Planar Wing Research Articles

A Novel Tailsitter UAV with Configurable Wings

In this study, we propose a novel tailsitter unmanned aerial vehicle with configurable wings using a parallel link mechanism. It has two flight modes: a hover mode and a forward flight mode by pitching, similar to conventional tailsitters. In addition, it can deform its airframe in each flight mode. In the hover mode, it can tilt the frame in the pitch direction while hovering. In the forward flight mode, it can change the configuration of the wings during forward flight. In experiments, we show that it can transition from the hover mode to the forward flight mode with three wing configurations: non-staggered wings (biplane) and positively and negatively staggered wings (tandem wing plane), using an attitude controller for conventional quadrotors.

What Puts the "Tribo" in Triboelectricity?

An enduring question in science has been why sliding plays a major role in the triboelectric generation of static electricity-the "tribo" in triboelectricity. We provide here a general explanation which is rooted in established science. When sliding is taking place, there is symmetry breaking due to elastic shear, so the front of the sliding body experiences different elastic strains from the back. Consequently the polarization and associated charges at the front and back are not the same, and the difference between the two leads to current flow similar to the difference in air pressure above and below a plane's wing leading to lift. Specific calculations are provided which show good agreement with prior experimental measurements of size and shape dependencies, and reasonable quantitative agreement with experimental current measurements.

Relative positioning method for unmanned aerial vehicles in complex electromagnetic environment

In view of the problem that satellite navigation and positioning systems may fail or be unreliable in complex electromagnetic environments, which may lead to divergence of UAV positioning, the inertial navigation systems working for a long time may lead to increasing errors. This paper adopts a relative navigation algorithm that combines airborne inertial navigation systems and inter-aircraft relative information measurement. The algorithm requires each UAV to load relative navigation equipment and inertial navigation systems and acquire and fuse relative navigation information through inter-aircraft communication. In this relative navigation algorithm, the host and wing plane can transmit their respective navigation information and relative navigation information to each other, and fuse information from different sources through a Kalman filtering algorithm to enhance the accuracy of relative positioning data. With the help of corrected and feedback relative positioning data, the relative location of the host and wingman is achieved. The actual simulation results show that the relative position RMSE of the host, Wing Plane 1, and Wing Plane 2 in the X, Y, and Z dimensions are 1.345 m, 0.7388 m, 1.645 m, 2.167 m, 1.201 m, and 2.069 m, respectively. It is apparent that this scheme improves the relative navigation performance and robustness of the UAV group.

Acetabular retroversion: functional or anatomical?

The aim of this study is to evaluate whether acetabular retroversion (AR) represents a structural anatomical abnormality of the pelvis or is a functional phenomenon of pelvic positioning in the sagittal plane, and to what extent the changes that result from patient-specific functional position affect the extent of AR. A comparative radiological study of 19 patients (38 hips) with AR were compared with a control group of 30 asymptomatic patients (60 hips). CT scans were corrected for rotation in the axial and coronal planes, and the sagittal plane was then aligned to the anterior pelvic plane. External rotation of the hemipelvis was assessed using the superior iliac wing and inferior iliac wing angles as well as quadrilateral plate angles, and correlated with cranial and central acetabular version. Sagittal anatomical parameters were also measured and correlated to version measurements. In 12 AR patients (24 hips), the axial measurements were repeated after matching sagittal pelvic rotation with standing and supine anteroposterior radiographs. Acetabular version was significantly lower and measurements of external rotation of the hemipelvis were significantly increased in the AR group compared to the control group. The AR group also had increased evidence of anterior projection of the iliac wing in the sagittal plane. The acetabular orientation angles were more retroverted in the supine compared to standing position, and the change in acetabular version correlated with the change in sagittal pelvic tilt. An anterior pelvic tilt of 1° correlated with 1.02° of increased cranial retroversion and 0.76° of increased central retroversion. This study has demonstrated that patients with symptomatic AR have both an externally rotated hemipelvis and increased anterior projection of the iliac wing compared to a control group of asymptomatic patients. Functional sagittal pelvic positioning was also found to affect AR in symptomatic patients: the acetabulum was more retroverted in the supine position compared to standing position. Changes in acetabular version correlate with the change in sagittal pelvic tilt. These findings should be taken into account by surgeons when planning acetabular correction for AR with periacetabular osteotomy.

