Aircraft Wing Structures Research Articles

Выбор оптимальной конструктивно-силовой схемы лонжеронного композитного крыла

This paper describes a method for optimizing the design of a spar-type composite aircraft wing structure based on multi-criterion approach. Two types of composite wing structures such as two-spar and three-spar ones were considered. The optimal design of a wing frame was determined by the Pareto method basing on three criteria: minimal weight, minimal wing deflection, maximal safety factor and minimal weight. Positions of wing frame parts, i.e. spars and ribs, were considered as optimization parameters. As a result, an optimal design of a composite spar-type wing was proposed. All the calculations necessary to select the optimal structural and design of the spar composite wing were performed using nonlinear static finite element analysis in the FEMAP with NX Nastran software package.

Improved Immune Genetic Algorithm to Optimize the Design of Wing Structure of Competition Aircraft

An improved immune genetic algorithm is used to design and optimize the wing structure parameters of a competition aircraft. According to the requirements of aircraft design, multi-objective optimization index is established. On this basis, the basic steps of using immune algorithm to optimize the main design parameters of aircraft wing structure are proposed, and the optimization of the wing parameters of a competition aircraft is used as an example for simulation calculation. The design variables in the optimization are the size of the wing components, and the optimization goal is to minimize the weight of the wing and the maximum deformation of the wing structure. Research shows that compared with traditional optimization methods; the improved immune genetic algorithm is a very effective optimization method. At the same time, a prototype is made to check the validity and feasibility of the design. Flight test results show that the optimization method is very effective. Although the method is proposed for competition aircraft, it is also applicable to other types of aircraft.

Effective Application of an Anisogrid Composite to Design the Components of the Aircraft Wing Structure

Effective Application of an Anisogrid Composite to Design the Components of the Aircraft Wing Structure

Structural Static/Fatigue/Damage Tolerance Comprehensive Design Optimization of Composite Laminate

This paper develops a structural static/fatigue/damage tolerance comprehensive design method for composite laminated structures under mechanical–thermal coupling environments. The developed design method can finely quantify the additional stress and deformation caused by the mechanical–thermal coupling effect. In addition, a new damage evolution-based fatigue reliability evaluation method is proposed, and the structural fatigue behavior can be described and predicted. The different failure modes of composite material and their correlations are considered during the damage evolution analysis. The structural possible accidental damage can also be taken into account by applying the global preset damage in design stage. Thus, the static requirement, fatigue requirement, and damage tolerance requirement can all be considered simultaneously during the design process. The structural comprehensive design of composite laminate is conducted by virtue of the two-level optimization method. A case of a notched composite laminate is employed to verify the proposed method. In addition, a case of a civil aircraft wing structure is used to explain the feasibility of the developed method in dealing with structural design problems in engineering.

Numerical modeling on dynamics of droplet in aircraft wing structure at different velocities

PurposeThe purpose of this paper is to find the droplets impact on the airplane wing structure. Two kinds of characteristics of the droplet at different velocity and viscosity are assumed. The droplet is assumed to be spherical cubic form and it is injected from the convergent divergent nozzle with a passive control.Design/methodology/approachThis paper presents the results of a numerical simulation of droplet impact on the horizontal surface. The effects of impact parameters are studied. The splash effect of the droplet also visualized. The results are presented in form of stress, strain, displacement magnitude of the droplet.FindingsCrosswire is used as passive control. The behavior of the droplet impact is observed based on the kinetic energy and the gravitational forces.Originality/valueThe results predict that smooth particle hydrodynamic designed droplet not only depend on the equation of state of the droplet but also the injection velocity from the nozzle. It also determined that droplet velocity is depending on the viscosity of the fluid.

Ground Structures-Based Topology Optimization of a Morphing Wing Using a Metaheuristic Algorithm

This paper presents multi-objective topology and sizing optimization of a morphing wing structure. The purpose of this paper is to design a new aircraft wing structure with a tapered shape for ribs, spars, and skins including a torsion beam for external actuating torques, which is anticipated to modify the aeroelastic characteristic of the aircraft wing using multi-objective optimization. Two multi-objective topology optimization problems are proposed employing ground element structures with high- and low-grid resolutions. The design problem is to minimize mass, maximize difference of lift effectiveness, and maximize the buckling factor of an aircraft wing subject to aeroelastic and structural constraints including lift effectiveness, critical speed, and buckling factors. The design variables include aircraft wing structure dimensions and thickness distribution. The proposed optimization problems are solved by an efficient multi-objective metaheuristic algorithm while the results are compared and discussed. The Pareto optimal fronts obtained for all tests were compared based on a hypervolume metric. The objective function values for Case I and Case II at 10 selected optimal solutions exhibit a range of structural mass as 115.3216–411.6250 kg, 125.0137–440.5869 kg, lift effectiveness as 1.0514–1.1451, 1.0834–1.1639 and bucking factor as 38.895–1133.1864 Hz, 158.1264–1844.4355 Hz, respectively. The best results reveal unconventional aircraft wing structures that can be manufactured using additive manufacturing. This research is expected to serve as a foundation for future research into multi-objective topology optimization of morphing wing structures based on the ground element framework.

