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DTSTART:20240101T000000
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20251113T110000
DTEND;TZID=Asia/Kolkata:20251113T130000
DTSTAMP:20260505T232957
CREATED:20251112T061505Z
LAST-MODIFIED:20251112T061505Z
UID:10000094-1763031600-1763038800@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg): Aerodynamic Shape Optimization of Low Observable Air Intake Duct : A Gerlach Inspiration
DESCRIPTION:Air intake system supplying air to the aircraft’s propulsion system is an important part of the aircraft. In modern military aircraft\, air intake ducts are bent due to stealth and layout considerations. Due to significant contribution from rotating jet engine components to Radar Cross Section\, need to inhibit direct line of sight of the Engine Face from RADAR’s eye is required and this leads to aggressively turning ducts. Owing to large pressure loss happening due to the secondary flows and consequent flow separation arising out of centrifugal forces or its gradients during flow turns\, total pressure recovery at Engine Face is likely to suffer. This thesis addresses this concern\, specifically for a top mounted serpentine intake duct of flying wing configuration.\n\nA shaping technique called “Gerlach Shaping” proposed by C. R. Gerlach and E. C. Shroeder to minimise secondary flows and subsequent losses forms the core of this thesis. An important feature of the shaping concept is the use of ideal flow assumptions for a flow known to be viscosity driven. As a part of the current research\, formulation and implementation of Gerlach shaping is subject to detailed analysis. Gerlach shaping principles are extended\, opening further possibilities for low loss bend designs. Radial pressure gradients and secondary flow mixing are managed more efficiently leading to smooth flow with reduced flow separation and pressure drops. Superiority of newer designs called “Gerlach Inspired Bend Designs” are proven on a square elbow and RAE M 2129 S-duct. It may be surprising to note that the losses encountered in one of the 90◦ bend designs is even lower than that of a straight duct.\n\nA new methodology called “Gerlach Inspired Duct Optimization” for aerodynamic shape optimization of low observable air intake duct design driven by conflicting aerodynamics and stealth requirements is developed. Understanding of Gerlach shaping principles gained during the evolution of design methodology for low loss bends is a stepping stone to the optimization process. Keeping the spirit of Gerlach Shaping alive\, the highlight of this process is the use of low fidelity inviscid CFD tool for a problem considered to be highly viscous. The step is crucial as integrating CFD simulations with Gerlach Shaping as against ideal flow assumptions would considerably improve the accuracy of the flow field description and enhance the duct design. Moreover\, integration of an inviscid solver facilitates robust\, fast generation of flow field and a large number of candidate designs could be analysed. A completely automated Genetic Algorithm based optimization framework integrated with Computational Fluid Dynamics simulations to realize this methodology inspired by\nGerlach Shaping gives substantial performance enhancement as compared to Reference Duct (designed using conventional design methodology) and Gerlach Duct (generated by morphing the reference duct as per Gerlach shaping).\n\nSpeaker : V Valliammai\n\nResearch Supervisor : N. Balakrishnan
URL:https://aero.iisc.ac.in/event/ph-d-engg-aerodynamic-shape-optimization-of-low-observable-air-intake-duct-a-gerlach-inspiration/
LOCATION:Online
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/11/v.jpg
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20251110T160000
DTEND;TZID=Asia/Kolkata:20251110T170000
DTSTAMP:20260505T232957
CREATED:20251107T053302Z
LAST-MODIFIED:20251107T053440Z
UID:10000093-1762790400-1762794000@aero.iisc.ac.in
SUMMARY:From Shock to Shield: Designing Materials for Space\, Defense\, and Beyond
DESCRIPTION:The next frontier of materials innovation lies in designing systems that not only survive but thrive under harsh environments. From hypersonic vehicles and next-generation defense systems to lunar construction and in-space manufacturing\, the demand for ultra-lightweight\, high-strength\, and resilient materials has never been greater. Yet\, our ability to understand and design materials that endure such conditions remains limited by slow\, expensive testing and computationally intensive models ultimately leading to a lack of physical understanding of mechanical response. In particular\, data describing how materials deform and fail under ultra-high strain-rate loading conditions which are typical of aerospace and defense structures—are exceptionally scarce. As a result\, materials development has relied on costly\, well-established systems; but the emergence of commercial space and reusable aerospace structures now demands a new generation of high-fidelity insights into material behavior under dynamic extremes.