ANALISIS CFD PADA SAYAP MINI GLIDER DENGAN PENAMPANG LOW REYNOLD NUMBER AIRFOIL DAN FOLDED FLAT PLATE AIRFOIL

The purpose of this research is to make a very small unmanned aircraft as a teaching aid in aerospace engineering workshops, because of its very small size, this type of unmanned aircraft is abbreviated as Micro Air Vehicle, this MAV is only operated at low Reynolds numbers. MAV development research for smaller sizes continues to be carried out such as the Micro Glider. In this study, the author uses the Computational Fluid Dynamic method and the software used ANSYS Fluent and compares the existing DATCOM data, the author simulates the 4 types of airfoils into a wing object. The results of this study can be seen that based on the average deviation diff value that has been obtained in a population to determine the error from the comparison of the reference airfoil lift coefficient and its FFP by comparing the two methods, namely the IISHI airfoil reference geometry is 6.22% while the FFP is is 11.25% and the SD 7037 airfoil reference geometry is 3.71% while the FFP is 2.11%. Then for the comparison of the maximum lift to drag ratio values, it is obtained that the airfoil reference geometry (SD 7037) has a value of = 9.96 while the airfoil reference geometry (IISHI) has a value of = 8.81. In the Folded Flat Plate airfoil geometry (SD 7037) it has a value of = 7.61 while the Folded Flat Plate airfoil (IISHI) has a value of = 7.37. Then for the visualization of fluid flow can be obtained, namely the results of visualization of fluid flow in several parts of the angle of view / plane of the wing geometry when the AoA is high, namely the root plane to the half wing plane. early, while the geometry of SD 7037 (airfoil reference) is not easy to occur early turbulence flow. Second, that in general the fluid flow pattern seen in the FFP airfoil geometry (FFP IISHI) has the most dominant turbulence flow pattern (very much/large) while the FFP airfoil geometry (FFP SD 7037) has very little/small turbulence flow pattern..

Investigating Planar and Nonplanar Wing Planform Optimisation for Ground Effect Aircraft

Wing-in-Ground (WIG) effect aircraft are gaining attention for their potential in reducing environmental impact. However, optimising wing planforms based solely on aerodynamics might improve performance while compromising static height stability of WIG aircraft. This study investigates the effects of planar and nonplanar wing planform optimisation for regional transport ground effect aircraft. Three distinct multiobjective wing planform optimisations are explored: planar wing optimisation, nonplanar wing optimisation, and nonplanar wingtip optimisation. These optimisations assess the impact on both aerodynamic efficiency and static height stability characteristics of a wing planform in ground effect, at three different flying altitudes. In extreme ground effect, the Pareto set includes wings with negative spanwise camber, enhancing both cushion sensation and aerodynamic efficiency by effectively utilizing ground effect, thus proving advantageous over planar wing configurations.

Levy Flight Equilibrium Optimizer–Based Wing Design Optimization Using Functional Constraints

