Browse Topic: Materials properties

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Design-Driven Sustainability of Automotive Components: A Comparative LCA from Conventional to Metal and Composite Additive Manufacturing2026-37-0037To be published on 06/09/2026
The increasing pressure to decarbonize manufacturing systems is pushing industry beyond conventional lightweighting strategies toward material and process paradigms, capable of delivering functional performance with radically lower environmental impact. In this context, polymer-based composite Additive Manufacturing (AM) offers an underexplored yet highly promising pathway for sustainable production of load-bearing components. This study presents a preliminary comparative cradle-to-gate Life Cycle Assessment (LCA) of a Formula SAE brake pedal, assessing the environmental transition from conventional CNC machining of Aluminum 7075-T6 to additive manufacturing solutions, with specific focus on Carbon-Fiber-Reinforced Polymer (CFRP) composites. Two topology-optimized designs, respectively for Powder Bed Fusion (PBF) in AlSi10Mg and Material Extrusion (MEX) in PETG-CF are compared to machined aluminum benchmark. The analysis is integrated in the product and process design following ISO
Dalpadulo, Enrico, Russo, Mario, Apté MD, Raphaëlle, Leali, Francesco
A predictive methodology for 3D-CFD simulation of piston thermal field in sustainable high-performance engines2026-37-0002To be published on 06/09/2026
In recent years, especially in high performance engines, the thermal stress of pistons has gradually increased due to the implementation of various technologies, aimed at meeting emission reduction and specific power increase requirements. If the heat is not properly dissipated, cracking and plastic deformation of the material as well as formation of hot spots triggering self-ignition can occur. To overcome these problems, one or more jets of oil are directed towards the piston undercrown region, impacting at high speed. This technique ensures immediate cooling and allows the engine performance to be increased without compromising the useful life. In order to optimize the oil jet effectiveness, 3D-CFD can be proficiently adopted. In this regard, the aim of this work is to define a robust numerical methodology able to simulate oil jet impingement and piston thermal field. In particular, a 3D-CFD Volume-of-Fluid (VoF) simulation is used to numerically assess the oil jet impact and
Duni, Andrea, Berni, Fabio, Breda, Sebastiano, Fontanesi, Stefano, Gilioli, Filippo
Predictive model and analysis of the resultant force in the dry machining of Mg-4Zn/Si3N4 nanocomposites2026-26-0762To be published on 06/01/2026
In aerospace and automotive applications, the usage of magnesium (Mg)-based alloys and composites reduces the structural weight due to their low density. They also possess good specific strength and are abundantly available. The Mg-4Zn alloy is one such Mg-based alloy that is also biodegradable and biocompatible. In spite of these advantages, there is a strong need and scope to improve its wear resistance and mechanical properties. Mg-4Zn nanocomposites with Si3N4 reinforcements (also a biocompatible bio-ceramic) are hypothesized to possess superior properties. Sustainable machining with minimal subsurface defects and minimal energy consumption is necessary to manufacture components from these vacuum stir-cast nanocomposites. The resultant machining force (Fr) is a good indicator of subsurface quality and energy consumption in machining. The addition of Si3N4 reinforcement to improve the properties of the Mg-4Zn alloy could introduce challenges in machining and could influence Fr. To
N, Anand, Shaju, Tony M, G, Nagamalleswara Rao, D, Bijulal, K, Jayaprakash Reddy, K, Vijayan, Chaman, Joji J
Wear Resilience Characteristics of 2% Silicon Nitride Strengthened AZ31 Magnesium Composite2026-26-0740To be published on 06/01/2026