Reliability-Based Design of an Aircraft Wing Using a Fuzzy-Based Metaheuristic

The purpose of this paper is to design aircraft wing using reliability-based design optimization concerned to fuzzy uncertainty variables. A possibilistic safety index-based design optimization (PSIBDO) with fuzzy uncertainties is proposed to overcome difficult tasks from the original probabilistic problem. The design problem is to minimize mass of a composite aircraft wing subject to aeroelastic and structural constraints through consideration of the material properties are the uncertainties. The design variables include aircraft wing structure dimensions. The reliability-based design approach is needed to alleviate such a problem. Due to the complexity of the aircraft wing structures design and aeroelastic analysis, nonprobability-based design is an alternative choice to increase computational efficiency in the design process. The optimum results show the efficiency of our proposed approach.

Метод расчета усталостного повреждения регулярных зон крыла самолета при случайном нагружении на этапах типового полета

In accordance with the airworthiness standards, the aircraft structure must be operationally survivable, it means that structure must be able to remain efficiency in the presence of admissible damage. But, accumulating above than a certain level, damages cause fatigue failure of the structure, in the form of micro- and submicrocracks, thus reducing its strength characteristics. Currently, several approaches have been formed to ensure the safety of an aircraft structures in terms of strength. One of them is ensuring a safe resource (safe durability). This principle implies that during the specified service life of the product, no damage will occur in it, reducing the strength below the permissible level. The aircraft resource is limited “from above” by the durability of the regular zones of airframe. Therefore, predicting the durability of an aircraft wing structure at the design stage is a fundamental engineering problem to ensure its safety and economic efficiency. At the same time, the first step in dealing with aircraft fatigue damage at the design stage is the collection and assessment of the operational loads of the analog aircraft. However, at the design stage of a new aircraft model, obtaining such data is not always possible. Therefore, the purpose of this article is to develop a method for calculating fatigue damage at the stage of cracking and assessing the durability of regular zones of a transport aircraft wing, taking into account the conditions of its operation. The tasks to be solved are: to isolate the factors that determine the durability of the aircraft at flying in turbulent air; to take into account the asymmetry of loads and accumulated damage that occurs at each stage during the entire flight of the aircraft; to determine the aircraft's resource depending on the profile of a typical flight. The method is based on a standardized atmospheric turbulence model, typical flight profiles, fatigue characteristics of materials, the hypothesis of linear summation of damages and calculation based on nominal stresses. As result, comparison between the calculated integral repeatability of overloads and equivalent bending moments with the results of processing flight test data showed good agreements. Conclusions. The scientific novelty of the work lies in the fact that a method for calculating the fatigue damage of the regular wing zones, taking into account the expected flight profile of the aircraft was developed. This means that the proposed method makes it possible to carry out a preliminary assessment of the resource when designing an airplane without using data on the operational loads of an analogue airplane, and also estimate the residual resource of the airplane during its operation.

Multi-Performance Optimization in Friction Stir Welding of AA6082/B4C Using Genetic Algorithm and Desirability Function Approach for Aircraft Wing Structures

Multi-Performance Optimization in Friction Stir Welding of AA6082/B4C Using Genetic Algorithm and Desirability Function Approach for Aircraft Wing Structures

A Study on the Deformation due to High Speed Processing of Aircraft Wing Structure

Residual stresses generated during high-speed machining of spoiler beams used in aircraft cause product deformation and dimensional mismatch, which increases the defect rate and leads to material waste. To overcome this problem, the processing site uses manual modification techniques that stretch part of the workpiece according to the experience of skilled workers. However, due to the nature of the aviation parts industry, there are no established methods for modification of product shapes and parts. Studying the modification process would allow for increased productivity, such as shorter working hours, throughout the aviation industry. In this study, a method of predicting residual stress due to frictional heat generated during high-speed machining and applying a tensile force to a model deformed by residual stress was used to modify the product. Our analysis showed that a degree of deformation similar to the measured value was produced, and that the product was modified by applying a tensile load.

