FBE- Uçak ve Uzay Mühendisliği Lisansüstü Programı - Doktora

Bu koleksiyon için kalıcı URI


Son Başvurular

Şimdi gösteriliyor 1 - 5 / 64
  • Öge
    Deformation behavior of thin walled structures filled with auxetic and non-auxetic core materials
    (Lisansüstü Bilimleri Enstitüsü, 2021) Usta, Fatih ; Türkmen, Halit Süleyman ; Scarpa, Fabrizio ; 670691 ; Uçak ve Uzay Mühendisliği
    Air vehicles can be exposed to structural damages and disable integrity due to static and dynamic loads. Windshields of an airplane, i.e., fuselage or wing surfaces, can have a risk of these loads, and therefore, they should withstand these external loads. The skin shape of the air vehicle components, e.g., fuselage/wing/empennage of airplane and blade/canopy of the helicopter, can be considered as the combination of curved or flat panels. Likewise, thin-walled tubular structures, which can be utilized as the forms of landing gears or frames of aircraft, can possess curved or flat surfaces depending on cross-section types. This thesis proposes to increase the indentation and impact resistance of the air vehicles under low and high-velocity impact loading. The structural durability of the aircraft components under compressive loading has a key role in the protection of structural integrity during accidents. We mainly focus on enhancing mechanical performances of integrated structures, e.g., sandwich panels and thin-walled tubes with auxetic (i.e., negative Poisson's ratio) and non-auxetic core. In particular, we focus on the effects of curvature by examining flat, single, and doubly curved sandwich panels and then curved thin-walled tubes throughout the thesis studies. The results are compared in terms of compressive modulus, strength, and energy absorption metrics. In the first part of this thesis, we develop novel auxetic open cell assemblies to provide high-performance core structures for integrated stuctures. We describe the behavior of a novel class of hierarchical slotted and asymmetrical edge cellular shapes honeycombs with auxetic and non-auxetic configurations subjected to edgewise compression. Hierarchical (slotted) and non-hierarchical specimens, including hexagonal, traditional re-entrant, and asymmetric re-entrant, are produced by the Fused Deposition Modeling (FDM) method, which is the most common method for additive manufacturing. The specimens are 3D printed by using Raise3D N1 3D machine and Polylactic acid (PLA) plastic filament, and then they are tested under edgewise compression along the in-plane directions. The number of cells is determined as 5x4, and dimensions of 122x105x10 mm3 are kept constant for each design. A rigid mass is crushed through the top edge surface at an axial quasi-static speed of 3 mm/min by using an Instron Roell Amsler test machine. An Imetrum Video GaugeTM system is also used to capture the images of the test samples during crushing and to determine the Poisson's ratio of the samples. The material properties of the PLA plastics are determined via tensile tests following the ASTM D638-14 test standard. FE analyses have been performed using the LS-DYNA code to benchmark force-displacement curves with the experimental results. The numerical models are validated by comparing the load-displacement responses with the experimental results for each sample. Linear elastic properties, crashworthiness, and energy absorption capability of the novel honeycomb structures are evaluated from the experimental and numerical standpoint. Specific metrics like normalized compressive modulus, compressive strength, and specific energy absorption (SEA) are evaluated. The Poisson's ratio of the hierarchical honeycomb configurations is compared to the bulk ones. In this section, we also introduce a novel type of composite open cells honeycombs with the PLA plastic reinforcements, hydrogel, and polyurethane foam over a hierarchical cellular platform. The first class is represented by a hybrid architecture combining a hierarchical honeycomb with polyurethane foam filler, while the second is a multiphase structure produced by injecting a sodium alginate hydrogel into the hierarchical voids of the honeycomb metamaterial. The hydrogel formulation consists of sodium alginate (alginate) and a non-ionic surfactant, Pluronic F127. Gel-containing PLA structures are immersed in a 100mM CaCl2 bath prepared by dissolving calcium chloride powder in deionized water. The resulting gel structure is injected into the voids of PLA structures by using syringes. Semi-reticulated polyurethane rigid (PUR) foam blocks (density 69 kg m-3) are processed by using a CNC machine in accordance with the dimensions of gaps in the architectural structures. Then twelve different auxetic and non-auxetic metamaterial architectures are subjected to edgewise compression loading at the same test speed. A parametric numerical analysis is also performed using validated FE models to identify the best metamaterial architecture configurations. Second, we conduct the studies on flat, single, and doubly composite sandwich panels under low and high-velocity impact loading. Sandwich panels are composed of two thin stiff and strong face sheets and a thick lightweight core. The geometrical configuration has a key role to be able to absorb more energy and have more impact resistance. The interface angle, stacking sequence, ply orientation, ply thickness, and material type are the important parameters for manufacturing composite sandwich panels. Here we mainly focus on the effects of different types of auxetic and non-auxetic core structures and curvature of composite panels. In addition, the effects of thickness and stacking sequence of the composite panels are examined, and then an optimization study of the impact behavior of curved plates is performed by using multi-objective optimization techniques. Impact resistance of composite sandwich panels with different types of auxetic (re-entrant, double arrowhead, and hexachiral) and non-auxetic core structures are investigated by using