To develop magnesium matrix composites, ceramic silicon nitride (Si3N4) particles are used to strengthen the magnesium (AZ31) matrix by adding 2 wt.%. The composite is developed by disintegrated melt deposition vacuum stir casting method. Microstructural studies reveal the presence of Si3N4 particles and their uniform distribution. A L9 orthogonal array planned using Taguchi’s experimental design is chosen for three wear parameters axial load (AL), rotational speed (RS), and time duration (TD) for trials as per G99 standard in pin-on-disc apparatus. Experimental outcomes show a rise in axial stress; wear loss increases dramatically. Because the area of contact shrinks as sliding speed increases, wear loss diminishes dramatically. When the AL is low, CoF increases, and when the AL is large, CoF drops. When the sliding speed is increased, CoF decreases. To optimize multiple responses effectively, the TOPSIS method (Technique for Order of Preference by Similarity to Ideal Solution) was
Senthilkumar, N., Dhinakar Raj, C K
Evaluation of Thermal and Thermo-Mechanical Behavior of Ramie Fiber/Delrin Composites for Aircraft Cabin Components2026-26-0754To be published on 06/01/2026
Abstract This study investigates the fabrication and evaluation of Delrin (polyoxymethylene, POM) composites reinforcing 5, 10, 15, and 20 wt.% chopped ramie fiber (RF). The polymer composites were fabricated via injection moulding technique. Glass transition temperature (Tg), thermal conductivity, Vicat softening temperature (VST), heat deflection temperature (HDT), melt flow index (MFI), and coefficient of linear thermal expansion (CLTE) were the various thermo-mechanical and thermal characteristics of the composites that were systematically evaluated as per the ASTM standards. The Delrin matrix's performance was drastically altered by the addition of RF. Within the formulations, the composite with 15 wt.% RF had the best combination of properties: higher VST and HDT values responsible for more dimensional stability at high temperatures, lower CLTE producing lesser thermal expansion, comparatively better thermal conductivity and more heat dissipation. Eventually, there was a moderate
S, Thirumalvalavan, Senthilkumar, N., Selvarasu, S
Augmented Reality and Multimodal Interfaces for Astronaut Training and In-Orbit Operations2026-26-0796To be published on 06/01/2026
Augmented Reality (AR) and multimodal human–machine interfaces (HMI)—combining visual overlays, voice, gesture, eye-tracking, and biometric sensing—are now maturing into flight-relevant technologies capable of transforming astronaut training and in-orbit operations. These interfaces reduce task time, lower error rates, and mitigate cognitive load, thereby strengthening both crew autonomy and mission safety. For India, the timing is critical: Gaganyaan human spaceflight program is approaching decisive crewed missions in the late 2020s, and the Bharatiya Antariksh Station (BAS) is targeted for the 2030s. AR/MMI can be positioned not as an accessory but as a core enabling system for training throughput, real-time crew support, and resilient station operations. This paper provides (i) an overview of India’s current scenario, including Gaganyaan astronaut training ecosystems, IIT Madras collaborations on AR/VR, and Vyommitra humanoid readiness; (ii) synthesis of global case studies—NASA
Yadav, Anoop Singh
IMPROVEMENT OF MECHANICAL PROPERTIES OF SYNTHETIC FIBER REINFORCED COMPOSITES THROUGH ADDITION OF GRAPHENE OXIDE2026-26-0753To be published on 06/01/2026
Unmanned Aerial Vehicles (UAVs) demand structural materials that are lightweight, strong, impact-resistant, and durable in diverse environments.The synthetic fiber and natural fiber reinforced polymer composites have varying mechanical performance depending on the fibermatrix interfacial properties. This research analyzes the influence of Graphene Oxide (GO) nano fillers on mechanical properties of composites. Firstly, the epoxy resin was was modified by incorporating different weight percentage of graphene oxide. This resin was used to make an composite laminate using different materials (Carbon, Glass and Natural Fibers). Then the composites were put through the tensile, compression, flexural, and impact strength tests. The synthetic fiber and natural fiber reinforced polymer composites have a significant improvement in mechanical properties due to the addition of graphene oxide.