This paper presents wing design optimization with functional constraints using the proposed method. The proposed method is an equilibrium optimizer (EO), and it is motivated by controlling the volume mass balance method to calculate both equilibrium and dynamic states. A well-defined generation rate term is verified to strengthen the capability of the EO at exploitation and exploration. Here, the EO’s updating behavior is enhanced by Levy flight. Hence, it is named as Levy flight–based equilibrium optimizer (LFEO). The analysis device of aerodynamics is intended by combining the numerical nonlinear lifting-line method to attain the coefficients of lift and drag of the baseline wing. The proposed method is utilized for solving restricted optimization problems, and three various optimization problems are solved. The functional restrictions are connected to wing weight, wing plan form area, and root bending moment, which is included in the first optimization issue, and then the second optimization issue is created. The third optimization issue is attained by including to the second issue the state of level flight and minimum speed of the baseline unmanned air vehicle (UAV) at the maximum speed of level flight and obtainable power restrictions. It shows that describing the moment of root bending, wing area, and obtainable power restrictions at aerodynamic optimization issues may lead to various realistic wing-plane and airfoil shapes. Finally, the proposed method is implemented using MATLAB or Simulink and it is compared with existing techniques such as EO and genetic algorithm (GA).

Nanogenerator based self-powered motion monitoring for flapping wings of bio-inspired flying robots

Under the constraints of weight and power, achieving airborne monitoring of wings' flexible motion toward bio-inspired flying robots is an arduous challenge. Herein, we present a self-powered motion monitoring method based on nanogenerators to tackle this issue. First, a locally adaptable integration structure of triboelectric nanogenerator (TENG) integrated wings is proposed for the design of airborne devices. Second, a theoretical output model is developed to dynamically monitor the flapping motion of TENG-integrated wings. The proposed approach is a multi-target monitoring technique that enables the sensing of parameters, such as the flapping frequency and the flapping angles with stability. After validation, the monitoring error of the wing plane's pitch angle affected by device stability is less than 0.7°. Likewise, the maximum observed error rate for flapping frequency monitoring is about 0.1%. This technique will further enhance the intelligent airborne wing state perception for bio-inspired flying robots.

A Reconstructive Approach for Design of a Planar Supercritical Wing

Effort is made to design an efficient planar wing that can support transonic pressure distribution. Wing for transport airplane role is considered. First optimal warp is generated for minimum induced drag for a Mach number that is just below transonic Mach number. Optimal warp thus generated is split into twist and camber. The resulting camber is used to form a planar wing. The camber of this aerofoil is varied along span. Twist is no more considered. Aerofoil thickness is superimposed on this camber. Mach number is increased till supercritical flow appears.The whole process is reconstructive in approach. Results obtained are very encouraging and are application oriented. Pattern of supercritical pressure distribution is studied from point of view of suction peaks, shock wave location, and aft loading intensity occurring towards trailing edge. Main effort of our exercise is to create shock free transonic wing.

Vortex generation due to multiple localized magnetic fields in the hybrid nanofluid flow – A numerical investigation

Vortices capture the attention of every scientist (as soon as they come into existence) while studying any flow problem because of their significance in comprehending fluid mixing and mass transport processes. A vortex is indeed a physical phenomenon that happens when a liquid or a gas flow in a circular motion. They are generated due to the velocity difference and may be seen in hurricanes, air moving across the plane wing, tornadoes, etc. The study of vortices is important for understanding various natural phenomena in different settings. This work explores the complex dynamics of the Lorentz force that drives the rotation of nanostructures and the emergence of intricate vortex patterns in a hybrid fluid with Fe3O4–Cu nanoparticles. The hybrid nanofluid is modeled as a single-phase fluid, and the partial differential equations (PDEs) that govern its behavior are solved numerically. This work also introduces a novel analysis that enables us to visualize the flow lines and isotherms around the magnetic strips in the flow domain. The Lorentz force confined to the strips causes the spinning of hybrid nanoparticles, resulting in complex vortex structures in the flow domain. The results indicate that the magnetic field lowers the Nusselt number by 34% while raising the skin friction by 9%. The Reynolds number amplifies the influence of the localized magnetic field on the flow dynamics. Lastly, the nano-scaled structures in the flow enhance the Nusselt number significantly while having a minor effect on the skin friction factor.