Instron 9340 drop test machine. In the experimental studies, sandwich panels are manufactured with the constituents of UD carbon fiber reinforced epoxy resin (CFRP) composite face sheets and PUR foam core and 3D printed PLA plastic cellular core. Composite face sheets consisting of three plies with the [0/45/90] stacking sequence are manufactured with wet/hand lay-up method. A Heatcon vacuum press test machine is used to cure the epoxy resin and ensure a uniform flatness on both sides of the face sheets. The material properties of the constituents have been determined via tensile and compression tests in accordance with the relevant ASTM test standards. The cellular core topologies are fixed to have the same dimension of wall thickness and number of cells (39x4 except hexachiral topology). A rigid striker with a hemispherical head tip is dropped on the specimens with a speed of 2.6 m/s. A set of numerical analyses with different impact energies are performed using validated FE models to identify the best core design. Then, we indicate how an open cellular core topologies (re-entrant lattice) and a PUR lightweight foam core structures affect the high-velocity impact behavior of the doubly curved CFRP sandwich panels. Composite face sheets are manufactured with the dimensions of 250-mm radius, 30-mm core thickness, and 1.05-mm face sheet thickness by using a doubly curved mould made of aluminum alloy. High-velocity impact tests are carried out by using an air gas gun test machine capable of maximum 40-bar compressed air. Frames and fasteners of the gas gun are renewed considering the connection surface of the specimens. Frames are designed and produced with the same radius of curvature of the sandwich panel. In the experimental studies, a 10-mm diameter spherical steel projectile is launched to the centre of the specimens with a speed of 100 m/s. The FE models are developed by using the LS-DYNA software to simulate the high-velocity impact behavior of the specimens. The strain values measured by using strain gauges are recorded via a data acquisition system. The penetration depth of the projectile is measured by using a digital caliper. Moreover, the effects of curvature on the impact behavior of composite panels are examined by using numerical methods. The doubly curved surfaces are investigated and classified according to the Gaussian curvature coefficient. The impacted surface is extracted from the surfaces of torus, ellipsoids, spheres, and cylinders. We evaluate twelve different doubly and one single curved panels impacted by a spherical projectile at a velocity of 100 m/s. The results are firstly discussed by considering the effects of the curvature on the backplane displacement and the energy absorption of the panels. In addition to these, a multi-optimization study based on the Genetic algorithm and Response Surface method is carried out in order to determine the optimum designs of curved plates under high-velocity impact loading. Third, we conduct the studies on crash tubes subjected to axially quasi-static compression and low-velocity impact loading. Crash tubes are important safety components used as thin-walled structures owing to their lightweight. Here we investigate the effects of filler types, curvature, tube numbers, cross-section, and imperfection on the single and multi-tube systems' crashworthiness performance. Re-entrant and hexagonal configurations are chosen as unit cell shapes of the filler. The numerical studies are conducted using LS-DYNA software. Material properties of tubes made of aluminum alloy and auxetic lattices utilizing Acrylonitrile butadiene styrene (ABS) plus and PLA plastics are determined by using tensile tests according to ASTM E8/E8M and ASTM D638-14 test standards. The effects of imperfection on the tube and using auxetic filler on the crushing behavior of circular crash tubes are examined by using numerical methods. FE analyses are performed at 5 m/s impact velocity. Two different trigger shapes are suggested and compared to each other and discussed the advantages and disadvantages over non-triggered tubes. In order to indicate the effects of auxeticity, circular crash tubes with and without re-entrant lattices are examined under dynamic loads by using experimental and numerical techniques. The tubes in the specified length are cut from the extruded cylindrical aluminum profiles. Then, each specimen is placed in the special grooves on the aluminum plate and bonded using adhesive. Impact tests are conducted by using the Instron Dynatup 8150 test machine. As a special case of integrated thin walled structures, nested tubes are also examined in this section. The effects of using hexagonal honeycomb filler, increasing the numbers of tubes, and changing the lengths of the tubes on the nested tube structures are examined both experimentally and numerically. In the experimental study, a mass is dropped at 2.75 m/s impact velocity onto the multi-tubular crash tubes by a drop test machine. The results of single, double, triple, quadruple, and quintuple tubular structures with and without the honeycomb filler are compared in terms of collapse mechanism and common crashworthiness indicators. Furthermore, the effects of taper angle, imperfection, and cross-section types on the impact behavior of nested tubes are investigated numerically. Lastly, we present a crashworthiness optimization of nested and concentric circular tubes under impact loading which is performed by coupling FE model, Response Surface models, and Genetic algorithm. Length and thickness of three concentric tubes, as well as the radius of one tube, are adopted as design variables, which are effective parameters on crashworthiness and energy absorption. To reduce the computational cost of the optimization procedure, simple and computationally cheap Response Surface models are created to replace FE analyses in further calculations. The Non-dominated Sorting Genetic Algorithm –II (NSGAII) is applied to obtain the Pareto optimal solutions.
