, and offers a way to circumvent the conflict between the method and the mathematical model. In this manner older and newer results are presented in a unitary concept and in a selfcontained approach. Numerical simulations are applied to a real-world model: an active vibration control for a physical model of an intelligent airplane wing in a wind tunnel. The substantial result of the simulations is the minimum guaranteed dwell time that characterizes the equilibrium stability of the switching system with control delay.

Stability analysis of electrical magneto hydrodynamic stagnation point flow of Ag-Cu/water hybrid nanofluid over a permeable stretching/shrinking slendering sheet: Entropy generation

The current study emphasises the stability test of electrical magneto hydrodynamic stagnation point flow of hybrid nanofluids with entropy generation in the existence of velocity and thermal slips over a porous slendering stretchable sheet. A mathematical modelling of [Formula: see text]/water hybrid nanofluid has been explored. Heat transfer proficiency of airplane wings is evaluated with the inclusion of distinguished effects like viscous dissipation and solar-based thermal radiation, so we included them in this article. Using suitable self-similarity transformations, the system of the fluid transport equations are converted into an ordinary differential system, which are determined by utilising the bvp4c in MATLAB software. The achieved outcomes are expressed as the skin friction, Nusselt number, velocity, temperature, Bejan number, entropy generation and streamlines with an influence of diverse physical parameters. The boundary-layer separation happens when the number of results fails to happen ahead of the critical value of the contracting parameter. To show the effect on flow and heat transfer of appropriate parameters, graphs are used. Stability is shown to be better in solution one than in the second, according to the results. The wall thickness variable augmented the velocity profile of the hybrid nanofluid for the first solution and a contrary for the second solution. Higher values of the thermal radiation parameter resulted in enhanced temperatures in the first and second solutions. It is also observed that the rate of heat transfer in the first solution increased as the electric field value increased.

Structural Analysis of Airplane Wing Using Composite and Natural Fiber Materials: A Survey

Abstract: Natural fiber-reinforced polymer-based composites are increasingly used in modern society due to their numerous benefits for uses in mechanical engineering. Polymer-based composite materials are widely employed in civil construction, automotive, aerospace, and many other industries due to their many benefits. Natural fibers can be used to create new, highperformance polymer materials because they are affordable, environmentally friendly, renewable, and partially and fully biodegradable. Examples of these fibers include EGR Glass R Glass, Carbon fiber, and S Glass, as well as kenaf, pineapple, sugarcane, hemp, oil palm, flax, and leaf. The purpose of this study is to explore the use of natural fibers and composites in the production of airplane wings, including mechanical characteristics, applications, and potential as well as problems and future demand for natural composite materials for engineering uses. A good 50% of the airspace's components are natural composites. Because natural composites have the ability to lower aircraft weight, they are currently being used to construct helicopters, military fighter aircraft, small and large civil transport aircraft, cockpits, satellites, launch vehicles, and missiles. Rudder, spoilers, LG doors, keel beam, airbrakes, elevators, turbine engine fan blades, propellers, rear bulkhead, wing ribs, main wings, interior fixtures, etc. Composites made of natural fibers are attractive and promising. The use of natural fiber-based composite materials is growing daily due to their strength and integrity. The natural fiber is a renewable, environmentally beneficial, and biodegradable raw material. Both its mechanical and thermal insulation qualities are strong in natural fiber. However, the loading placed on the natural fiber and its youthful modulus determines its strength In addition to discussing the benefits of natural fibers over other materials, this paper provides a description of the several types of natural fiber, their physical and mechanical properties, and their advantages.

Analysis of Existing Physical Theories Explaining Aerodynamic Lift Production by an Airplane

Since the first successful airplane, invented by The Wright brothers in the early 1900s, air travel has become one of the most common modes of transportation. While airplane production and use rapidly increase, explanations regarding the physics of flight remain elusive due to major shortcomings. With all the research available, this paper aims to explore how accurately current theories have explained lift production by an airplane's wing. The contents of this paper will touch on the subject of physics, more specifically fluid dynamics and aerodynamics, and even more specifically, the aerodynamic force known as lift. Theories analyzed in this paper include the "Equal Transit", "Skipping Stone", "Venturi", Momentum-Based, Bernoulli-Based, and Circulation theory. Overall, limitations leading to the inaccuracy of these explanations include not providing physical explanations for specific assumptions, misusing and misinterpreting principles and theorems, simplifying explanations thus not accounting for all necessary factors, proposing one-way causation relationships, confusing mathematical theories for qualitative physical theories, and conflicting experimental data. Because of this, an additional purpose of this paper is to provide a more accurate and comprehensive explanation for lift.

Modeling sloshing fuel tanks to provide oscillatory damping for airplane wings

Damping via fuel tanks could allow for lighter wing structures, but the complex flow behavior can be challenging to study.