Effect of winglet cant angle on the performance of an aircraft wing

The complicated and quick Winglet tool is attached to the end of the plane's wings. It's more like a vertical or angled extension on each wing's parameters. Due to wingtip vortices, airplane wing performance is primarily low, bringing about drag. In this project, wing evaluation of the Cessna wing prototype for the NACA 2412 at Mach 0.1 is accomplished at one sort of cant angle. At this time, certain Winglet angles of 150, 350 and 550 are chosen to fill in any study gaps and provide results based on systematic research through CFD evaluation of the factors. The objective of this project is to provide a precise approach for reading in Ansys Workbench concerning the preferred Catia CAD model. At high and idle speeds, well-designed winglet reduces drag and potentially enabling the increased cruise speed. Winglets offer an incredibly inexpensive way to improve an aircraft's standard performance, especially when comparing unique solutions with engine upgrades.

Probabilistic Risk Assessment of Accidental Damage to Civil Aircraft Composite Structures

<div>In view of the structural accidental events in the ongoing airworthiness stage of civil aircraft, it is necessary to conduct a risk assessment to ensure that the risk level is within an acceptable range. However, the existing models of risk assessment have not effectively dealt with the risk of accidental structural damage due to random failure. This article focuses on probabilistic risk assessment using the Transport Airplane Risk Assessment Methodology (TARAM) of accidental structural damage of civil aircraft. Based on the TARAM and probability reliability integral, a refined failure frequency probability calculation model is established to elaborate on composite structure failure frequency. A case study is analyzed for the outer wing plane of an aircraft having impact damage of composite materials. Finally, results of the risk assessment without correction and risk assessment with correction are presented for detailed visual inspection and general visual inspection.</div>

Biomechanical evaluation of custom-made short implants with wing retention applied in severe atrophic maxillary posterior region restoration: A three-dimensional finite element analysis.

Severe bone atrophy in the maxillary posterior region poses a big challenge to implant restoration. Digitally designed and customized short implants with wing retention provide a safer and minimally invasive implant restoration scheme in such circumstances. Small titanium wings are integrated with the short implant supporting the prosthesis. Using digital designing and processing technology, the wings fixed by titanium screws can be flexibly designed, providing the main fixation. The design of the wings will influence the stress distribution and implant stability. This study analyzes the position, structure, and spread area of the wings fixture scientifically by means of three-dimensional finite element analysis. The design of the wings is set to linear, triangular, and planar styles. Under the simulated vertical and oblique occlusal forces, the implant displacement and stress between the implant and the bone surface are analyzed at different bone heights of 1mm, 2mm, and 3mm. The finite element results show that the planar form can better disperse the stress. By adjusting the cusp slope to reduce the influence of lateral force, short implants with planar wing fixtures can be used safely even if the residual bone height is only 1mm. The results of the study provide a scientific basis for the clinical application of this new customized implant.

Conceptual Aircraft Empennage Design Based on Multidisciplinary Design Optimization Approach

Within a conventional aircraft design process, the horizontal tail and vertical tail are generally sized via volume coefficient methods. In this manuscript, an improved method for conceptual aircraft tail design based on multidisciplinary design optimization (MDO) approach with stability and control constraints has been developed. To develop this method, first, the tail design requirements have been derived from the regulations and the fundamental functionalities of tail plans. Then, the empennage design is formulated as an MDO problem. Eventually the design optimization of horizontal and vertical tail is combined with the design optimization of the aircraft wing. A test case is presented for concurrent wing and tail plane design, which resulted in more than 9% reduction in aircraft block fuel weight and more than 3% reduction in aircraft maximal takeoff weight, which indicates a great potential for fuel burn and carbon reductions with empennage design optimization at conceptual aircraft design phase.