  • Öge
    Digital-twin flight modelling through machine learning for trajectory error estimation and recovery
    (Lisansüstü Eğitim Enstitüsü, 2021) Uzun, Mevlüt ; İnalhan, Gökhan ; Demirezen, Mustafa Umut ; 670702 ; Uçak ve Uzay Mühendisliği Ana Bilim Dalı
    High fidelity aircraft performance models are essential for the precise estimations of 4D trajectories and fuel consumption. A correct fuel flow model is critical for flight planning purposes, especially in calculating the fuel load required for a trip. Airlines use manufacturers' performance models to calculate fuel consumption for flight planning rather this be at the integrated operations center or at the cockpit level. As such, within the scope of Air Traffic Management (ATM), for problems such as trajectory planning/estimation for separation assurance and capacity and demand balancing, performance models such as the Base of Aircraft Data (BADA) by Eurocontrol are utilized. These baseline models are structured around polynomial approximations of Original Equipment Manufacturer (OEM) performance tables within generic aircraft models. However, flight data strongly suggest that the aircraft tend to deviate from these baseline models as they age and as, are exposed to maintenance, and are operated in diverse regions. Current ground-based flight planning systems utilize aircraft type-specific performance tables to determine fuel flows for given flight conditions and parameters such as altitude, mass, and speed. A performance factor corrects these tables as the aircraft ages. Despite this update, planned fuel consumption may indeed not overlap with the actual one. In addition to the aircraft performance model, wind uncertainty affects fuel consumption by its impact on ground speed. Because ground speed changes trip time, it determines how much fuel is to be consumed for a travel distance. This thesis focuses on the flight planning at the ground level and propose a data-driven machine learning approach to develop a data-driven aircraft digital-twin model using the most fundamental and airborne recorded flight trajectory and flight parameters data set. In particular, this thesis considers on two distinct problems: uncertainties in aircraft performance models and uncertainties in the wind. In this sense, this thesis proposes methodologies to improve baseline models for fuel flow, and wind estimations via operational data. In particular, this study has investigated introducing neural network architectures to estimate tail-number specific updates to the aircraft baseline fuel flow model through deep learning for climb, cruise, and descent phases of flight. For training our neural network models, this study has utilized a QAR data set from 30 different tail-numbers with more than 2 million flight segments in total from a fleet of a wide-body aircraft operated by a major European flag carrier airline. The proposed architecture is designed to retain the compatibility to the flight planning applications by using the same features that the baseline aircraft models do for computing flight trajectory and the fuel flow. Throughout an extensive feature engineering, the thesis reveals the parameters with a significant impact on fuel flow. The analysis shows that the discrepancy between the modeled and the actual fuel flows stems from a) parametric biases in fuel flows and b) operational variations in the actual implementation of the flight modes. As such, the estimation errors in throttle and the corresponding thrust and excess thrust levels, play a key role in error dynamics. This fact is utilized to further refine the neural network architecture into a novel cascaded structure, which embeds estimation of critic engine related parameters that are not available within baseline models for flight planning. Furthermore, the study has implemented a physics-guided deep neural network framework to improve data-driven models' consistency in flight regimes that are not covered by data. In particular, we guide the neural network with the equations that represent fuel flow dynamics. In addition to the empirical error, we embed this physical knowledge as several extra loss terms. In wind uncertainty part, historical Global Forecast System (GFS) predictions are utilized as baseline estimations. Wind measurements in QAR footprints are considered as ground-truth. State-of-the-art deep learning algorithms are deployed to map baseline estimations for fuel flow and wind to their ground truths. A comparison of the models with real flight data shows that precise estimation of fuel flow with mean absolute errors lower than %0.7 can be achieved at all the flight modes. We further tested these models on different tail numbered aircraft to show the generalization capability of the algorithm. Results on the wind side also show that we can achieve a considerable reduction in wind uncertainty both from a mean error and variance sense. Finally, our fuel flow models are compared with the Airline ground-based planning fuel flow models on the actual flight plans generated by the ground-based system. Total trip fuel comparisons show discrepancies up to %3.5 total fuel loading weight, which will result in potential fuel savings by decreasing the fuel load during take-off for flights with unnecessary excess fuel load. An example of a specific tail-number suggests that for typical operation of 200 long-haul flights per day, yearly savings on the order of 17 million USD can be achieved at current jet fuel prices. This "tail-number specific" performance modeling approach is projected to open considerable frontiers, including further reduction of fuel load safety margins and in-flight update of performance models through machine learning methods.