\n\nIn this talk\, I will introduce a new data intensive high-throughput experimental framework for probing material behavior under extreme dynamic loading. At its core is an automated laser-driven micro-plate impact platform that enables rapid\, cost-effective measurement of key material properties under shock loading. For the purpose of this talk we will in particular look at the Hugoniot Elastic Limit (the onset of plasticity under uniaxial strain loading) and spall strength (the threshold for dynamic fracture) of metals\, when subjected to ultra-high strain rate impacts (10^6 to  10^7 /s). Traditionally\, these properties required large-scale\, single-shot experiments; this new approach achieves them with statistical richness and precision\, dramatically accelerating the rate of materials discovery for extreme environments. Using this dataset\, I will discuss how loading kinetics\, microstructure\, and composition govern material performance\, and how transforming a data-scarce field into a data-rich one enables AI-driven approaches such as active learning and Bayesian optimization for autonomous extreme-mechanics experimentation.\n\nLooking ahead\, integrating this data-rich experimental capability with AI-driven modeling and automation opens a pathway toward physics-informed design principles for lightweight alloys\, ceramics\, and architected composites. In the near term\, this framework will shorten material certification cycles for hypersonics and spacecraft\, rapidly and cheaply explore a wide range of potential materials solutions; in the long term\, it will enable data-driven design of resilient materials for aerospace\, defense\, energy applications and beyond. By uniting experimental mechanics\, data science\, and materials design\, this work lays the foundation for a new era of adaptive\, high-performance materials engineered for extremes.\n\nSpeaker : Dr. Piyush Wanchoo\n\n\nBiography:\nDr. Piyush Wanchoo is a Postdoctoral Fellow at Johns Hopkins University’s Hopkins Extreme Materials Institute (HEMI). His research focuses on understanding how materials behave under extreme conditions such as shock\, impact\, and blast loading. He develops high-\nthroughput\, AI-integrated experimental platforms that enable rapid\, data-driven discovery of material solutions for aerospace\, defense\, and space applications.
URL:https://aero.iisc.ac.in/event/from-shock-to-shield-designing-materials-for-space-defense-and-beyond/
LOCATION:Online
CATEGORIES:AE Seminar
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/11/Piyush.jpg
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250429T170000
DTEND;TZID=Asia/Kolkata:20250429T183000
DTSTAMP:20260505T232957
CREATED:20250424T044437Z
LAST-MODIFIED:20250424T044437Z
UID:10000072-1745946000-1745951400@aero.iisc.ac.in
SUMMARY:Eulerian-Lagrangian Modeling of Flash-boiling Injection Processes in Internal Combustion Engines
DESCRIPTION:Reducing greenhouse gas emissions from the transportation sector\, especially carbon dioxide\, is one of the main global challenges to achieve a more sustainable future. Developing internal combustion engines with advanced injection and combustion concepts that improve efficiency and decrease pollutant emissions are essential steps towards reducing their environmental impact. Over the past decades\, flash-boiling injection has become a promising alternative to generate a much finer spray compared to high-pressure injection. The rapid phase-change phenomenon during flash-boiling injection occurs due to the superheating of the liquid fuel upon entering the combustion chamber\, resulting in tiny droplets due to the abrupt disintegration of the liquid jet\, which in turn enhances the mixture homogeneity between air and fuel by increasing the vaporization rate\, widening the spray plume due to the increased radial expansion via bubble growth\, and reducing the droplet velocities\, thus leading to shorter penetrations. A detailed understanding of the underlying mechanisms of the flash-boiling process\, such as nucleation of vapor bubbles\, bubble growth\, and finally jet burst\, at a microscopic droplet level is necessary to accurately quantify its effect on the macroscopic spray structure. In this talk\, I will first discuss the modeling of single-droplet flash-boiling behavior using a Lagrangian particle tracking (LPT) technique. Following this\, a novel reduced-order Lagrangian model will be introduced to accurately capture the vapor bubble growth in superheated microdroplets\, accounting for interaction among multiple bubbles. Next\, a simplified nondimensional semi-analytical solution for bubble growth\, based on dimensional analysis of the modified Rayleigh-Plesset equation\, will be presented. This solution offers accurate predictions of bubble growth considering bubble interactions using larger time step sizes\, making it effective for simulating large-scale superheated sprays with numerous droplets under varied conditions. Finally\, a three-dimensional two-way coupled large-eddy simulation of superheated spray case will be discussed\, incorporating the newly developed bubble growth model within the LPT framework. \nSpeaker : Dr. Avijit Saha \nBiography: \nDr.