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TZID:Asia/Kolkata
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DTSTART:20250101T000000
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250305T140000
DTEND;TZID=Asia/Kolkata:20250305T170000
DTSTAMP:20260430T105755
CREATED:20250305T053106Z
LAST-MODIFIED:20250305T053338Z
UID:10000058-1741183200-1741194000@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg): Numerical Studies on the effect of core metal type and thickness on the mechanical behaviour of fiber metal laminates
DESCRIPTION:Fiber Metal Laminates are materials that combine metal properties with Fiber Reinforced Plastics (FRP) to improve mechanical performance. This research investigates the impact of core metal type and thickness on the tensile and impact behavior of FMLs. Initially two types of FML were modeled: GFML based on GFRP and HFML based on CFRP and GFRP. Numerical simulations were performed to predict FMLs’ behavior under low-velocity impact loading. Results showed that hybridization of CFRP with GFRP increased maximum force but reduced maximum displacement and energy absorption. Studies have shown that GFRP and CFRP layer positioning and thickness along the laminate the can enhance contact force and energy absorption\, but enhances the delamination at material interfaces. The importance of optimal stacking sequences is evident as hybridization also causes enhanced delamination. The study also\, examined the effect of the core metal layer thickness on low-velocity impact behavior of FMLs. It found that adding a thicker aluminum layer to the middle of the laminate improves energy absorption and reduces permanent displacement due to higher plastic dissipation. Laminates with thicker aluminum cores also show superior impact resistance\, making them suitable for impact-prone applications. Initial studies found that the metal layer in the fiber metal laminates plays a dominant role in achieving the desired properties. Hence\, the present study focuses on the role of core metal type and its thickness on the tensile\, low velocity\, and high velocity impact behavior of fiber metal laminates. Aluminum 2024 T3 – GFRP-based FML with a titanium 6Al 4V core layer and Titanium 6Al 4V – GFRP-based FML with an aluminum 2024 T3 core layer are considered to study the effect of the core metal layer and its thickness on the tensile and impact behavior of fiber metal laminates. Tensile simulations were performed for different core metal layers with varying thicknesses ranging from 0.8 mm to 2 mm at the core position of the laminate. The results show that aluminum-based FML with a titanium core improves elastic modulus\, yield strength\, ultimate tensile strength\, and failure strain compared to titanium-based FML with an aluminum core. In addition\, the deep neural network has been used to predict the stress-strain curve of FMLs\, focusing mainly on the thickness of the core metal. The DNN results closely match the FEA results. In continuation\, numerical simulations were carried out to study the effect of the type of core metal and its thickness on the low-velocity impact behavior of fiber metal laminates. The results showed that an increase in the thickness of the titanium core in aluminum-based FMLs reduces the energy absorption capacity and the plastic dissipation energy while increasing the maximum force and displacement ratio. The study shows that titanium as the core layer is recommended when the thickness of the titanium layer is less than the total thickness of the aluminum layer. In addition\, numerical simulations were also carried out to evaluate the influence of the core metal type and its thickness on the high-velocity impact behavior of FMLs. The results indicated that the ballistic velocity increases with increasing thickness of the titanium layer. Laminates with thicker titanium layers showed higher impact resistance and energy absorption. This thesis establishes an approach to tailoring FMLs by describing the relationship of fiber hybridization\, core metal type\, and its thickness to achieve desired FML properties. The findings demonstrate the development of innovative hybrid materials with superior impact resistance\, tensile strength\, and energy absorption\, confirming their suitability for demanding engineering applications. \n  \nSpeaker: Sadananda Megeri   \n  \nResearch Supervisor: Narayana Naik G
URL:https://aero.iisc.ac.in/event/ph-dengg-numerical-studies-on-the-effect-of-core-metal-type-and-thickness-on-the-mechanical-behaviour-of-fiber-metal-laminates/
LOCATION:Online
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/03/SADANANDA.jpg
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250307T110000
DTEND;TZID=Asia/Kolkata:20250307T130000
DTSTAMP:20260430T105755
CREATED:20250304T093656Z
LAST-MODIFIED:20250304T093656Z