  • Öge
    High-speed trajectory replanning and trajectory tracking for collision avoidance
    (Fen Bilimleri Enstitüsü, 2021) Hasanzade, Mehmet ; Koyuncu, Emre ; 670701 ; Uçak ve Uzay Mühendisliği
    Not long ago, the operations or the applications requiring high-performance guided and navigation would have required the use of tactical-size unmanned aerial vehicles. The main reason for this was that high-performance algorithms required bigger or heavier avionics with high computing capabilities or reliable communication buses linked with the ground systems. However, with the development of technology, these capabilities can now be achieved in smaller avionics, making it possible on-board for small-size unmanned aerial vehicles. New lightweight sensory systems enabled small unmanned systems to have advanced "situational awareness" and allow them to be capable of performing complex missions. Yet, guidance, navigation, and motion planning methodologies are still mostly "conservative" and "use-case-specific," render the UAVs incapable of performing multipurpose-operations. There are many studies on route planning algorithms for situations where the map of the environment is known. Since these studies can operate in the initial phase of the operation, where a response is not expected to be very fast, it can guide the vehicle from the starting point to the end point safely, which is feasible and safe for the vehicle. However, in cases where unknown obstacles occur which can be sensed by any sensor, replanning of the trajectory is necessary in order to avoid obstacles. It is expected that the algorithms will be able to generate the replanned trajectory since the vehicle has less time to avoid it. Therefore, The time efficiency of the replanning phase is directly related to the speed and the aggressiveness of the trajectory followed by the vehicle. it is crucial to utilize an algorithm that generates an evasive maneuver in real time and ensures safety and dynamical feasibility. In this thesis, studies were carried out on two topics, trajectory replanning and trajectory tracking. The first study, this thesis proposes a fast re-planning strategy based on deep reinforcement learning for highly agile aerial vehicles. First, the differential flatness model of an air vehicle is utilized, allowing us to directly map the desired output trajectory, which is parameterized with b-spline curves, into required input states to track trajectory. Moreover, perception model is used with fixed range and FOV on the vehicle, and as soon as the vehicle detects the obstacle, it performs the real-time evasive action through repetitive re-planning over an infinite trajectory. Specifically, the algorithm is initialized with a flight trajectory plan, then performs optimal control point vector update and knot insertion to generate a dynamically feasible conflict-free trajectory. Through this modification, the regenerated trajectory provides feasible evasive maneuvers for the vehicle, where the location and the number of the added control points form the "agility" of this evasive maneuver. The control point insertion considering dynamic constraints and the defined agility metrics is transformed into a trajectory optimization problem, which is solved through deep reinforcement learning (DRL). The proximal policy optimization (PPO) method is utilized to train the re-planner with the random forest generation environment. The agent produces re-planned dynamically feasible conflict-free trajectories with modified control points approximately in 400us, which enables the real-time flight trajectory generation for highly agile aerial vehicles. The second study proposes a deep reinforcement learning-based trajectory tracking controller, enabling to minimize the positional and velocity track error for aerial vehicles based on a Proximal Policy Optimization (PPO) algorithm where the controller is trained through randomly generated feasible trajectories. PI controller is utilized for the attitude controller and PID for the attitude rate controller as the aerial vehicle's low-level controllers. The trajectory generator based on the dynamic model guarantees the flat outputs, such that they do not exceed the given dynamical limitations of the vehicle, and produces pitch and roll references to the attitude controller. Simulation results show the root mean square error of the trajectory tracking performance. Also, DRL agent performance is compared with LQR and LQI based trajectory tracking controllers.