Design and experimental structural analysis of a solar powered aircraft wing structure

Structural architecture plays a vital role in the design of solar powered aircraft. Wing analysis is critical as wings experience different loads and stresses. The objective of this work is to explore the use of renewable energy sources in aircraft technology in the form of solar-powered aircraft. The number of solar panels needed for a manned aircraft is determined based on the several solar factors. Thus this paper initially deals with the design of the wing structure for a solar powered two-seater aircraft. Also, the present work experimentally analyses the structural responses of a composite wing panel with and without the solar panel which makes this study significant.

Approach to optimization of composite aircraft wing structure

This paper describes an approach to optimization of composite aircraft wing structure basing on multi-criterion method. Two types of composite wing structures such as two-spar and three-spar ones were considered. The optimal layout of a wing frame was determined by Pareto optimization method basing on three criteria: minimal wing deflection, maximal safety factor and minimal weight. Positions of internal wing frame parts (spars and ribs) were considered as optimization parameters. As a result, an optimal design of a composite spar-type wing was proposed.

Vibration analysis of interply hybrid composite for an aircraft wing structure

Due to the rise in environmental issues the research and development of natural and synthetic fibers have risen exponentially for various industrial applications. Research is going on to develop newer fiber-reinforced plastic composites in order to replace metals and alloys. Due to the flexibility composite materials offer compared to metals there has been many innovations coming up in the aerospace industry. Composite materials due to their most desirable property, the high strength to weight ratio have play a major role in weight reduction, and they used for both structural applications and components of all automobiles and space crafts. With primary focus of aerospace industry being to reduce weight and thereby reducing fuel consumptions. The objective of this project is to design and fabricate a simple airfoil wing skin using hybrid composites and to experimentally study its vibrational behavior. The primary focus of this project is to understand the effect of hybridization on the mechanical properties namely vibrational behavior of composite structures. The composites used are carbon, aramid, basalt and glass fibers. The specimens were fabricated by the simple and most common hand lay-up method. The hybrid configurations fabricated were CGC (carbon/glass/carbon), AGA (aramid/glass/aramid) & BGB (basalt/glass/basalt). Free vibration tests were performed to study their natural frequencies and also to understand their damping characteristics.

Optimization Design of an Aircraft Wing Structure based on Response Surface Method

Wing is the most critical part of an aircraft whose structural weight holds prime importance. It is always desirable to reduce the weight of an aircraft. In this work, a detailed analysis of wing is carried out and results pertaining to stress distribution are recorded. Commercial software ANSYS is used to perform simulations related to stress, strain and displacement distributions. Moreover, the optimization design of an aircraft wing was conducted using design of experiments (DOE) and response surface method (RSM) technique for the reduction of computational cost. The aircraft wing is efficiently optimized by changing thickness under the same loading and flight conditions. Results show that this optimization technique is useful to reduce stresses as well as overall weight of the structure with minor variation in thickness of components.

Multi-objective topology optimization and structural analysis of periodic spaceframe structures

Reduction of structural weight provides significant benefits in many engineering applications. While methods to optimise structural shape and topology of both continuous solids and discrete frame structures have existed for a while, the advent of additive layer manufacturing processes has enabled more complex geometries to be feasible. In this paper, a periodic spaceframe structure is designed for minimum mass and maximum effective flexural and torsional rigidities. A method of parametrising the spaceframe through its constituent unit cells is proposed, and Genetic Algorithm (GA) multi-objective optimisation is used to optimise its topology, size and geometry as a generic structure. The superior performance of the topology optimised periodic spaceframe is highlighted in terms of structural rigidity, large deformation capability, buckling and vibrational modal analysis in compare to equivalent beam structures of identical weight and comparable domain. The results show that the proposed method can effectively generate lightweight substitute structures of great mechanical performance in many beam structures applications, such as: aircraft wing spars. The periodic spaceframe is applied into a conventional aircraft wing structure to demonstrate the possibilities of promoting weight saving in the design of civil aircraft wings.