Experimental Study of Flutter Characteristics of Selected Wing Plan forms for the Effect of Camber

This article focuses on understanding the effect of airfoil camber on the flutter characteristics of the wing. Experiments were conducted on four-wing models at different air velocities/ airspeeds and at different angles of attacks on wing models that are manufactured with the same span chord dimensions and also the same material. Accelerometers are attached to the wing tip on the leading and trailing edges to measure the change in value of acceleration with time using the Arduino and Arduino code. From the results obtained, it is observed that as the location of camber moves closer to the flexural axis, the flutter seems to be induced faster than otherwise.

Effect of Plasmonic Au and Ag/Au Nanoparticles and Sodium Citrate on the Optical Properties of Chitin-Based Photonic Nanoarchitectures in Butterfly Wing Scales

Porous butterfly wings with hierarchically organized structures from nanometer to centimeter scales were tested as substrates for carrying plasmonic Au and Ag/Au nanoparticles with potential application in photocatalysis. Wings exhibiting structural color generated by chitin-air nanocomposites were used. Hundreds of butterfly species possess these types of color-generating photonic nanoarchitectures, producing color by a similar mechanism to manmade photonic crystals. Artificial photonic crystals are known to enhance photocatalytic processes through the slow light effect. The impact of pure water, water-based sodium citrate solution, and Au and Ag/Au alloy nanoparticles on the optical properties of the natural photonic structures were separated. While water and aqueous sodium citrate solutions change the wing reflectance by the alteration of the wing scale position with respect to the wing plane, Au and Ag/Au alloy nanoparticles form a new, hybrid nanostructure with the chitin nanoarchitecture modifying the structural color of the butterfly wings. The optical properties of the new types of hybrid photonic nanoarchitectures (consisting of butterfly wings and plasmonic nanoparticles) are different from those of the components.

Thermal cooling process by nanofluid flowing near stagnating point of expanding surface under induced magnetism force: A computational case study

This paper is dedicated to the exam of entropy age and research of the effect of mixing nanosolid additives over an extending sheet. In this review, Newtonian nanofluid version turned into researched at the actuated appealing field, heat radiation and variable heat conductivity results. With becoming modifications, the proven PDEs are moved into popular differential situations and paintings mathematically making use of a specific mathematical plan called the Keller box method (KBM). The ranges of different dimensionless parameters used in our study are volume fraction of nanoparticles 0.01 ≤ φ ≤ 0.04 , magnetic parameter 0.5 ≤ Λ ≤ 2 , thermal radiation 0.1 ≤ N r ≤ 0.3 , heat source/sink parameter 0.5 ≤ Q 0 ≤ 2 , Prandtl number 5.7 ≤ P r ≤ 6.2 , variable thermal conductivity 0.1 ≤ ε ≤ 0.3 , reciprocal magnetic Prandtl number 0.6 ≤ λ ∗ ≤ 1 , Brinkman number 5 ≤ B r ≤ 15 , Reynolds number 5 ≤ R e ≤ 15 , which shows up during mathematical arrangement are shown as tables and charts.Positive modifications in heat radiation and heat conductivity affects increment the hotness pass coefficient of solar primarily based totally plane wings. Titanium alloy primarily based totally water (H 2 O) are taken into consideration for our research. We will likewise alternate the grouping of nanoparticles to pay attention on their impact on numerous dynamic barriers of the framework. We can see that because the Reynolds range and Brinkman range increment, the entropy increments. The thermodynamic exhibition of Titanium alloy-water (Ti 6 Al 4 V–H 2 O) nanofluid has been portrayed higher that of base nanofluid with comparable situations. Recorded hypothetical reproductions may be greater beneficial to similarly increase daylight primarily based totally nuclear strength frameworks.