  • Öge
    Investigation of interacting multiple fatigue cracks propagation using two-dimensional boundary cracklet method
    (Lisansüstü Eğitim Enstitüsü, 2021) Talal, Ahmed ; Türkmen, Halit Süleyman ; Yavuz, Abdulkadir ; 675445 ; Uçak ve Uzay Mühendisliği
    Aircraft structures experience fatigue loading emanating from different sources e.g. variation of aerodynamic loads on wings and repetitive pressurizing and depressurizing the cabin of the aircraft etc. It is a well-known fact that fatigue loading is more responsible for the failure of aircraft structures as compared to static loading because a single surface crack can lead to a catastrophic failure due to fatigue loading. At the early stages of the life of aircraft, these surface cracks have no effect on the structural integrity of the aircraft, but with the passage of time, environmental effect, and nature of loading these cracks propagate and interact with each other. These cracks propagate, up to the point where the remaining cross-section of the component is not being capable of carrying the loads and the component will be subjected to sudden fracture. The failures due to fatigue usually start at small surface cracks which act as local stress raisers and propagate and interact with each other and turn into large damage-producing cracks. In practice, these micro surface cracks are always likely to be present in many aircraft structural components even the newly made components can have these cracks due to certain imperfections in machining processes during the manufacturing of aircraft. To produce a damage tolerance design and to meet the certain requirements of certifications applicable in the aerospace industry, it becomes very important to know the behaviour of aerospace structures in the presence of these inevitable surface cracks under fatigue loading. Thus, a fast and accurate method of predicting the behaviour of these cracks under fatigue loading plays a vital role. This fact forces engineers to develop new methods and models which can simulate the effects of existing cracks so that they can predict the remaining useful life of aircraft structure more accurately. Such methods and simulation techniques not only reduce the high cost of physical testing of the aerospace structures but also play a crucial role in producing a better design of these structures. For the analysis of planar cracks, different commercial tools are available, which are mostly based on the analytical formulations and different handbook solutions e.g. NASGRO and AFGROW. These software packages can simulate the fatigue crack growth (FCG) problems of predefined cracks under mode-I loading conditions only, but most of the real problems in the industry are under the influence of mix mode loading where crack tip grows under the effect of both mode-I and mode-II loading conditions. Therefore, these software packages cannot handle such complex problems of mix mode crack growth. Finite element methods are also being used from a long time for the study of FCG. These methods can simulate the interactions of cracks with reasonably good accuracy. But, due to the requirement of fine mesh at the crack tip, generation of a representation of the crack advancement and regeneration of FE mesh after each iteration of FCG, make these methods challenging to adopt. To overcome these difficulties of FEM, in 1999, a mesh-independent method called Extended-FEM (XFEM) with minimal re-meshing was developed and since then a continuous improvement has been seen in the implementation of these methods. However, the accuracy of these methods decreases as the complexity of the problem increases and still a lot of research efforts are underway to overcome this shortcoming. By considering the above-mentioned limitations of the conventional methods to analyse the FCG of problems involving multiple cracks under mixed-mode conditions, there is always room to develop such methods which can mitigate the deficiencies of these methods. Recently, in 2006, a fast and accurate semi-analytical method called Boundary Cracklet Method (BCM) is developed by Prof. Dr. A. K. Yavuz (co-advisor of this study) and Prof. Dr. S. L. Phoenix at Cornell University, to find the overall stress field and the stress intensity factor (SIF) for crack tips and crack singular wedges at the crack kinks. This method is based on the dislocation distribution approach which approximates the crack opening displacement profiles by using certain power series that satisfy the traction-free condition on crack faces. Unlike the conventional mesh dependent methods, where a very fine mesh is required to overcome the stress singularities around crack tips, BCM takes care of crack tip singularities by including wedge eigenvalues in power series and makes sure that all integrals necessary to calculate stress fields are in closed form to give fast solutions. The solution of these integrals is the most time-consuming part in other mesh-dependent methods such as FEMs and BEMs. Moreover, only a few numbers of allocation points are used around the crack tips to satisfy traction-free boundary conditions instead of using more elements. These factors make the algorithm of BCM more reliable and fast as compared to other methods and enable us to solve difficult fatigue crack growth problems. Therefore, the main objective of this thesis is to analyse the multiple cracks interaction under mix mode fatigue loading by using BCM in the two-dimensional domain and to show the accuracy and versatility of the method to different fatigue crack growth problems that are difficult to solve by