Manoharan, Dinesh, Langford, Peter, M.K., Padmanabhan, R, Prithviraj, Rajkumar, Subbiah, Karthikeyan, Ravikumar, Veeramuthu, Balasubramaniyan, Gunaseelan, John, T, Thangaraj
Finite Element Approach for Fatigue Life Prediction of Threaded Bolts with Experimental Validation2026-26-0745To be published on 06/01/2026
Predicting the fatigue life of threaded bolts is crucial in aerospace and mechanical assemblies where cyclic loading can cause early joint failure. Previous research conducted experiments to develop S-N curves for high-strength bolts under different pretension and temperature conditions (Zhang et al. 2024). However, there are a very few numerical methods that can replicate these results, especially for bolts with screw threads. In this work a finite element analysis (FEA) methodology is developed to predict the fatigue performance of threaded bolts under axial loading and validated using the experimentally derived Series-1 S-N data for M20 high-strength bolts. The approach includes detailed FEA modelling (3D solid) with explicit thread geometry to capture local stress distributions under cyclic tensile loading. Peak stress amplitudes are employed to estimate fatigue life by applying the Basquin relation and the Series-1 S-N curve. The results are compared with the calculated fatigue
K R, Lesanth, S, Suhail Ahmed, C, Arunvetrivel, P, Krishnakumar, P S, Premkumar, Vasantharaj, C
Non-Intrusive Fatigue Detection and Alerting for Pilots2026-26-0793To be published on 06/01/2026
Pilot fatigue represents a critical concern in aviation safety, as it can significantly impair cognitive functions, decision-making abilities, and reaction times. In addition to decreasing performance, chronic fatigue has negative long-term health effects. Possible causes of fatigue include sleep loss, extended time awake, circadian phase irregularities and workload. Conventionally, the risk due to fatigue in aerospace is reduced by limiting pilot's flying hours and controlled rest requirements. Despite regulations on flying hours and optimal rostering, fatigue cannot be prevented completely. Hence, there is need to detect pilot fatigue in real time, annunciate in cockpit and transmit the information to airliners post-flight for appropriate fatigue risk management. There is ongoing research to detect pilot fatigue using devices that can capture Electroencephalogram (EEG) and Electrocardiogram (ECG). Though these devices have high fidelity, they are intrusive and can limit pilot
Nyamagoudar, Vinayak, P R, Namratha, Ramachandran, Venkataramani
Reducing Test Campaigns through Advanced Yield Surface Modeling for New Aircraft Metal Grades2026-26-0755To be published on 06/01/2026
Qualification of new aerospace alloys requires extensive mechanical testing to capture anisotropy and ensure reliable performance under complex loading conditions. This process is costly and time-consuming, particularly with emerging manufacturing routes such as additive manufacturing. Advanced yield surface prediction offers a route to reduce test campaigns by linking microstructural features to macroscopic constitutive models. In this work, Digimat is employed as a multi-scale material modeling platform to generate yield surfaces of polycrystalline metals using computational homogenization. Representative volume elements (RVEs) are constructed from experimental texture and grain morphology data, and their response under multiaxial loading is simulated using a crystal plasticity framework. The computed yield loci are then fitted with phenomenological functions (e.g. Barlat2000), enabling calibration of anisotropic yield models from virtual testing. As a case study, an AA6016-T4 sheet
Padhan, Manas, Uppaluri, Rohith, Lemoine, Guerric, Soni, Ganesh
Porosity Matters: Multiscale Simulation of Composite Panel Performance in Aerospace Structures2026-26-0731To be published on 06/01/2026
Porosity in carbon fibre reinforced polymers (CFRP) remains a critical concern for aerospace engineers, as even minor voids introduced during manufacturing can undermine the reliability of structural components. This work explores the influence of interply porosity on composite panel behaviour, employing a multiscale simulation approach that bridges material characterisation and full-scale structural analysis. The study begins with virtual coupon testing using Digimat-VA and Digimat-MF, enabling the prediction of material allowables and the assessment of defect variability. Homogenised material properties derived from these simulations are then applied to detailed panel models constructed in MSC Apex, ensuring accurate representation of layup and orthotropic behaviour. The workflow can support a range of structural load cases, allowing for the evaluation of stiffness, buckling, or other relevant scenarios as dictated by aerospace certification requirements. Nonlinear finite element
Savane, Vishal, Kumar, Rajat
Investigation of Aluminium Alloy Composites Reinforced with Zirconium oxide and Solid Lubricant Attributes for Brake and Clutch Components of Aircrafts2026-26-0752To be published on 06/01/2026
For brake and clutch components of aircraft, which require higher mechanical strength and wear resistance, lightweight aluminum composites were developed by infusing solid lubricant. In this study, hybrid composites were developed using the powder metallurgy route, using aluminum alloy AA356 and various amounts of zirconium oxide (ZrO₂) (0, 5, 10, 15, and 20 wt.%) as reinforcements. A solid lubricant, hexagonal boron nitride (hBN), at a fixed 5 wt.% is considered. Following the appropriate ASTM guidelines, the specimens were mechanically characterized by measuring their density, porosity, micro-hardness, compression strength, impact strength, and flexural strength, among other properties. The findings showed that the composites' physical and mechanical behaviour were greatly affected by the addition of ZrO₂.Porosity increased as a result of particle clustering and interfacial voids, while density increased gradually as ceramic content increased. Consistently increasing ZrO₂ addition
Senthilkumar, N.