UID:10000057-1741345200-1741352400@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg): Studies on Fluid Structure Interactions in Hypersonic Flow
DESCRIPTION:The global thrust towards the development of hypersonic cruise systems for various applications is leading towards slender configurations with lifting and control surfaces which are thin and complaint and face a hypersonic flow. Hypersonic flows are characterized by large flow kinetic energy and momentum\, which manifests into strong shocks\, high temperatures\, and associated effects that can cause coupling between the flow\, structure\, and thermal effects. Therefore\, understanding Fluid-Structure Interactions (FSI) in hypersonic flow gains significance\, and its predictive modelling is necessary to avoid adverse effects in flight. The majority of literature in supersonic and hypersonic FSI  consider low-fidelity modelling using piston theory\, two-dimensional FSI  computations\, and a limited number of experiments on mainly fully clamped flat panels subjected to aerodynamic loads\, including shock-boundary layer interactions at supersonic Mach numbers. Studies on cantilevered panels\, which are template shapes of control surfaces\, at hypersonic Mach numbers are few\, and there is a significant need to obtain experimental data to aid physical understanding\, validate computational tools and methodology and model the hypersonic FSI  phenomena.\n This motivated the study of three different template flat plate experimental models in the hypersonic shock tunnel HST-2 in the Ludwieg  Mode of Operation\, which has 35 ms of test time. The freestream Mach number of M=6.6 is incident upon a) a cantilevered panel placed along the direction of the flow\, b) a cantilevered panel with an impinging shock\, and c) a trapezoidal wing-like shape fixed at the root and placed transverse to the flow. High-speed schlieren imaging and static pressure measurements at specific locations yield information on the flow characteristics. Image tracking methods are used to extract structural deformation\, and accelerometers measure the oscillatory structural response in the presence of hypersonic flow. Complementary two-dimensional numerical simulations in a fully coupled format are conducted for a limited number of cases. Parametric studies are conducted by varying the panel thickness\, angle of attack\, and mass ratio for plain panels and the impinging shock characteristics for the panel with shock impingement. Natural\, free vibration experiments using an impact hammer excitation are first carried out to evaluate the natural structural modal frequencies.\n Great care is taken in designing all experimental models so that the FSI  response can be captured during the short test time. Oscillatory response is captured successfully using the different diagnostic tools.   For a plain cantilevered panel placed at the Angle of Attack of 20 degrees\,  the FSI response is dominantly near the first structural bending mode at a frequency of 89.65 Hz\, which is higher in comparison to the natural frequency of 75.82 Hz. Multiple diagnostic tools and Dynamic Mode  Decomposition analysis confirm these observations. The angle of attack and mass ratio affect the amplitude of oscillations. Varying thickness changes the structural stiffness\, and accordingly\, the oscillations occur at higher frequencies. Higher downstream pressures on the top surface of the panel due to forebody shock first cause the panel to bend away from the flow\, which leads to the formation of expansion fans\,  releasing the pressure and causing the elastic restoring force to bring it back. Complementary two-dimensional FSI simulations showed good agreement with the experiments\, though the magnitude of amplitude was higher due to the 2D nature of the simulation. Shock Boundary Layer  Interaction is significantly affected by the panel’s compliance. There is a 29.6% reduction of the SBLI separation bubble size on a complaint cantilevered panel. The twin effects of a relaxation in pressure gradient and the existence of wall-normal velocities due to a vibrating panel can be attributed to the observed effect. The trapezoidal wing shape exhibited significantly higher magnitudes in the second structural mode.\nThe studies have laid the foundations for deeper investigations using field imaging techniques like 3D-Digital Image Correlation in the future. The experimental database can be used to develop predictive modelling approaches and data-driven modelling.\n\nSpeaker: Ms. Kartika Ahuja \n\nResearch Supervisor: Prof. Srisha Rao M V
URL:https://aero.iisc.ac.in/event/ph-d-engg-studies-on-fluid-structure-interactions-in-hypersonic-flow/
LOCATION:STC Seminar Hall\, Dept. of Aerospace Engineering
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/03/Kartika.jpg
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250312T150000
DTEND;TZID=Asia/Kolkata:20250312T170000
DTSTAMP:20260430T105755
CREATED:20250307T064034Z