using the conventional methods. Throughout the thesis, it has been proved that the proposed scheme is a reliable and accurate method to simulate the fatigue crack propagation (FCP) involving multiple cracks in complex plate geometries under different conditions of fatigue loading. The accuracy of the method is established through the results presented by different researchers which were already available in the literature. Crack tip SIFs, fatigue crack propagation paths and the number of loading cycles required to produce a given crack length extension are used as a parameter for the comparison. A good agreement among the results of each mentioned parameter is achieved for every problem. Further, this proposed method is used to simulate the FCP in different plate geometries involving single as well as multiple cracks under different conditions of fatigue loading which are typical and difficult problems to solve in aerospace structural components. For this purpose, three different studies are conducted, and the findings of each study are published in different international prestigious forums. In the first study, fatigue crack growth in an infinite plate having two rivet holes separated at some distance and crack emanating from a certain location and orientation from one hole are analyzed under three different far-field fatigue loadings i.e. loading in X-direction, loading in Y- direction and shear loading. The maximum tangential stress (MTS) criterion is used to predict the trajectories of crack growth. Paris's Law along with the approach of equivalent stress intensity factor is used to compute the number of loading cycles to produce a required crack length. It is concluded that after some initial number of loading cycles, the fatigue crack growth path becomes perpendicular to the direction of applied loading in case of far-field applied tensile stress (whether in X or Y direction), and similarly, in the case of shear loading, cracks propagate perpendicular to the direction of maximum principal stress. Almost ten times fewer loading cycles are required to reach at a certain crack size under shear loading as compared to the normal applied stress, which shows that the rate of crack propagation is ten times higher under shear stress. Therefore, among the given three loading conditions, cycling shear stress is the worst one and needs more attention while designing the structures having rivet holes. In the second study, fatigue crack growth simulations of interacting multiple cracks in perforated plates with multiple holes are discussed. To show the versatility of the proposed method, emphasis is given to study such complicated problems which cannot be solved by conventional methods to analyse the FCG. Three different studies with multiple cases of initial cracks emanating from side edges, the center of the plate and the outer periphery of holes in the plate at different orientations are simulated. It has been concluded that the FCG of complicated problems e.g. plate with six holes having seven pre-cracks can be computed fast by the proposed scheme. The conventional methods of analysing FCG have limitations in solving such complex problems. Moreover, the effect of a newly added crack in the vicinity of already present crack is also analyzed and concluded that when two coplanar cracks approach each other, they exhibit an over-constraining phenomenon, which causes the near-tip stress field to be significantly higher than that near a single crack and hence ultimately increases the rate of crack growth. To show the efficiency of a computational method in fatigue problems a new and very useful parameter is also introduced: Yavuz's fatigue computational efficiency factor, YCF = µN/t, which is the number of computed million loading cycles per hour (CPU time). In the third study, FCG behaviour of symmetric cracks emanating at different locations at the outer periphery of the hole in an infinite plate with different orientations under in-phase tension-tension biaxial loading is presented. As the effects of initial crack orientation under uniaxial fatigue loading are well reported in the literature but the same under the effect of different conditions of biaxial loading has not been investigated. The rate of FCG is computed using Walker's equation, whereas the direction of propagation of crack tip is predicted using the minimum strain density (MSED) criterion. Our results show that BCM is equally effective in predicting the FCG behaviour under complex cases of fatigue loading. It is concluded that cracks tend to propagate perpendicular to the direction of dominant stress in the case of biaxial load where biaxiality ratio λ≠1 and there is no effect of location and orientation of initial crack on the crack trajectory. For equibiaxial loading where λ = 1, the crack tends to propagate diagonally, and its path depends upon the location and orientation of the initial pre-crack. As far as the number of loading cycles for a given crack extension are concerned, equal load cycles are computed for λ = 0, 0.5, 1 whereas it is concluded that for λ = 1.5, the rate of crack growth increases, and fewer loading cycles are required to produce the given crack length. It is also concluded that there is no change in crack trajectories under different stress ratios (R). For a given effective stress intensity factor (ΔKeff) the rate of crack propagation is increased with the increase in R, but for a given value of stress, the value of ΔKeff is lower for a higher R-value, which results in a higher number of required loading cycles to produce the same crack extension.