CNT Reinforced Laminated Composite under In-Plane Tensile Loading: A Finite Element Study

The present study is mainly aimed at investigating the distribution of in-plane stresses of a rectangular plate under localized uniform in-plane tensile loading through finite element analysis. The configuration used in the analysis is analogous to the case of premature failure of stiffened panel due to the termination of a stiffener in aircraft wing structure. In this current work, three different types of materials namely, isotropic, plain woven and transversely isotropic materials are being considered. Aluminium is taken as isotropic; high strength carbon/epoxy is being assigned as plain woven composite and carbon nanotube based hybrid composite is used as transversely isotropic material, due to their wide range of applications in aircraft structures. The effect of different materials on overall axial, transverse and shear stress distributions at different layers of the stiffened composite panels are demonstrated using finite element analyses. Further, the variations of these stresses along axial and transverse directions are also compared for different materials. It can be concluded from the present study that the peak stress developed near the load application zone should be incorporated in the design criteria of such plates to avoid failure.

Surrogate-Assisted Reliability Optimisation of an Aircraft Wing with Static and Dynamic Aeroelastic Constraints

This paper presents a numerical strategy for reliability-based design optimisation of an aircraft wing structure using a surrogate-assisted approach. The design problem is set to minimise aircraft wing mass subject to structural and aeroelastic constraints, while design variables are structural dimensions. The problem has uncertainties in the material properties. The Kriging model is used for estimating the values of design functions. Two strategies of sampling technique are used, i.e., optimum Latin hypercube sampling (OLHS) with and without infill sampling. Uncertainty quantification is achieved by means of optimum normal distribution Latin hypercube sampling. The original design problem is converted to be a multiobjective optimisation problem. Optimum results show that OLHS with infill sampling gives a more accurate surrogate model; however, OLHS without infill sampling results in the better design solutions based on actual function evaluations.

Static and Dynamic Analysis of Aircraft Wing Made by LM 25 and ALSiC Metal Matrix Composite

This paper discusses about the weight reduction in the wing structure that improves the productivity and performance of an aircraft wing. Decrease in the mass of the wings has higher significance compared all other air craft parts Aircraft wing structures are analyzed with LM25 and a metal matrix composite material which is a mix of LM25 and Silicon Carbide (SiC) where in aluminum is the base metal and silicon carbide is added in different weight proportions. By varying silicon carbide percentage in LM25 four types of samples are prepared utilizing stir casting process. The young's modulus, Poisson's ratio and thickness of every sample are determined cautiously by exposing the sample to tensile test and hardness test. By looking at the material properties acquired tentatively ideal level of silicon carbide in aluminum is found. Static basic investigation is completed in ANSYS by contributing the properties of the ideal example which are acquired tentatively. The outcomes acquired from ANSYS for pure AL25 and metal matrix composite (SiC) are compared. By looking at the outcomes it is discovered that composite material has preferred material properties and stresses over LM25.

Normal mode finite element analysis of aerofoil wing structure with different materials

There are a lot of study regarding on the aircraft components. One of the critical components for an aircraft would be the wings. The wing structure of an aircraft is one of the complex structures of a designed aircraft. This paper is about identifying the modal properties which are the mode shape and the corresponding natural frequencies of the aircraft wing structure. The modal properties of the wing structure would be compared for two different materials applied towards the wing structures which are the aluminium alloy AA-7075-T6 and AA-2024-T3 which currently being widely used by the aircrafts. The study for this aircraft wing structure would be using the approach of finite element analysis (FEA) method. The 3D model is design by using SolidWorks. The modal properties are identified with the help of MSC PATRAN and MSC NASTRAN. The results obtained for both materials for 10 mode shapes are compared and it could be observed that AA-7075-T6 are much lower compared to AA-2024-T3. Hence, from the result, AA-7075-T6 is more suitable to be used for the wing structures.

Numerical simulation of water droplet impact test on aircraft wing structure

The three-dimensional simulation is carried out to study the collision dynamics of the water droplets impinging on the aircraft structures at higher velocities. The composite wing made of hybrid fiber of combination, Kevlar-Glass with nanocomposite graphene (5 sheets of kevlar and 3 Sheets of glass). Meanwhile, the fibers are fabricated using vacuum bagging process. In addition to the epoxy, the catalyst and the nanoparticle added to the resin to increase the strength of the laminates. The water droplet model is designed using Smoothed-particle hydrodynamics (SPH) modelling with the aid of Navier Stokes equation. Furthermore, the water is impinged using an elliptical spray nozzle at a constant height of 100m. For feasibility, the small part of the composite wing structure is exposed to the impact of water droplet at different velocity ranges from 0 to 40m/s. Subsequently, the behaviour of the droplet is studied for three various crosswind effects of 15m/s and 25m/s. From the results, it is clear that the stress and strain are depending on the impact velocity of the droplets. On the contrary, the damage is very little which does not cause any deformation or failure of the structure of the airplane. The numerical observations results are in reasonable and acceptable.