LAST-MODIFIED:20250307T064034Z
UID:10000059-1741791600-1741798800@aero.iisc.ac.in
SUMMARY:Ph.D.(Engg) : Multi-Agent Pursuit-Evasion and Coverage Strategies
DESCRIPTION:Autonomous agents are increasingly being used to solve many tasks\, deemed complex by humans\, with ease and effectiveness. Two such applications are in defense scenarios and in coverage. This thesis\, therefore\, is devoted towards study of motion planning strategies for autonomous agents in the context of pursuit-evasion problems as well as different coverage problems. The thesis comprises two parts. In the first part\, pursuit-evasion is considered between an evader and one or more pursuers\, all the agents being non-holonomic having turn radius constraints. A partial information setting is considered wherein the agents (evader and pursuer) know about each others’ speed and position but not about their turning capability. The objective in these problems\, where the pursuer is of higher speed but less agile\, is to obtain an evasive strategy. A two-phase evasive strategy is proposed as an effective solution against the pursuers. It is a proximity based strategy. In the first phase\, when the pursuer is beyond a critical distance from the evader\, the latter assumes the worst that the pursuer is holonomic and solves for the best response strategy. This phase is called the Worst Case Scenario Planning (WCSP). When the evader is within the critical range from the pursuer\, the former attempts sharp maneuvers to sidestep the pursuer and extend time of capture. This phase is called the Proximity Based Maneuver (PBM). Dynamic programming is used to solve for the WCSP strategy. In case of multiple pursuers\, the concept of dominance regions is used to obtain the WCSP strategy. Additionally\, the pursuit-evasion problem is extended to a reach-avoid problem where the evader has the dual objective of avoiding the pursuer and reaching a target. This thesis considers the problem of reaching a moving but non-maneuvering target by a turn radius constrained evader in the shortest time. The evader is modeled as a Dubins vehicle and the reaching strategy is deduced by studying the time-to-go properties for different strategies and chronologically checking simple conditions at crossover points. The proposed two-phase evasive strategy is used for avoiding the pursuer. The reaching strategy and the avoiding strategy are linearly combined to obtain the net reach-avoid strategy. Extensive simulation results are provided to corroborate the effectiveness of both the evasive and the reach-avoid strategies. In the second part of the thesis static and dynamic coverage problems are discussed. Inspiration from flocking principles with substantial modifications is used to design a static coverage strategy. This ensures that the covering agents are spread uniformly around the structure while avoiding collision among themselves and with obstacles in the environment. Coverage is addressed for convex and non-convex shapes in 2D and 3D. For dynamic coverage\, concept of Lissajous curves is used to achieve coverage. Dynamic coverage is split into two chapters: coverage of planar regions and coverage of 3D structures. For planar regions\, the boundary of the region is approximated using Fourier series and radial Lissajous curves are generated within the boundary as reference coverage paths. The optimal field-of-view size is analytically determined along with the upper-bound on the time taken for complete coverage. Various extensions of the strategy such as preferential coverage and simultaneous coverage are also discussed. For 3D structures\, an enclosing volume is considered and Lissajous curves are generated on the surface of the enclosing volume. Conditions for complete coverage as well as collision free coverage in case of multiple agents are determined analytically. Artificial potential fields are used to obtain coverage by conforming to shape of the structure. A variety of enclosing volumes are discussed along with diverse applications such as patch coverage\, waypoint coverage\, and coverage of moving structures. Performance metrics are proposed for both static and dynamic coverage problems that helps in ascertaining the quality of coverage. \n  \nSpeaker : Suryadeep Nath    \nResearch Supervisor: Debasish Ghose
URL:https://aero.iisc.ac.in/event/ph-d-engg-multi-agent-pursuit-evasion-and-coverage-strategies/
LOCATION:STC Seminar Hall\, Dept. of Aerospace Engineering
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/03/SURYADEEP-.jpg
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250313T150000
DTEND;TZID=Asia/Kolkata:20250313T170000
DTSTAMP:20260430T105755
CREATED:20250311T110524Z
LAST-MODIFIED:20250311T110524Z
UID:10000061-1741878000-1741885200@aero.iisc.ac.in
SUMMARY:Ph.D.(Engg) : Effect of Laser Shock Peening on Residual Stress and Mechanical behaviour of Aluminium alloy AA2219 Friction Stir Weld