Hybrid Digital Twin for Aero-Engine Bearing Prognostics: A Physics-Informed Machine Learning Approach to RUL Prediction2026-26-0718To be published on 06/01/2026
Unscheduled maintenance due to the failure of critical components, such as aero-engine rolling element bearings, is a leading cause of costly Aircraft-on-Ground (AOG) events; consequently, current time-based maintenance practices are inefficient and prone to risk. This paper develops a resource-efficient Hybrid Digital Twin (HDT) model for an engine bearing, focusing on the dynamic prediction of spall growth due to Rolling Contact Fatigue (RCF), thereby enabling a condition-based maintenance paradigm. The HDT architecture integrates two core models: (1) a physics-informed model that uses established life and fatigue theory to define initial degradation thresholds and constrain the failure envelope, and (2) a data-driven Recurrent Neural Network (RNN) (specifically, an LSTM) for dynamic degradation rate modeling. The methodology utilizes a Monte Carlo simulation coupled with RCF progression equations to generate a large, synthetic run-to-failure dataset under varying operational loads
Mohamed, Abbas
Lightweight Magnesium Nanocomposites with Enhanced Wear Resistance for Landing Gear Application2026-26-0751To be published on 06/01/2026
This study systematically evaluated the wear behaviour of an AZ61 magnesium alloy reinforced with 15 wt.% SiC and different amounts of multi-walled carbon nanotubes (MWCNTs) under dry sliding circumstances, adopting a pin-on-disc apparatus (ASTM G99). To identify the influence of factors like sliding speed (SS) (1-3 m/s), axial load (AL) (10-30 N), and MWCNT concentration (0-3 wt.%) on tribological performance, experiments were developed using a Central Composite Design (CCD) under Response Surface Methodology (RSM). Findings showed that wear loss (WL) was greatly amplified by increasing AL owing to localized heating and contact stresses, and that a compacted tribolayer was formed by increasing SS, which decreased WL but marginally raised the coefficient of friction (CoF). At moderate AL (15-20 N), SS (2 m/s), and 2 wt.% MWCNT, the wear resistance was significantly improved by improving load transfer and creating a lubricating carbon-rich coating, resulting in a decreased WL of around
Senthilkumar, N.
Rings, Flash-Welded, Titanium and Titanium AlloysAMS7498T (Current)4/26/2026
This specification covers flash-welded rings made of titanium and titanium alloys (see 8.5).
AMS G Titanium and Refractory Metals Committee
Titanium Alloy, Sheet, 5Al - 4V - 0.75Mo - 0.5Fe, AnnealedAMS6951B (Current)4/26/2026
This specification covers a titanium alloy in the form of sheet 0.025 through 0.100 inch (0.63 through 2.54 mm), inclusive, in thickness (see 8.6).
AMS G Titanium and Refractory Metals Committee
Aluminum Alloy Castings, 7.0Si - 0.58Mg - 0.15Ti - 0.06Be (D357.0-T6), Solution and Precipitation Heat Treated, Dendrite Arm Spacing (DAS) ControlledAMS4241F (Current)4/25/2026
This specification covers an aluminum alloy in the form of castings.
AMS D Nonferrous Alloys Committee
Titanium Alloy, Welding Wire, 6AI - 2Sn - 4Zr - 2MoAMS4952H (Historical)4/25/2026
This specification covers a titanium alloy in the form of welding wire (see 8.5).
AMS G Titanium and Refractory Metals Committee
Steel, Corrosion- and Heat-Resistant, Bars, Wire, Forgings, Mechanical Tubing, Rings and Forging Stock, 15Cr - 25.5Ni - 1.2Mo - 2.1Ti - 0.006B - 0.30V (A286), Consumable Electrode Melted, 1750 °F (954 °C) Solution Heat Treated, Welding Grade, Precipitation HardenableAMS5895G (Current)4/25/2026
This specification covers a corrosion- and heat-resistant steel in the form of bars, wire, forgings, mechanical tubing, flash-welded rings, and stock for forging, flash-welded rings, or heading.