-Ing. Avijit Saha is a postdoctoral researcher at the Center for Aeromechanics Research\, Department of Aerospace Engineering and Engineering Mechanics\, The University of Texas at Austin\, USA. His current research primarily focuses on terahertz time-domain spectroscopy (THz-TDS) for the characterization of plasma properties\, including electron density and collision frequency. In addition to his experimental work\, he is developing a novel Bayesian framework for quantifying uncertainties in measurement data\, with the goal of enhancing the reliability and interpretability of spectroscopic diagnostics. He obtained his Ph.D. in Mechanical Engineering from RWTH Aachen University in September 2023\, making him the youngest individual to receive the doctorate degree from ITV. His dissertation focused on the physics based reduced-order modeling of flash-boiling injection processes in internal combustion engines. Prior to this\, he completed his B.Tech. (Hons.) and M.Tech. in Aerospace Engineering from IIT Kharagpur. He was the first recipient of the distinguished ASME IGTI Student Scholarship in the Aerospace department. His research interests span experimental fluid dynamics\, optical diagnostics\, multiphase flow modeling (DNS\, LES\, reduced-order models)\, combustion instabilities\, high-performance computing\, and their applications in aerospace propulsion systems. He has authored numerous publications in leading international journals and conferences\, earning recognition through several prestigious awards. Among his accolades are the Jang Young Sil Post-doctoral Research Fellowship from Korea Advanced Institute of Science & Technology (KAIST) in 2024\, Post-doctoral fellowship from MIT in 2025\, and his role as Principal Investigator for a high-impact compute-time research project under National High-Performance Computing Center for Computational Engineering Science (NHR4CES)\, Germany. Dr. Saha also serves as a reviewer for several notable journals like Nuclear Technology\, Physics of Fluids\, Proceedings of Combustion Institute\, Atomization and Sprays\, and SAE International Journals.
URL:https://aero.iisc.ac.in/event/eulerian-lagrangian-modeling-of-flash-boiling-injection-processes-in-internal-combustion-engines/
LOCATION:Online
CATEGORIES:AE Seminar
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/04/Avijit-.jpg
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250423T100000
DTEND;TZID=Asia/Kolkata:20250423T130000
DTSTAMP:20260505T232957
CREATED:20250422T055303Z
LAST-MODIFIED:20250422T055303Z
UID:10000071-1745402400-1745413200@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg): Navigation of Autonomous Vehicles using Event Cameras and Modified RRT Methods
DESCRIPTION:Autonomous vehicles\, such as unmanned aerial vehicles (UAVs) and autonomous mobile robots (AMRs)\, are at the forefront of technological innovation and are widely used across various applications. As these vehicles become more agile and operate primarily in unstructured environments\, the components of the navigation pipeline must function in real time while optimizing limited onboard computing and memory resources. The challenges faced by a fast-moving vehicle in indoor environments differ significantly from those encountered by outdoor systems. This thesis focuses on autonomous vehicles operating in indoor\, GPS-denied\, and unstructured environments. The algorithms presented address these specific challenges and contribute to the growing body of research on real-time navigation solutions for such scenarios. In this thesis\, we have investigated and addressed various aspects of the autonomous vehicle navigation pipeline. A key focus throughout the work is ensuring real-time performance on edge computing systems. Inspired by the emergence of bio-inspired event cameras\, which offer potential solutions to the limitations of current state-of-the-art algorithms\, the first part of the thesis explores the use of these sensors for perception tasks such as localization and obstacle avoidance. Event cameras provide several advantages\, including motion blur-free data output\, a high dynamic range\, and enhanced low-light sensitivity. These features make them particularly suitable for improving Visual-Inertial Odometry (VIO) systems over traditional frame-based cameras. However\, the sparse and asynchronous nature of event data poses challenges for conventional computer vision algorithms. Existing approaches often convert event streams into image-like representations\, limiting the full potential of event cameras. To overcome these challenges\, asynchronous (data-driven) methods are essential for event-camera-based VIO solutions. The work here introduces an end-to-end data-driven event camera-based Visual-Inertial Odometry (AeVIO) algorithm that updates the system state based on camera velocity. The algorithm performs event feature detection and tracking asynchronously from the event stream and integrates these measurements with IMU data using a structureless Extended Kalman Filter (EKF) to refine state estimates. Given that the data rate of event cameras depends on the scene texture and the relative motion between the object and the camera\, we also explore their application for high-speed obstacle avoidance. Time-to-contact (TTC) is a critical measure estimating the time before collision if the current motion remains unchanged. While event cameras excel at capturing small\, rapid changes\, they lack the detailed scene information that depth cameras provide. We present a novel approach to