Design and Analysis of Composite of Aluminium-7075 and Si-C Metal Matrix Composite with Egg Shell

Abstract: Metal Matrix Composite possess increasingly improved properties including high enduringness, hardness, density and sensible wear resistance compared to alloys or the other metals.during this paper the composite material is developed by reinforcing of silicon carbide (Si-C) powder and egg shell in metal alloy Al7075. The composites square measure fabricated by Stir Casting Machine. TheMMC’s specimens square measure ready by varyingthe proportion of weight fraction of the particles in three compositions. During this work Al-7075 Si-C MMCs square measured by admixture molten metallic element with silicon carbide by the help of mechanical stirring, called stir casting methodology.Conjointly during this work, the stir casting methodparameters square measure optimized at intervals thevary to get sensible mechanical characteristics anduniform admixture of reinforcement, that could be amajor concern in stir casting. The mechanical properties square measure enduringness, Impact check, Hardness is planned to analyze. The investigation is performed to check if the new MMCare able to replace plane wings.

Horizontal tail buffeting characteristics at wing vortex flow impact

Modern, high-agility aircraft configurations often suffer from tail buffeting at subsonic speeds and medium to high angles of attack. This structural dynamic excitation through the unsteady flow field can result in heavy structural damage and degraded handling qualities. A flexible wind tunnel half model was developed at the Chair of Aerodynamics and Fluid Mechanics of the Technical University of Munich in cooperation with the Department of Acoustics and Vibration of Airbus Defence and Space. To provide enough flexibility, the wing and horizontal tail plane (HTP) are 3D-printed from polylactide (PLA). The model is used to experimentally analyze buffeting and to validate computational buffeting prediction. The objective of the present work is to examine aeroelastic phenomena with the modular designed flexible wind tunnel model. The measurement campaign takes place at the Göttingen type wind tunnel A. The model is equipped with various sensors. For unsteady pressure measurements on the surface of the wing and the HTP, piezo-resistive Kulite pressure transducers are installed on the wing and on the HTP. In addition, the flow field is described on the basis of numerical simulation results. For analyzing the structural response resulting from buffeting, miniature accelerometers are installed at the tips of the wing and the HTP. Strain gauges are used for calculating bending strains. As a reference case, a fully aluminum model is equipped correspondingly, but without strain gauges. Dominant frequencies corresponding to the structural eigenmodes can be identified and are excited in the PLA-setup (Buffeting). The unsteady pressure fluctuations on the surfaces act as the aerodynamic excitation input (Buffet). The measured tip accelerations of wing and tail are compared to simulation results with a one-way coupling CFD-CSM simulation.

Selection Criteria for Biplane Wing Geometries by Means of 2D Wind Tunnel Tests

This paper presents a study based on wind tunnel research on biplane configurations. The objective of this research is to establish an experimental basis for relationships between the main geometrical parameters that define a biplane configuration (stagger, decalage, gap, and sweep angle) and the aerodynamic characteristics (CL, CD). This experimental study focuses on a 2D approach. This method is the first step towards dealing with the issue, and it allows the variables involved in the tests to be reduced. The biplane configuration has been compared with the monoplane configuration to analyze the viability for implementing the biplane configuration in the field of application for micro air vehicles (MAV). At present, the biplane and other unusual configurations have not been a common design for MAV; however, they do have unlimited future potential. A set of experimental tests were carried out on various biplane configurations at low Reynolds numbers, which allowed the criteria for selecting the best wing configuration to be defined. The results obtained here show that the biplane configuration provides a higher maximum lift coefficient (CLmax) than the planar wing (monoplane). Furthermore, it has a larger wetted surface than the planar configuration, so the parasitic drag increases for the biplane configuration. This research is focused on a drone flight regime (low Reynolds number), and in this case, the parasitic drag (profile drag) has an important role in the total drag of the airplane. This study considers whether the reduction in the induced drag due to three–dimensional configuration (biplanes, box–wings, and joined–wings) can reduce the total drag or if the increase in the parasitic drag is bigger. Additionally, the increase in lift and the decrease in parasitic drag (profile drag) will be studied to determine if they have a greater influence on the performance of the airplane than the increase in structural weight. Further research is planned to be performed on 3D prototypes, with the selected configurations, and applied to nonconventional wing planforms.