  • Öge
    Numerical and experimental investigation on the crushing behaviour of auxetic lattice cells produced with additive manufacturing techniques
    ( 2020) Günaydın, Kadir ; Türkmen, Halit Süleyman ; Grande, Antonio Mattia ; 635490 ; Uçak ve Uzay Mühendisliği Ana Bilim Dalı
    In aerospace, automotive, marine, and military applications, low-density lightweight structures such as sandwich structures and filling materials have an important role in crashworthy applications due to their crush resistance during impact and blast situations. Large deformation can occur during the impact, blast and crush events; therefore sandwich structures and sacrificial crash tubes can bottom out and very high peak load can rise. For preventing this phenomenon, auxetic materials have drawn attention as a core and filling material due to their negative Poisson's ratio (NPR) specification, which provides lateral expansion under tensile loads and shrinkage under compressive loads. The purpose of this study is to examine the energy absorption characteristics of additively manufactured polymer and metal 2D auxetic lattice cells, in the edgewise direction where auxeticity can be experienced, subjected to axial quasi-static loads. Total mass and volume of lattice cell structures are kept almost equal for better comparison. % In the work presented in this dissertation, additive manufacturing (AM) is used to produce auxetic lattice structures. AM is an improved method for quick and complex productions, and layered manufacturing is the most common method for AM; aiming the design verification, visualization, and kinematic functionality testing. AM is a computer-controlled manufacturing method of needed parts which are directly transferred as a solid model from the computer. It is a very sufficient and proved way to reduce the time for product development. There are several methods for AM, which are selective laser sintering (SLS), electron beam melting (EBM), fused deposition modelling (FDM) and stereolithography (SLA). FDM is used in this study because of its device and consumption material are cheaper compared to other mentioned methods. On the contrary of advantages of FDM method, there are some uncontrollable production problems to be solved such as incomplete bottom layers, hanging strands, missing walls, pillowing, shifted layers, unfinished parts, delamination of layers, warping syndrome, burn marks and irregular walls. In this study, FDM production problems are listed and investigated. Furthermore, solution approaches are presented to prevent those production flaws. Zortrax M200 3D printing device and Acrylonitrile butadiene styrene (ABS) are used in this study. NX 12: Siemens PLM Software is used for designing the representation of a solid model then it is converted to a stereolithography (STL) file. The converted file is then imported to the machine software of Zortrax which is called Z-Suite. For the FDM productions, production variables are defined as high quality, maximum infill, normal seam, and no support usage. Different layer thicknesses of the productions are assigned as 0.09, 0.14, 0.19, 0.29 and 0.39 mm. Several specimens in each group are manufactured to determine the effect of the layer thickness on the tensile properties. As a result, stress-strain graphs are obtained, and the effect of printing options to mechanical properties are investigated to define the feasible layer thickness for producing structures. Consequently, it is understood that ABS is not enough ductile to maintain the auxeticity of the structures for a certain period. Thus, electron beam melting (EBM) is used in this study. It is one of the promising and sophisticated AM techniques that uses an electron beam to melt metallic powders. Titanium alloy (Ti6Al4V) is used by the reason of its outstanding mechanical properties of high specific strength, high corrosion resistance, excellent biocompatibility; hence titanium alloys are prominent material for aerospace and bioengineering fields. ARCAM EBM A2 3D printing machine and ARCAM Ti6Al4V ELI, which is a gas atomized prealloyed powder in a size range of 45-100 $\mu$m, are used in this study. To understand the mechanical behaviour and characterize EBM printed parts tensile tests are conducted. Each test specimens are produced in three different directions, 0, 45 and 90 due to characteristic anisotropic behaviour of EBM printed parts. Moreover, a study on the effect of inner defects, which are detected as the lack of fusion, in the EBM printed parts is conducted to define the mechanical performance of EBM printed components. The area of defect regions are observed using a scanning electron microscope and measured to investigate the defect area effect to mechanical performance. As a result, EBM printed Ti6Al4V parts experiences isotropic elasticity and yield stress, however, strain at break specifications show substantial differences according to build orientation which is dominated by the lack of fusion (LOF) problems. As an output, it is understood that the increase in the LOF region shows an almost linear decreases pattern with the strain at break value. Furthermore, firstly a comparative study with re-entrant and anti-tetrachiral auxetic is conducted to define the better auxeticity mechanism for 2D auxetic lattices. However, anti-tetrachiral auxetic structures show greater results than the re-entrant auxetic structures and, a