A new study for aeroplane wing shapes made of boron nitride nanotubes-reinforced aluminium, Part I: review, dynamical analyses and simulation

A new approach for airplane wing shapes is found in this study with an analytical method. The paper studies the dynamical characteristics of aircraft wing plates using boron nitride nanotube (BNNT) reinforced for aluminium. The distribution of reinforcements through the thickness of the plates is considered to be uniform and functionally graded. The plate profile is defined in terms of a rectangular plate, in which an edge following a function is introduced according to arbitrary functions such as linear, circular, or hyperbolic functions. Equations of motion using geometric nonlinearities defined by von Karman-Donnell and theory of elasticity with applying Galerkin's method is used to obtain the dynamic and chaotic properties of the structure. The achieved results are validated with the previous documents and the finite element analyses (FEA) for fundamental frequencies to confirm the accuracy and reliability of the calculation method in this paper. The influence of the thermal environment, the volume of BNNT, the distribution pattern of reinforcement, as well as geometrical parameters are scrutinized in this paper. The research results show the superior properties of BNNT materials in reinforcing aircraft wings.

Stability analysis of diamond-silver-ethylene glycol hybrid based radiative micropolar nanofluid: A solar thermal application

The current study emphasizes the stagnation point flow and heat transmission properties of a hybrid-based micropolar nanofluid over a porous Riga plate that is capable of both shrinking and stretching. A mathematical modeling of diamond-silver-ethylene glycol/water hybrid nanofluid has been explored. Here 20% of ethylene glycol and 80% of water are considered as the base fluid. Heat transfer proficiency of airplane wings is evaluated with the inclusion of distinguished effects like viscous dissipation and solar-based thermal radiation, so we included them in this paper. By employing some suitable transformations, the system of nonlinear ordinary differential equations are attained and numerically solved by using MATLAB software. The dual nature of skin friction, Nusselt number, and micro-rotation gradient solutions are demonstrated for a wide variety of relating parameters. The boundary-layer separation happens when number of results fails to happen ahead of the critical value of the contracting parameter. To show the effect on flow and heat transfer of appropriate parameters, graphs are used. Stability is shown to be better in solution one than in the second, according to the results. It is detected that the temperature has decelerated in the presence of micropolar heat conduction parameter for both solutions The radiation parameter reduces the Nusselt number of the hybrid nanofluid for the first solution and a contrary for second solution. The array of the skin friction values are moving downwards for fluctuating values of heat source/sink. Sun based energy is the chief source of heat from the sun, and it utilizes in photovoltaic cells, sun-based power plates, photovoltaic lights and sun-based hybrid nanofluids. Specialists are currently exploring the utilization of nanotechnology and sun-based radiation to further develop flight effectiveness.

Unsteady Radiative Maxwell Fluid Flow over an Expanding Sheet with Sodium Alginate Water-Based Copper-Graphene Oxide Hybrid Nanomaterial: An Application to Solar Aircraft

The primary heat source from the sunlight is solar energy, which is used in photovoltaic panels, solar power plates, photovoltaic streetlights, and solar-based hybrid nanocomposites. A hybrid nanofluid is traversing an expanding sheet in this investigation. Maxwell fluid stream with two nanoparticles is going towards a trough with a parabolic form and is situated within the solar aircraft wing to investigate the phenomena of heat transfer rate. The term solar thermal radiation was introduced to describe heat transfer occurrence. The effectiveness of heat transmission from airplane wings is assessed by taking into account unique phenomena such as magnetic field and heat source. The bvp4c procedure was applied to quantitatively explain the energy and motion equations with MATLAB software. The copper (Cu) and graphene oxide (GO) nanosolid particles are mixed with sodium alginate (SA), a common liquid, to form the nanosolid particles. Numerous control variables are thoroughly examined, including temperature, shear stress, motion, friction component, and Nusselt number. The skin-friction coefficient upsurges with a growing magnetic impression. The upsurge in Deborah number reduces the skin-friction coefficient. The heat source impression declines the heat transport rate but upsurges the skin-friction coefficient. The skin-friction coefficient and heat transport rate increase with growing magnetic impression. When it comes to heat transfer analysis, hybrid nanofluid efficiency is substantially superior to that of regular nanofluid.

Comparison of Adaptive Fuzzy EKF and Adaptive Fuzzy UKF for State Estimation of UAVs Using Sensor Fusion

Development of an Adaptive Fuzzy Extended Kalman Filter (AFEKF) and an Adaptive Fuzzy Unscented Kalman Filter (AFUKF) for the state estimation of unmanned aerial vehicles (UAVs) were presented in this paper based on real flight data of a fixed wing airplane. The Adaptive Neuro Fuzzy extension helps to estimate the values of the EKF's and UKF's Rk covariance matrix at each sampling instant when measurement update step is carried out. The ANFIS monitors the EKF's and UKF's performances attempt to eliminate the gap between theoretical and real innovation sequences' covariance. The investigations show that AFUKF can provide better performance in accuracy and less error than the AFEKF in case of real flight data for maneuvering fixed wing UAVs.