DESCRIPTION:Aluminium alloy AA2219 is a precipitation hardenable wrought alloy with copper as a major alloying element. Large-volume propellant tanks of space launch vehicles are manufactured by joining AA2219 aluminium alloy through Friction Stir Welding (FSW) and it is designed optimally to improve the payload capability.  An increase in the strength of the FSW joint results in payload improvement of space launch vehicles. Residual stress is one of the crucial parameters for the design of pressure vessels\, and it is also necessary to mitigate or reduce the same to improve structural margins. The main challenge is understanding the cause of residual stress\, its evaluation\, and mitigation due to the FSW process. Laser shock peening (LSP) is one of the most promising surface modification techniques to improve the performance of weld joints. In the LSP process\, a high-energy laser beam impacts the surface of the specimen and generates ionized plasma by evaporating a thin ablative layer on the specimen. When a high-energy laser pulse passes through the transparent layer and hits the sample\, the thin ablative layer is vaporized and continues to absorb the laser energy resulting in the generation of ionized plasma. Rapidly expanding plasma is entrapped between the specimen and the transparent layer\, generating high surface pressure and propagating into the sample as a shock wave. When the peak pressure exceeds the material’s yield strength\, plastic deformation occurs in the specimen.\n\nThe present work aims to investigate the impact of LSP on residual stress\, microhardness\, global tensile behaviour\, tensile behaviour of various zones (local tensile behaviour)\, stress corrosion cracking behaviour and surface roughness of AA2219 T87 FSW. Surface and through-thickness residual stress were investigated in this work. In as-welded conditions\, tensile residual stress exists in the weld region with a peak value of +123.5 MPa in the Thermo-Mechanically Affected Zone (TMAZ). LSP has significantly affected all the regions of the weld and reduced tensile residual stress to compressive. Longitudinal residual stress is non-uniform through thickness as well as across the weld. Peak tensile residual stress is +160 MPa at the centre of the weld in mid-thickness\, and the LSP process led to a 55% reduction.\n\nAA2219 T87 FSW exhibits a yield strength of 197 MPa and an ultimate tensile strength of 348 MPa at ambient temperature. The LSP process increased the yield strength of the FSW joint by 7 – 14%. A similar increase is seen in cryogenic temperatures also. The increase in the yield strength is due to the strain-hardening effect induced by LSP. The response of different zones of FSW to tensile lading and LSP was investigated using the digital image correlation technique. LSP led to an increase in YS in Weld Nugget and TMAZ. However\, HAZ does not exhibit a significant increase in YS. The LSP process led to an increase in microhardness of 7 – 20%. Single-layer peening has affected < 0.5 mm depth\, whereas three and six layers of peening have influenced a depth of 1.0 mm and more than 2 mm\, respectively. Metallographic study of LSP specimen confirms an increase in dislocation density\, which is the cause for the increase in YS and microhardness.  The LSP process has increased surface roughness in all regions of FSW\, and the increase is substantial in the weld nugget and TMAZ regions. The LSP process has not affected stress corrosion cracking resistance\, irrespective of the number of layers of peening.\n\nIn summary\, a systematic investigation of the effect of LSP on AA2219 T87 FSW joint is carried out using various experimental and characterization techniques and the benefits of LSP are clearly brought out. LSP of AA2219 FSW reduces tensile residual stress and increases YS. This study has also quantified the improvement in YS of various zones of AA2219 FSW due to the LSP. An increase in microhardness was also noticed due to LSP. In addition\, resistance to stress corrosion cracking is not compromised due to LSP. This research outcome will be useful in improving the structural safety margin or reducing the inert mass of aerospace structures and pressure vessels.\n\n\nSpeaker : Dhanasekaran M P\n\n\nResearch Supervisor: Prof. D. Roy Mahapatra
URL:https://aero.iisc.ac.in/event/ph-d-engg-effect-of-laser-shock-peening-on-residual-stress-and-mechanical-behaviour-of-aluminium-alloy-aa2219-friction-stir-weld/
LOCATION:Online
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/03/Dhanasekaran.jpg
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250318T110000
DTEND;TZID=Asia/Kolkata:20250318T130000
DTSTAMP:20260430T105755
CREATED:20250311T060827Z
LAST-MODIFIED:20250311T060827Z
UID:10000060-1742295600-1742302800@aero.iisc.ac.in
SUMMARY:Ph.D.(Engg): Investigations on Hypersonic Laminar to Turbulent Boundary Layer Transition in a Shock Tunnel.