AMS F Corrosion and Heat Resistant Alloys Committee
Plating, Nickel-Thallium-Boron or Nickel-Boron, Electroless DepositionAMS2433E (Current)4/25/2026
This specification covers the requirements for an electroless nickel-thallium-boron or nickel-boron deposit on various substrates.
AMS B Finishes Processes and Fluids Committee
Aluminum Alloy, Castings, 5.0Si - 1.2Cu - 0.50Mg (355.0-T51), Precipitation Heat TreatedAMS4210N (Historical)4/25/2026
This specification covers an aluminum alloy in the form of castings (see 8.6).
AMS D Nonferrous Alloys Committee
Steel, Corrosion- and Heat-Resistant, Investment Castings, 19Cr - 12Ni - 1.0Cb (Nb), Solution Heat TreatedAMS5362N (Current)4/25/2026
This specification covers a corrosion- and heat-resistant steel in the form of investment castings.
AMS F Corrosion and Heat Resistant Alloys Committee
Castings, Aluminum Alloy Sand, 5.0Si - 1.2Cu - 0.50Mg (355.0-T71), Solution Heat Treated and OveragedAMS4214L (Current)4/25/2026
This specification covers an aluminum alloy in the form of sand castings (see 8.6).
AMS D Nonferrous Alloys Committee
Titanium Alloy Sheet, 6Al - 4Sn - 3Nb - 0.5Mo - 0.3Si, Duplex AnnealedAMS6953B (Current)4/25/2026
This specification covers a titanium alloy in the form of sheet 0.020 to 0.1874 inch (0.51 to 4.760 mm), inclusive, in nominal thickness (see 8.6).
AMS G Titanium and Refractory Metals Committee
Aluminum Alloy, Extrusions, 0.68Mg - 0.40Si (6063-T6), Solution and Precipitation Heat TreatedAMS4156M (Current)4/24/2026
This specification covers an aluminum alloy in the form of extruded bars, rods, wire, profiles, and tubing up to and including 1.000 inch (25.4 mm) in diameter, least thickness, or tube wall thickness (see 8.6).
AMS D Nonferrous Alloys Committee
Copper-Beryllium Alloy, Bars, Rods, Shapes, and Forgings, 98Cu - 1.9Be, Solution Heat Treated (TB00)AMS4650P (Current)4/21/2026
This specification covers a copper-beryllium alloy in the form of bars, rods, shapes, and forgings (see 8.5).
AMS D Nonferrous Alloys Committee
Aluminum Alloy, Hand Forgings, 6.2Zn - 2.3Cu - 2.2Mg - 0.12Zr (7050-T7452), Solution Heat Treated, Compression Stress-Relieved, and OveragedAMS4108G (Current)4/21/2026
This specification covers an aluminum alloy in the form of hand forgings 8 inches (203 mm) and under in nominal thickness and of forging stock (see 8.6).
AMS D Nonferrous Alloys Committee
Aluminum Alloy, Extruded Profiles (2065-T84), 4.2Cu - 1.2Li - 0.52Mg - 0.32Mn - 0.32Ag - 0.1Zr, Solution Heat Treated, Stress Relieved by Stretching and Artificially AgedAMS4366B (Current)4/21/2026
This specification covers an aluminum-lithium alloy in the form of extruded profiles with a maximum cross-sectional area of 19 square inches (123 cm2) and a maximum circle size of 11 inches (279 mm) from 0.040 to 0.499 inch (1.00 to 12.50 mm) in thickness (see 8.6).
AMS D Nonferrous Alloys Committee
Steel Bars, Forgings, Mechanical Tubing and Forging Stock, 1.2Cr - 3.25Ni - 0.12Mo (0.07 - 0.13C) (9310), Premium Aircraft-Quality, Electroslag Remelted or Consumable Electrode Vacuum RemeltedAMS6267L (Current)4/20/2026
This specification covers a premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock.