fuse the low temporal resolution data from a depth camera with the high-speed output of an event camera to compute TTC with obstacles. The proposed algorithm is integrated into the AirSim simulator and evaluated across various dynamic obstacle scenarios\, demonstrating its effectiveness in collision avoidance. The second part of this thesis focuses on the path planning component of the autonomous navigation pipeline. Effective navigation for AMRs and UAVs requires advanced path planning that accounts for kinematic constraints and enables smooth trajectory execution in complex\, cluttered environments. We investigate a probabilistic framework based on the Rapidly Exploring Random Tree (RRT) algorithm\, which incorporates vehicle kinematics to identify the most likely direction for the next node generation. This approach utilizes Gaussian Mixture Models (GMMs) to improve node generation efficiency while addressing optimization challenges in both 2D and 3D spaces. This acts as dynamic bias in the algorithm. Additionally\, we introduce a next-node selection heuristic that directs the search tree expansion toward the goal while avoiding obstacles. To enhance convergence\, we explore methods to discretize both the action and search spaces. Initially\, the method is applied to AMRs and is subsequently extended to the more complex task of 3D path planning for UAVs. In summary\, this thesis contributes to the navigation pipeline by developing simple\, computationally efficient algorithms that leverage event sensors and probabilistic methods. These algorithms are designed to operate in real-time on modern UAVs and AMRs while preserving their agility\, enabling operation in indoor GPS-denied environments\, and accommodating limited onboard computing resources. \n  \nSpeaker: Ankit Gupta \nResearch Supervisor: Debasish Ghose
URL:https://aero.iisc.ac.in/event/ph-d-engg-navigation-of-autonomous-vehicles-using-event-cameras-and-modified-rrt-methods/
LOCATION:Online
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/04/Ankit-.jpg
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250416T150000
DTEND;TZID=Asia/Kolkata:20250416T170000
DTSTAMP:20260505T232957
CREATED:20250407T063952Z
LAST-MODIFIED:20250407T101249Z
UID:10000068-1744815600-1744822800@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg): Behaviour Modelling of Non-Cooperative Space Objects and Strategies for Decision Support in Space Situational Awareness
DESCRIPTION:In this modern era\, Space is vital for a Nation’s prosperity and without space\, many critical functions would simply stop working. The increasing number of satellite launches in recent times\, is congesting the space environment. Space is also becoming an increasingly contested environment from the perspective of non-civilian applications of satellites. The civilian and non-civilian space applications mandatorily require a complete awareness of the space environment before taking any operational decisions. Space Situational Awareness [SSA] is the comprehensive knowledge of Resident Space Objects [RSOs] which may include satellites\, rocket bodies\, debris\, and the ability to track and understand their behaviour. Space objects can be majorly categorized into two broad types\, cooperative space objects and non-cooperative space objects. A noncooperative space object is defined as a non-friendly object in space and can be perceived as a threat if it performs anomalous maneuvers in space. Modelling pattern-of-life of non-cooperative space objects is an essential requirement of SSA. Maneuvers of non-cooperative satellites is an important event of interest in their life pattern. In this thesis\, we investigate the behaviour of various classes of satellites through data driven modelling. We also study the threat perception from non-cooperative space objects to space assets of our interest. There are four key areas\, in which the thesis has significantly contributed. The first area deals with investigating\, exploring and modelling pattern-of-life of non-cooperative space objects. We have crafted data-driven solution methodologies from time series analysis\, machine learning\, deep learning to suit specific requirements. The second area pertains to the maneuvers of non-cooperative space objects. Identifying them\, helps in analyzing their behaviour. Since there may be numerous non-cooperative space objects and not all maneuvers of non-cooperative space objects may be threatening in nature\, it is essential to segregate routine maneuvers needed by a satellite to maintain its orbit from anomalous and abnormal maneuvers which may be perceived as threat. In this thesis\, we designed an approach to segregate benign and regular pattern-of-life maneuvers of non-cooperative space objects from their orbital data . The routine pattern-of-life maneuvers of satellites are events of interest\, but are infrequent and hence the non-maneuver class was observed to be far more numerous than the maneuver class label in the dataset. Through this thesis work\, we have applied Synthetic Minority Oversampling Techniques (SMOTE) and its variants to handle the imbalance in dataset available for classification. Different missions of cooperative civilian satellites in Low Earth Orbit (LEO) space regime were evaluated