modification for the re-entrant structure is needed to increase its energy absorption ability. Besides, another 2D auxeticity mechanism, which is called rotating rigid auxeticity, exists, however, this type of structure is not feasible for crushing applications due to bulky parts in the structure so it is not counted in this study. A comparative compression investigation of anti-tetrachiral and modified re-entrant lattices is conducted in-plane direction using experimental and numerical analyses. Lattice structures are manufactured using FDM 3D printing technology and crushed at the quasi-static condition. Non-linear finite element (FE) models of both structures are established, and the FE results are systematically compared with the experimental results. The onset of densification phases of both structures is determined numerically. Results indicate that deformation modes strongly affect the force-deflection response of both designs. In this manner, failure regions and buckling deformation in the tests are identified to find a relation with theory and to modify geometries. The anti-tetrachiral design exhibits higher specific energy absorption than modified re-entrant hexagonal lattices. Beyond the auxetic characteristics, deformation mechanism of the anti-tetrachiral lattices provides an opportunity to construct excellent crush absorption in-plane direction thanks to its high shear strength stem from its unique deformation mechanism. After having the validated constitutive equation for FDM printed ABS, a benchmark test is conducted using ABAQUS commercial finite element method (FEM) software to evaluate and define the energy absorption effective chiral mechanism among hexachiral, trichiral, anti-trichiral, tetrachiral, anti-tetrachiral and regular hexagonal topologies. As a result, hexachiral (chiral) auxetic lattice is selected, and a part of the study is devoted to the understanding of the energy absorption characteristics of filled chiral auxetic lattices cylindrical composite tubes subjected to a uniaxial and lateral quasi-static load. The lattice structures are manufactured using an FDM 3D printing technique and ABS material. Composite tubes without filling material are initially subjected to uniaxial and lateral quasi-static crushing loads at a rate of 10 mm/min. The same types of experiment are then performed on chiral lattices and chiral lattices filled composite tubes. For the different cases, the load-displacements curves are analyzed and the specific energy absorption (SEA) values are compared. The SEA capability for the axial quasi-static crushing of the chiral lattices filled composite tubes reach 43 J/kg with a 45\% decrease in comparison with the hollow composite design. On the contrary – and quite remarkably - the average SEA value in the case of lateral loading is 2.36 J/kg, with a 450\% increase in comparison with the hollow composite configuration.% Finally, chiral auxetic unit cell structures are produced from Titanium Alloy (Ti6Al4V) metallic powder using Electron Beam Melting (EBM) additive manufacturing technology. EBM printed chiral auxetic lattices are compressed with a three steps cyclic load profile in the edgewise direction numerically and experimentally. Also, a crush study is performed numerically and experimentally to evaluate the energy absorption ability of EBM printed metallic chiral lattice cells. For material characterization and understanding the material behaviour of EBM printed parts tensile and three-point flexural tests are conducted. Tensile and bending specimens are produced in two different thicknesses and orientations. Moreover, a surface roughness study is conducted due to high surface roughness of EBM printed parts, and an equation is offered to define load-carrying effective area for preventing cross-section measurement mistakes. In compliance with the equation and tensile test products, a constitutive equation is formed and used in the numerical analyses after selection and calibration process. The constitutive equation is verified by the comparison of experimental and numerical three-point bending test results. Furthermore, a compressive load profile is applicated to the EBM printed chiral lattice unit cells with two different thicknesses to track their Poisson's ratio variation, and displacement limit under large displacements without the formation of degradation, permanent deformations and failures. The utilization of a finite element code to verify a numerical model for optimum topology design and mechanical performance forecast, the same scenarios investigated in the compressive load profile experiments are then evaluated using non-linear computational models. In the computational models, a Fortran subroutine is used to define the load and displacement controls. In addition, in the numerical crush analysis, auxetic lattice cells are crushed between two rigid plates using damage and failure criteria for simulating failures. As a result, it is revealed that the thickness of the chiral lattice cells is the dominating parameter about its stiffness and auxeticity. Increase in the chiral node radius to thickness rate of 0.15 to 0.30 causes loss of auxetic behaviour. Lastly, their compression behaviours are compared, and the one showing auxeticity presents better energy absorption ability in terms of crush force efficiency, however, considering specific energy absorption value the results show the opposite.