AMS E Carbon and Low Alloy Steels Committee
Nickel Alloy, Corrosion- and Heat-Resistant, Bars, Forgings, Rings and Stock for Forgings, Rings and Heading, 72Ni - 15.5Cr - 0.95Cb - 2.5Ti - 0.70Al - 7.0Fe (Inconel® X750), Equalized, Precipitation HardenableAMS5667R (Current)4/13/2026
This specification covers a corrosion- and heat-resistant nickel alloy in the form of bars, forgings, flash-welded rings, and stock for forging, flash-welded rings, or heading.
AMS F Corrosion and Heat Resistant Alloys Committee
Steel, Corrosion- and Heat-Resistant, Sheet, Strip, and Plate, 15Cr - 25.5Ni - 1.2Mo - 2.1Ti - 0.006B - 0.30V (A286), Multiple Melted, 1800 °F (982 °C) Solution Heat Treated, Welding Grade, Precipitation HardenableAMS5858F (Current)4/13/2026
This specification covers a corrosion- and heat-resistant steel in the form of sheet, strip, and plate.
AMS F Corrosion and Heat Resistant Alloys Committee
Investigation of Metallurgical and Mechanical Behaviors of AA6061-AA2017 Joints Produced by Single- and Double-Pass Friction Stir Welding: Influence of Base Material Position and Post-Weld Shot Peening Technique05-19-04-00264/13/2026
The growing demand for lightweight, high-strength materials in marine and aerospace structures has promoted the use of friction stir welding (FSW) for welding dissimilar aluminum alloys. However, tensile residual stresses and microstructural heterogeneities often degrade weld integrity. This study investigates the combined impact of base material positioning, single- and double-pass FSW, and post-weld shot peening (SP) on the metallurgical and mechanical properties of AA6061–AA2017 joints. Five welding configurations were examined to evaluate how varying base material positions on the advancing and retreating sides affect material flow and mechanical behavior. Post-weld SP effectively presented compressive residual stresses, reduced surface defects, and refined surface grains. The average grain size in the stir zone was reduced from 5.2 μm (single-pass) to 2.0 μm (double-pass U-turn) after SP, confirming significant grain refinement through dynamic recrystallization. Mechanical testing
Nukathoti, Raja Sekhar, Battina, N. Malleswara Rao, Vanthala, Varaha Siva Prasad, Chirala, Hari Krishna, Maloth, Balu
Nickel Alloy, Corrosion- and Heat-Resistant, Sheet, Strip, and Plate, 45.5Ni - 25.5Cr - 3.2Co - 3.2Mo - 3.2W - 18.5Fe, (RA333®), Solution Heat TreatedAMS5593J (Current)4/13/2026
This specification covers a corrosion- and heat-resistant nickel alloy in the form of sheet, strip, and plate.
AMS F Corrosion and Heat Resistant Alloys Committee
Steel, Corrosion-Resistant, Investment Castings, 16Cr - 1.9Ni - 0.08N (431), As CastAMS5353G (Current)4/13/2026
This specification covers a corrosion-resistant steel in the form of investment castings.
AMS F Corrosion and Heat Resistant Alloys Committee
Steel, Corrosion-Resistant, Bars, Wire, Forgings and Forging Stock, 18.5Cr - 10Ni - 0.22Se (303Se), Free-Machining; for Swaging or Upsetting, Solution Heat TreatedAMS5641K (Current)4/13/2026
This specification covers a free-machining, corrosion-resistant steel in the form of bars, wire, forgings, and forging stock.
AMS F Corrosion and Heat Resistant Alloys Committee
Titanium Alloy Bars, Wire, Forgings, and Rings, 6Al - 6V - 2Sn, AnnealedAMS4978K (Current)4/13/2026
This specification covers a titanium alloy in the form of bars, wire, forgings, flash-welded rings 4.000 inches (101.60 mm) and under in diameter or least distance between parallel sides, and stock of any size for forging or flash-welded rings (see 8.6).
AMS G Titanium and Refractory Metals Committee
Magnesium Alloy, Investment Castings, 8.7Al - 0.70Zn - 0.22Mn (AZ91C-T6), Solution and Precipitation Heat TreatedAMS4452G (Current)4/9/2026
This specification covers a magnesium alloy in the form of investment castings (see 8.6).