to prove the efficacy of the approach. The third area of contribution is in developing methodologies to estimate the threat perception for Geostationary Orbit (GEO) space regime. Modelling pattern-of-life of non-cooperative GEO satellites helps to identify anomalous behaviour and is essential for SSA. Additionally\, given a satellite of interest\, an assessment of the area of influence of neighbourhood satellite operations is critical for assessment of threat. Nearest neighbour search is a fundamental problem in computational geometry and we studied two major concepts of computational geometry \, the Voronoi diagram and the Delaunay triangulation in detail and crafted algorithms to assess threat in the GEO space regime. The last area of contribution is with scheduling the limited and costly ground based sensors to monitor the large number of space objects. There exists a problem of gaps in the available orbital data of noncooperative satellites. Moreover\, the satellite maneuver (event of interest) occurrence information of some samples may be lost\, due to noise in the ground sensor observations or due to observation window limits or losing tracks. Conventional machine learning regression methods are not suited to be able to include both the event and time aspects as the outcome. The conventional models are also are not equipped to handle censored examples (incomplete data due to non-observability). Therefore\, in this thesis\, we devised a solution methodology by applying Time-to-Event data analysis (survival analysis) techniques to assess whether a satellite maneuvered\, that is whether the event of interest occurred or not\, and also estimate when the next maneuver would occur. We have explored a variety of approaches including Cox proportional hazards model\, Weibull distribution model\, Kaplan-Meier model\, Nelson-Aalen model\, Random survival forest\, Survival Support Vector Machines\, Gradient boosted survival analysis and Deep learning based survival analysis. Detailed experimental results based on real life satellite orbital datasets are presented to bring out the effectiveness of the solution methodology. To summarize\, the thesis contributes by developing a space situational awareness system to achieve behavioural modelling\, classification and characterization of space objects of interest\, maneuver classification\, anomaly detection and threat assessment through data driven methodologies. \n  \nSpeaker: Shiv Shankar S  \n  \nResearch Supervisor: Debasish Ghose
URL:https://aero.iisc.ac.in/event/ph-d-engg-behaviour-modelling-of-non-cooperative-space-objects-and-strategies-for-decision-support-in-space-situational-awareness/
LOCATION:Online
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/04/SHIV-.jpg
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250319T150000
DTEND;TZID=Asia/Kolkata:20250319T170000
DTSTAMP:20260505T232957
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
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250313T150000
DTEND;TZID=Asia/Kolkata:20250313T170000
DTSTAMP:20260505T232957
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
END:VEVENT
BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250305T140000
DTEND;TZID=Asia/Kolkata:20250305T170000
DTSTAMP:20260505T232957
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
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250218T160000
DTEND;TZID=Asia/Kolkata:20250218T170000
DTSTAMP:20260505T232957
CREATED:20250212T065012Z
LAST-MODIFIED:20250212T065012Z
UID:10000053-1739894400-1739898000@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg): Passive control and intermittent dynamics of the precessing vortex core oscillation in swirl flows
DESCRIPTION:Swirl is used in modern gas turbine combustor nozzles to achieve   reliable flame stabilization and efficient fuel-air mixing. The swirl   component in the nozzle jet flow induces an axial vortex. At high swirl   intensities\, vortex breakdown occurs\, creating a recirculation zone in   the flow known as the vortex breakdown bubble (VBB). VBB appearance is   typically accompanied by the emergence of a global self-excited   instability where the VBB precesses around the flow axis and causes the   axial vortex to form a co-precessing helical structure. This  instability  is referred to as the precessing vortex core (PVC). Several  prior  studies have shown that the PVC oscillation can significantly  impact  emissions and thermoacoustic stability characteristics of the  combustor.  This thesis studies the characteristics and passive control  of the PVC.  The non-reacting flow field in an axial entry swirl nozzle  combustor at  the Massachusetts Institute of Technology (MIT)\, USA\, is  investigated.  Planar three component time resolved velocity field  measurements in the  combustor for combinations of two swirl numbers\, S  = 0.67 and 1.17 and  centrebody diameters of Dc = 9.5 mm\, 4.73 mm and 0  mm (i.e. no centrebody) are analysed. All cases are at a fixed bulk  Reynolds number of 20\,000. A new modal decomposition method based on  wavelet  filtering and proper orthogonal decomposition (WPOD) is  developed in  this thesis to analyze the global non-stationary dynamics  of these  flows. WPOD analysis for configurations without a centrebody  for both  swirl conditions revealed a coherent PVC oscillation in the  flow. Large  eddy simulation (LES) is performed for configurations  without the  centrebody and with the Dc = 9.5 mm centrebody for both  swirl numbers.  