DESCRIPTION:The laminar to turbulent boundary layer transition onset has perplexed fluid dynamics community irrespective of the flow regime under which the phenomenon is probed. The complexity of the problem is compounded in high-speed compressible flows where in the transition onset location is a strong function of many subtle factors like freestream quality\, surface roughness\, wall temperature etc. The transitional and turbulent boundary layers bring their typical characteristics\, like an increase in skin friction\, heat transfer\, fluid dynamic parameters fluctuations\, mixing characteristics\, potential to negotiate adverse pressure gradient\, along with them. These typical characteristics of transitional and turbulent boundary layers can be both detrimental and advantageous to a given facet of an aerodynamic vehicle design. Hence the boundary layer transition onset location is one of the key design inputs in the development of aerodynamic vehicles operating in subsonic\, supersonic and hypersonic freestream environment. A plethora of work has been conducted to investigate the transition onset phenomena in supersonic and hypersonic flow regime since the beginning of space age and the inception of the idea of an air breathing hypersonic cruise vehicle. The outcomes of these investigations and studies on high-speed boundary layer transition onset although led to the development of several techniques and correlations to estimate the transition onset location\, applicable usually to a particular test model and freestream condition\, very few studies targeted the characterization of transitional boundary layer in hypersonic flow regime. The earlier and contemporary work on roughness induced transition onset focused on the effect of the said roughness element on transition onset location but the features associated with the instabilities thus generated by these roughness elements have seldom been reported in the open literature. Hence characterization of transitional boundary layer and the instabilities associated with the same was one of the primary objectives of the present work.\nThe present work on hypersonic boundary layer transition was conducted in a shock tunnel HST4 by employing generic test models like flat plate\, cone and elliptic cone. The work began with the design\, development and deployment of a new contoured nozzle\, with a nominal Mach number of 6.0\, for HST4. Before embarking on the boundary layer transition studies\, dedicated efforts were made to characterize the freestream noise environment of the test section of HST4 by employing experimental and numerical methods. A two-dimensional finite difference Navier-Stokes solver was developed in order to numerically compute the transfer functions required to retrieve freestream pressure fluctuations from the experimental measurements. The RMS of pressure fluctuations in the test section of HST4 was found to be 4.32% for the freestream Reynolds number of 4.5 million/m with major contribution of low frequency fluctuations (<50 kHz) towards the aforementioned RMS magnitude. The transitional boundary layer on smooth surface of a flat plate and an axisymmetric cone were characterized by experimentally measuring the intermittency associated with such boundary layers. The intermittent nature of the transitional boundary layer results from the convection of the turbulent spots along the boundary layer. The leading edge and trailing edge velocities associated with these turbulent spots as well as their generation rates were experimentally measured and computed. The second mode instabilities\, a typical characteristic of high Mach number boundary layers\, were also measured in terms of pressure fluctuations and the bandwidth of these instabilities was found to be in the range of 240-480 kHz. The wavelengths associated with these instabilities were found to be 2.5 times the local boundary layer thickness. Transition onset due to the presence of an isolated roughness element\, either a protrusion or a three-dimensional shoe box cavity\, was also investigated as part of the present campaign. Both isolated protrusion and cavity led to an early onset of transition when compared to the smooth test models with no isolated roughness element. In the case of transition onset due to an isolated cubic protrusion\, the Shuttle Orbiter correlations were found to be inadequate in estimating the transition onset and correlations based on the present dataset were formulated. A single frequency oscillation with a narrow bandwidth centered around 23 kHz corresponding to hair pin vortices in the wake of roughness element was found in the present work. It was also found that while the protrusion suppressed the second mode instabilities\, the cavity aided in the development of high frequency instabilities akin to second mode. Finally initial findings of the transition onset due to cross flow instabilities in an elliptic cone were also discussed in the present work. \n  \nSpeaker : Ankit Bajpai \n  \nResearch Supervisor : Prof. Gopalan Jagadeesh