AMS D Nonferrous Alloys Committee
Steel Bars, Forgings, and Tubing, Nitriding, 1.4Cr - 1.2Mo - 0.3V (0.29 - 0.36C), (32CrMoNiV5), Double Vacuum Melted, Premium Aircraft-Quality for Bearing ApplicationsAMS6498C (Current)4/9/2026
This specification covers a nitriding grade of premium aircraft-quality, low-alloy steel in the form of bars, forgings, mechanical tubing, and forging stock. AMS6496 and AMS6497 cover UNS K23280 with other quality levels.
AMS E Carbon and Low Alloy Steels Committee
Aluminum Alloy, Rolled or Forged Rings, 5.6Zn - 2.5Mg - 1.6Cu - 0.23Cr (7075-T651, 7075-T652), Solution Heat Treated, Mechanically Stress Relieved, and Precipitation Heat TreatedAMS4310G (Current)4/9/2026
This specification covers an aluminum alloy in the form of rolled or forged rings up to 6 inches (152 mm), inclusive, in thickness (see 3.3.1.1.1) and an OD to wall thickness ratio of 10 or greater (see 8.5).
AMS D Nonferrous Alloys Committee
Steel, Sheet, Strip, and Plate, 0.75Si - 0.62Cr - 0.20Mo - 0.10Zr (0.10 - 0.17C) (NAX 9115-AC)AMS6354H (Current)4/8/2026
This specification covers a low-alloy steel in the form of sheet, strip, and plate 4.00 inches (101.6 mm) and under in thickness.
AMS E Carbon and Low Alloy Steels Committee
Copper Alloy (Brass), Sheet, Strip, and Plate, 70Cu - 30Zn, Half Hard (H02)AMS4507K (Current)4/8/2026
This specification covers a copper-zinc alloy (brass) in the form of sheet, strip, and plate (see 8.6).
AMS D Nonferrous Alloys Committee
Aluminum Alloy, Sheet, 3.2Cu - 0.52Mg - 0.30Ag - 0.95 Li - 0.12Zr (2198-T8), Solution Heat Treated, Cold Worked, and Artificially AgedAMS4412C (Current)4/8/2026
This specification covers an aluminum alloy in the form of sheet from 0.063 to 0.249 inch (1.60 to 6.30 mm) in nominal thickness (see 8.6).
AMS D Nonferrous Alloys Committee
Magnesium Alloy, Investment Castings, 9.0Al - 2.0Zn (AZ92A-T6), Solution and Precipitation Heat TreatedAMS4453H (Current)4/8/2026
This specification covers a magnesium alloy in the form of investment castings (see 8.6).
AMS D Nonferrous Alloys Committee
Test Method for Measuring Wet Color Transfer CharacteristicsJ1326_202604 (Current)4/8/2026
This procedure describes a method of measuring the resistance to wet color transfer of materials such as textiles, leather, and composites.
Textile and Flexible Plastics Committee
ANN and RSM-Driven Optimization of Tribological Characteristics of CuO-Doped Castor Oil Bio-Lubricants2026-01-03534/7/2026
The development of renewable and eco-friendly bio-lubricants can address the environmental challenges posed by petroleum-based lubricants. At the same time, it is possible to improve the tribological properties of lubricants through alternative sources. To overcome these problems, castor oil is a potential basis for bio-lubricants due to its high viscosity, natural lubricity, and biodegradability. In the current work, castor oil was chemically modified by the epoxidation process. This process has improved the tribological properties of castor oil through the epoxidation method. In this method, the presence of hydrogen peroxide acts as an oxidizing agent while sulfuric acid serves as a catalyst, converting the unsaturated double bonds present in the oil into oxirane rings. At the same time, this modification enhanced the thermal stability and tribological applications in harsh operating conditions. The tribological performance of the epoxidized castor oil, further reinforced with copper
Prabhakaran, J, Pali, Harveer Singh, Singh, Nishant Kumar
Life of a Formula One Power Unit: Valvetrain Systems2026-01-02694/7/2026
The world of Formula One (F1) is changing with impending 2026 F1 regulations imposing even stricter limits on engine component usage while increasing races. The valvetrain system, specifically the intake valves, is a critical determinant in controlling gas exchange within the cylinders, directly impacting air-fuel charge and power output. The aim of this investigation is to study the mechanisms of intake valve and valve seat wear which will influence engine performance due to leakage path development. The wear mechanism of the intake valves considers wear from impact from valve seat interaction, sliding and foreign particle abrasion for quantifying valve seat recession. An FIA 2026-2030 regulations compliant valve train model was developed in GT-Suite to help estimate valve seat wear. The validated model could predict valve recession for a given engine operating speed trace from racetrack data. This report presents a systematic methodology for developing valve seat wear quantification
Soh, Sean Kendrick, Samuel, Stephen