For all four cases\, LES accurately captures flow  statistics and PVC  characteristics observed in the corresponding  experimental measurements.  Linear stability analysis (LSA) on the time  averaged flow for each value  of S in the configuration without a  centrebody yields a nearly neutrally  stable global mode whose  oscillation frequency and spatial flow  oscillation amplitude  distribution characteristics match those induced  by the PVC in each  case. The wavemaker region associated with the PVC  mode is shown to be  situated at the upstream end of the VBB on the flow  centreline.  Therefore\, the introduction of a centrebody disrupts the  wavemaker and  suppresses the PVC as the experiments verify. In both LES  and  experimental studies for the cases with the Dc = 9.5 mm centrebody\,  low  amplitude PVC like oscillations\, which are also intermittent in the   S=0.67 case\, are observed. Resolvent analysis (RA) for helical forcing   on the time averaged flow field from LES for these cases is performed.  RA reveals a low rank\, optimal helical mode pair at frequencies where   PVC like oscillations are observed. The output mode amplitude   distribution characteristics match those of the PVC like oscillations  at  both values of S. For the S=0.67 case\, the input mode structure  suggests  that intermittent separation between the centrebody wake and  the VBB\,  due to turbulence results in the startup of PVC oscillations\,  which  subsequent merger then suppresses. For the S=1.17 case\, the input  mode  structure shows that stochastic forcing of the flow by turbulence\,  generated by vortex shedding off the upstream swirler\, results in sustained PVC like oscillations due to a low-rank strongly amplified   flow response at the PVC frequency revealed by resolvent analysis. \n  \nSpeaker: Saarthak Gupta \nResearch supervisor: Prof. Santosh Hemchandra
URL:https://aero.iisc.ac.in/event/ph-d-engg-passive-control-and-intermittent-dynamics-of-the-precessing-vortex-core-oscillation-in-swirl-flows/
LOCATION:Online
CATEGORIES:Thesis Colloquium / Defence
ATTACH;FMTTYPE=image/jpeg:https://aero.iisc.ac.in/wp-content/uploads/2025/02/Saarthak-.jpg
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20250203T153000
DTEND;TZID=Asia/Kolkata:20250203T170000
DTSTAMP:20260505T232957
CREATED:20250130T070018Z
LAST-MODIFIED:20250130T070404Z
UID:10000051-1738596600-1738602000@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg): Ultrasonic Guided Wave-based Inspection of Additively Manufactured Components
DESCRIPTION:Layered structural components\, such as laminated composites and those made via Additive Manufacturing (AM)\, are widely used in aerospace and automotive industries due to their various advantages. The layer-wise approach allows for intricate and multifunctional designs\, but their performance depends on factors such as joining technique\, material properties\, manufacturing conditions\, and service environments. These layered components are susceptible to defects like delamination\, debonding\, porosity\, residual stress\, cracks\, and surface roughness\, affecting mechanical performance. In AM\, process parameters like laser power\, scan speed\, layer thickness\, hatch spacing\, scan strategies\, solidification strategies\, and build chamber conditions impact the quality of the produced parts. Optimizing these parameters and using in-process monitoring systems can minimize these defects. This thesis focuses on developing an ultrasonics-based monitoring system for AM processes.\nThis work involves the modeling and analysis of wave propagation in multi-layered structures. For this purpose\, three different approaches based on the modeling of interlayer interface bonding have been formulated. The developed models allow for the analysis of different levels of interface bonding\, including perfect bonding and complete debonding. The AM components are idealized as one-dimensional higher-order planar frame structures. The equations of motion are derived from Hamilton’s principle\, and the Fourier transform-based Spectral Finite Element Method (FSFEM) is used to perform the spectral analysis and the spectral elements formulation. The FSFEM formulation results in the dispersion curves and responses in frequency domain\, which is transformed into the time domain by performing the inverse Fast Fourier Transform. A concept of effective thickness is introduced to match the cut-off frequencies in the dispersion curves obtained from the developed approaches with those of exact Lamb waves\, which are used in determining the shear correction factors necessary for higher-order frame formulations.\nThe developed models undergo two levels of validation involving the validation of the dispersion curves\, and time-domain responses. Reference dispersion curves are computed from open-source software for dispersion curve computation\, while the reference time-domain responses are obtained from experiments and the Finite Element simulations.