URL:https://aero.iisc.ac.in/event/ph-d-engg-investigations-on-hypersonic-laminar-to-turbulent-boundary-layer-transition-in-a-shock-tunnel/
LOCATION:STC Seminar Hall\, Dept. of Aerospace Engineering
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/03/Ankit-.jpg
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250319T150000
DTEND;TZID=Asia/Kolkata:20250319T170000
DTSTAMP:20260430T105755
CREATED:20250313T105656Z
LAST-MODIFIED:20250326T050053Z
UID:10000063-1742396400-1742403600@aero.iisc.ac.in
SUMMARY:MTech(Res) : Elastic Wave Dispersion Analysis and Mode Shape Investigation of Higher-order Beam Theory for Thick Beams
DESCRIPTION:The dynamic behavior of structural components over broad frequency ranges\, particularly thick beams under different constraints\, is important in many engineering applications where reduced dimensional modeling is required for design. Applications are aerospace structures\, mechanical systems and civil infrastructure. The rigid cross-section assumption in Euler-Bernoulli and even third-order beam theories cannot accurately capture the effects of stress-free or finite surface conditions and higher-order stress distribution under dynamic situations. While some higher-order beam theories satisfy shear stress boundary conditions\, they do not fully account for normal stress. The higher-order beam theory employed in this study addresses these limitations. It satisfies both shear and normal traction conditions simultaneously. Another problem in guided wave behavior within thick beams is accurately modeling consistent surface or interior dynamics. For this\, the transverse displacement is approximated using a trigonometric variation across the thickness\, characterized by a fundamental wave vector consistent with the necessary stress variation throughout the thickness\, which is particularly relevant for thick structures.\n\nThere remains a lack of comprehensive comparison between different reduced-order models\, particularly in terms of their accuracy in predicting wave dispersion characteristics and dynamic deformation mode shapes in the short and long wavelength limits to evaluate the acceptability of specific models in specific applications. Also\, the choice of beam theory directly influences these properties. This study compares four different theories: Euler-Bernoulli\, Timoshenko\, Third-order shear\, and proposed higher-order theory with surface constraints. The dispersion characteristics of each beam theory are obtained by solving the characteristic equations using the polynomial eigenvalue method\, and dispersion curves are plotted to compare wave propagation behavior predicted by different theories. This comparison highlights the limitations of the lower-order theories\, especially in their ability to accurately capture the behavior of thick beams\, and demonstrates how higher-order theory provides improved predictions of wave behavior.\n\nTwo numerical validation techniques are employed to validate and investigate higher-order wave modes present in higher-order beam theory: one is based on the two-dimensional Fast Fourier Transform (2D FFT)\, and the other uses particle displacement vector plots. In the first approach\, a time-varying excitation is applied to the beam with a specific tonal frequency\, and time-domain response data is collected. The 2D FFT is then performed to extract the dominant wave modes. This method generates the flexural and axial modes at 300kHz frequency as an example\, which is better predicted using the higher-order beam theory. In the second approach\, wave motion is visualized as particle trajectories by plotting displacement components along axial and transverse directions. This method enables the generation of pure wave modes by solving the displacement field directly\, eliminating dependencies on boundary conditions and external excitation. This method validates all mode shapes present in the Higher-order beam theory.\n\nIn summary\, this thesis presents a comparative study of various beam theories to highlight the importance of higher-order beam theories where relevant physics needs to be captured. The dynamic effects are relevant in applications in vibrating machinery\, dynamic contact effects\, bearings\, and advanced contact force-based testing like resonance and force microscopy.\n\n\nSpeaker : Kratika Raje\n\nResearch Supervisor: Prof. D. Roy Mahapatra
URL:https://aero.iisc.ac.in/event/mtechres-elastic-wave-dispersion-analysis-and-mode-shape-investigation-of-higher-order-beam-theory-for-thick-beams/
LOCATION:Online
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/03/Kratika-1-1.jpg
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