Effective Prediction of the Mechanical Properties of Glue-Laminated Motor Stator Core with Consideration of Glue Disposition2026-01-01774/7/2026
This study presents an effective predictive methodology for determining the mechanical properties of glue-laminated motor cores, with explicit consideration of glue disposition, including bonding pattern, configuration, location, and coverage. In laminated stator cores, glue bonding and stacking processes jointly govern the mechanical integrity of the lamination stack. Practical production bonding schemes are typically nonuniform and localized, leading to spatial variations in stiffness and to locally anisotropic, orthotropic material behavior. These effects influence both the in-plane and through-thickness stiffness of the stator core. They can significantly affect the accuracy of structural simulations, such as NVH responses of high-speed traction motors and e-drive systems. Given the constituent material properties of the electrical steel laminations and the glue, this work distinguishes the governing mechanisms underlying the equivalent core properties. The in-plane stiffness is
Nie, Zifeng
Integrated Welding Simulation and Experimental Characterization of Weld-Metal and Heat-Affected-Zone Strength in AA6063-T62026-01-02304/7/2026
In the context of automotive lightweighting and efficient manufacturing, welding is a key joining method for aluminum body structures due to its maturity, versatility, and cost effectiveness. This study investigates MIG butt welding of AA6063-T6 sheets using a sequential thermo-mechanical finite element model with a double-ellipsoid heat source. Thermocouple histories and macroscopic metallography of the weld-pool morphology are used to validate the predicted temperature field, and post-weld deformation measured by a coordinate measuring machine is compared with the simulation to confirm overall model reliability. Hardness mapping across the joint partitions the material into weld metal (WM), heat-affected zone (HAZ), and base metal (BM). Miniature tensile specimens extracted along the weld provide local mechanical properties, from which linear strength–hardness relations are established. Building on these results, a five-material equivalent strength model covering WM, HAZ-I, HAZ-II
Shao, Jiyong, Meng, Dejian, Xiang, Yao, Gao, Yunkai
Kissing Bonds Inspection by Comparing Natural Frequencies Using Digital Holography2026-01-02074/7/2026
Accurate detection and evaluation of kissing bonds in composite materials is essential to ensure the integrity of the component structure, but traditional NDT (non-destructive testing) methods struggle to identify imperfect bonds and zero-volume debonds. In this study, a vibration analysis method based on holography was applied to detect kissing bonds by monitoring the changes in natural frequencies of the same sample before and after fatigue loading. Both pristine and kissing bond samples were tested under identical conditions, and their vibration characteristics (natural frequency, amplitude, and mode shape) were measured using holography. The experimental results show for the intact sample exhibited no changes in natural frequency amplitude or mode shape after fatigue loading, confirming that the applied fatigue test did not affect the integrity of its adhesive layer. In contrast, for the sample with a kissing bond, after fatigue loading, the natural frequency decreased by up to 22
Gao, Zhongfang, Fang, Siyuan, Gerini-Romagnoli, Marco, Yang, Lianxiang
Adhesion Strength of Coatings in Battery Structural Joints2026-01-02384/7/2026
In the design of Rechargeable Energy Storage System (RESS) structures, including battery trays, module side plates, and end plates, there are multiple conflating factors, including: Mechanical requirements necessitating the use of electrically conductive materials (steel and aluminum); proximity between battery module structure and battery cells, necessitating the use of electrical isolation coatings; and, module and pack designs that retain cells via the use of Structural Adhesive Material (SAM). Inherently, with this design approach, organic coatings are placed in a new and perilous position. In a sense, the coating becomes a supplement to an adhesive. As Computer-Aided Engineering (CAE) virtual analysis tools become more sophisticated, there is increasing reliance on these tools to predict the occurrence of structural failures in various load cases. Factors in test method, paint pretreatment, and topcoat affecting adhesion of organic coatings in structural adhesive joints are
Moceri, Charles, Harper, Jared
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