\nFurther\, this thesis focuses on examining the interaction of ultrasonic-guided waves (UGW) with two types of defects – porosity and delamination/debonding. The impact of porosity is analyzed through porosity-dependent constitutive models. Various levels of delamination/debonding are numerically simulated by varying the interface bonding strength in the defect region. Additionally\, the Semi-analytical Finite Element Method is employed to perform spectral analysis of defective structural waveguides with complex geometry\, where the impact of various defect parameters\, such as size\, depth\, and orientation\, have been investigated. Further\, the developed FSFEM models are employed to solve inverse problems for material property characterization\, porosity estimation\, and interface bonding strength characterization. Ultimately\, these models provide a framework for analyzing the dynamic behavior of multi-layered structures\, offering insights into the interaction of UGW with defects. \nAll are welcome. \n  \nSpeaker :   Anoop Kumar Dube \n  \nResearch Supervisor : Prof. S. Gopalakrishnan FNAE FASc\, FIMechE\, CEng
URL:https://aero.iisc.ac.in/event/ph-d-engg-ultrasonic-guided-wave-based-inspection-of-additively-manufactured-components/
LOCATION:Online
CATEGORIES:Thesis Colloquium / Defence
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20241203T110000
DTEND;TZID=Asia/Kolkata:20241203T130000
DTSTAMP:20260505T232957
CREATED:20241126T095210Z
LAST-MODIFIED:20241129T054751Z
UID:10000033-1733223600-1733230800@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg): Aeroacoustic sources in twin turbulent jets
DESCRIPTION:An understanding of the aeroacoustics of twin turbulent jets is essential for applications involving noise reduction in dual engine aircrafts and launch vehicles. The aeroacoustic dynamics of these jets are influenced by the spacing between the shear layer of the two jets as well as the spatio-temporal nature of the structures arising from the interaction between the two jets. In the present work\, we construct reduced-order models of aeroacoustic sources for single and twin subsonic jets ($M_j=0.9$\, $Re=3600$)\, with the individual jets being replicas of a single jet\, with the goal of accurately recovering the far-field sound over a rather wide band of frequencies St=[0.07\,1.0] and directivity angles\, phi = [30 deg\,120 deg] within a subdecibel level accuracy. These models are designed as linear combinations of spatio-temporally coherent SPOD modes obtained in terms of the Lighthill’s stress tensor\, which in turn is computed through large-eddy simulations (LES) of the turbulent jets.  The present investigation involves two sets of twin subsonic jets of diameter D each\, with spacings of 0.1D and 1D\, where the jets merge upstream and downstream of breakdown\, respectively.  This is observed to alter the dynamics of twin jet evolution.  The closely spaced twin jet decays the slowest due to reduced turbulent stresses which are\, however\, more broadband due to early merging.  Such jets also show strong shielding in the plane of jets\, especially at shallow directivity angles where sound levels may drop below that of the single jet.  The farther spaced twin jets have dynamics that are more akin to the constituent single jet with turbulent fluctuations peaking here at St=0.34\, but showing very little shielding\, with their OASPL mostly linked to the nature of extra flow structures created during merging.  Three-dimensional\, energy-ranked\, coherent structures (SPOD modes) for twin jets exhibit rather poor low-rank behaviour\, especially\, at the far-field spectral peak St=0.14\, unlike that of the single jet\, which is indicative of spatio-temporally complicated structures arising from the merging of the turbulent merging of the twin jets.  At St > 0.3\, the SPOD wavepackets show strong visual coherence\, resembling Kelvin–Helmholtz instability modes upstream of breakdown\, while at the lower frequencies there is very little spatial coherence with wavepackets peaking downstream of breakdown.  Although the leading SPOD modes radiate poorly\, reduced-order models using a subset of them\, up to 45 SPOD modes per frequency\, show for the first time remarkable match (within 1 dB) against the LES-predicted sound over 0.1 < St < 0.5\, at all angles investigated\, including that for the peak sound. At other frequencies\, the error barely exceeds a decibel\, except for the closely spaced twin jet which due to its greater hierarchy of spatio-temporal structures\, show slower convergence at the shallower angles for St > 0.5. \n  \nSpeaker:  Nishanth Muthichur \nResearch Supervisor: Santosh Hemchandra
URL:https://aero.iisc.ac.in/event/ph-d-engg-aeroacoustic-sources-in-twin-turbulent-jets/
LOCATION:Online
CATEGORIES:Thesis Colloquium / Defence
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20241127T110000
DTEND;TZID=Asia/Kolkata:20241127T130000
DTSTAMP:20260505T232957
CREATED:20241126T094710Z
LAST-MODIFIED:20241126T094710Z
UID:10000032-1732705200-1732712400@aero.iisc.ac.in
SUMMARY:Ph.D. (Engg): On the nature of transonic buffet in a finite span wing