Dynamics of radiative Williamson hybrid nanofluid with entropy generation: significance in solar aircraft

Sun based energy is the chief source of heat from the sun, and it utilizes in photovoltaic cells, sun-based power plates, photovoltaic lights and sun-based hybrid nanofluids. Specialists are currently exploring the utilization of nanotechnology and sun-based radiation to further develop flight effectiveness. In this analysis, a hybrid nanofluid is moving over an expandable sheet. Analysts are presently exploring the utilization of nanotechnology and sunlight-based radiation to further develop avionics productivity. To explore the heat transfer rate phenomenon, a hybrid nanofluid stream is moving towards a trough having a parabolic type shape and is located inside of solar airplane wings. The expression used to depict the heat transfer phenomenon was sun based thermal radiation. Heat transfer proficiency of airplane wings is evaluated with the inclusion of distinguished effects like viscous dissipation, slanted magnetic field and solar-based thermal radiations. The Williamson hybrid nanofluid past an expandable sheet was read up for entropy generation. The energy and momentum expressions were solved numerically with the utilization of the Keller box approach. The nano solid particles, which are comprised of copper (Cu) and Graphene oxide, are dispersed utilizing SA (Sodium alginate) as an ordinary liquid (GO). A huge number of control factors, for example, temperature, shear stress, velocity, frictional element along with Nusselt number are investigated in detail. Intensification of thermal conduction, viscous dissipation and radiation improve the performance of airplane wings subjected to heat transmission. Hybrid nanofluid performance is much better than the ordinary nanofluid when it comes to heat transmission analysis.

Predicting Coherent Turbulent Structures via Deep Learning

Turbulent flow is widespread in many applications, such as airplane wings or turbine blades. Such flow is highly chaotic and impossible to predict far into the future. Some regions exhibit a coherent physical behavior in turbulent flow, satisfying specific properties; these regions are denoted as coherent structures. This work considers structures connected with the Reynolds stresses, which are essential quantities for modeling and understanding turbulent flows. Deep-learning techniques have recently had promising results for modeling turbulence, and here we investigate their capabilities for modeling coherent structures. We use data from a direct numerical simulation (DNS) of a turbulent channel flow to train a convolutional neural network (CNN) and predict the number and volume of the coherent structures in the channel over time. Overall, the performance of the CNN model is very good, with a satisfactory agreement between the predicted geometrical properties of the structures and those of the reference DNS data.

Fatigue and static damage in curved woven fabric carbon fiber reinforced polymer laminates

Failure mechanisms of curved cross-ply laminates under static and fatigue loading have been studied extensively, but the examination of fabric laminates which are the most commonly used ply type in curved supports in airplane wing structures is lacking. In this study, unidirectional (UD) and fabric carbon fiber reinforced polymer (CFRP) laminates are examined to elucidate the failure initiation mechanisms of laminated composites under fatigue and static loading. The crucial point of the research is applying the analyses using fabric laminate with a currently used stacking sequence in commercial airplanes. In addition to the fabric laminate, UD laminate is also included in the research to compare the real complex stacking with the simplest stacking. In the experiments, it is observed that both static and fatigue failures initiate roughly at the maximum radial stress location (approximately 35% of the thickness from the inner radius). For UD laminates, there is no visible difference between the failure mechanisms under static and fatigue loadings. However, for fabric laminates, fatigue failure is observed to occur as a single major crack at the maximum radial stress location as in UD laminates, whereas static failure is observed to occur as multiple diffusive cracks at the maximum radial stress location. Additionally, cracks grow mostly as intralaminar cracks connected with regions of occasional interlaminar cracks.

Ultrasonic inspection for ice accretion assessment: effects on direct wave propagation in composite media

From aeroplane wings to overhead power lines, through giant blades of wind turbines, a build up of ice can cause problems ranging from impaired performance all the way to catastrophic failure. Therefore, it is of the utmost importance to control or prevent ice formation, especially on the critical areas of a structure. However, de-icing and anti-icing countermeasures can result energetically expensive and hazardous to the environment. In addition, excessive use of such of them will reduce the life of the ice protection system and introduce fatigue to the controlled structures. Thus, in order to manage properly the available resources, it is desirable to have an ice detection system that can both detect ice formation and monitor the thickness of ice on critical surfaces. This would allow acting when it is necessary. Ultrasonic guided-wave-based technique has been proved reliable for ice detection, but approaches to establish ice accretion over time have not been provided yet. The paper investigates the interaction of ultrasonic direct waves in composite plate with ice layers and the effects of ice thickening on the ultrasound propagation. Moreover, the use of metrics is discussed as indicators of ice growth.