DESCRIPTION:Transonic buffet\, or shock oscillations\, is a pre-stall aerodynamic instability\, caused by shock boundary layer interaction\, of the flow over a wing. This aerodynamic instability occurs at critical combinations of transonic Mach number and angle of attack. Shock oscillations cause vibrations of the wing and is known as buffeting. Buffeting may cause fatigue of the wing\, and in an overall sense limit the flight envelope of the aircraft. Despite decades of study\, an unequivocal understanding of the physical mechanism of transonic buffet is lacking. In literature\, global stability analysis\, modal analysis\, and spatial correlation-based wave propagation analysis have been the tools of choice in understanding the mechanisms that cause transonic buffet. Here we present a perspective on transonic buffet\, using results from correlation analysis\, streamwise and spanwise pressure distributions\, and the temporal evolution of skin friction lines on the surface of the Benchmark Supercritical Wing (BSCW). Skin friction lines and critical point theory are well established to describe 3D separated flows over solid walls and bodies. Together with correlation analysis of time-resolved fluid dynamics\, the evolution of skin friction lines reveals a new perspective on the driving mechanism for shock oscillations. This viewpoint supports\, in some ways\, earlier observations on the drivers of shock-induced separation in a finite span and infinite span wing but also reveals new insights on 3D shock oscillations. The presence and distribution of these critical points—unstable foci\, saddle points\, and nodes—lead to the formation of buffet cells or pockets of streamwise shock oscillations along the span. The topology of skin friction lines in the presence of these critical points gives rise to separation and re-attachment lines. In particular\, the propagation of buffet cells is shown to be due to the self-induced motion of contra-rotating unstable foci in the skin friction lines. The self-induced motion of these unstable foci\, or vortices\, causes them to convect inboard or oscillate spanwise. This perspective on transonic buffet based on the distribution of critical points of the skin friction lines\, enables possibilities of buffet control using low-order nonlinear dynamical system models. \nSpeaker: Magan Singh \nResearch Supervisor: Prof Kartik Venkatraman
URL:https://aero.iisc.ac.in/event/ph-d-engg-on-the-nature-of-transonic-buffet-in-a-finite-span-wing/
LOCATION:Online
CATEGORIES:Thesis Colloquium / Defence
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BEGIN:VEVENT
DTSTART;TZID=Asia/Kolkata:20240917T153000
DTEND;TZID=Asia/Kolkata:20240917T163000
DTSTAMP:20260505T232957
CREATED:20241118T094538Z
LAST-MODIFIED:20241118T094538Z
UID:10000021-1726587000-1726590600@aero.iisc.ac.in
SUMMARY:Advanced Mission Architectures for Long-term Exploration of Mars\, Venus\, and Beyond
DESCRIPTION:The increasing complexity of future space exploration roadmaps calls for novel mission architectures\, integrated mission analysis\, and systems engineering frameworks to inform early decision-making and technological innovation. In this talk\, I will discuss the mission architecture and analysis of two multi-decade campaigns: (1) human missions to Mars\, and (2) astrobiology-driven missions to Venus. First\, I will present the orbital design considerations and results for Mars Spacedock\, an orbital platform for sustainable human exploration. A system-level optimization incorporates discreet mission constraints and comprehensive analysis across all the mission phases from interplanetary trajectories to entry\, descent\, and landing (EDL). Surface accessibility from candidate orbits is obtained by implementing constant bank angle control during EDL. Next\, I will discuss the mission design for a series of missions to Venus searching for signs of life in the clouds. I will highlight the early trade-offs between objectives and operational constraints for a balloon platform and a sample return mission. A focal point will be the Venus ascent vehicle design for sample return through launch trajectory optimization. Additionally\, I will briefly discuss ongoing experiments to establish the feasibility of instruments for in situ analysis of sulfuric acid clouds. Finally\, I will discuss my future research plans in mission design\, systems engineering\, and innovative small-scale spacecraft testing platforms for advanced technologies such as GNC during proximity operations.   \nSpeaker: Dr. Rachana Agarwal \nBiography: Rachana Agrawal is currently a Postdoctoral Associate in the Earth\, Atmospheric and Planetary Sciences department with Prof. Sara Seager at MIT. She is leading mission design and instrumentation projects for astrobiology-focused missions to Venus. She obtained her PhD from the School of Aeronautics and Astronautics at Purdue University under the supervision of Prof. James Longuski and Prof. Sarag Saikia. Her PhD work focused on the design and analysis of an orbital logistics architecture for the sustainable human exploration of Mars. She is broadly interested in robotic and human space mission engineering with current focus on mission analysis\, systems engineering\, and technological innovation and development.
URL:https://aero.iisc.ac.in/event/advanced-mission-architectures-for-long-term-exploration-of-mars-venus-and-beyond/
LOCATION:Online
CATEGORIES:AE Seminar
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