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DESIGN & STATIC STRUCTURAL ANALYSIS OF COMPOSITE PROPELLER SHAFT: A COMPARATIVE STUDY2026-26-0297To be published on 01/16/2026
Advanced Fiber Reinforced Polymer (FRP) composites have emerged as an important class of engineering materials for load bearing applications with all round properties for many engineering and social applications. Composite materials are created by combining two or more dissimilar materials with a viewpoint to improve the properties or to create materials with desired properties. Substituting composite structures for conventional metallic structures has many advantages because of higher specific strength and stiffness of composite materials. The role of composite material in weight reduction and fuel saving in automobiles is highly significant. Advanced composite seems ideally suited for long, power drive shaft applications. Their elastic properties can be tailored to increase the torque and the rotational speed at which they operate. Composite driveshaft is designed based on filament winding technology for higher strength and torque applications. In the present work, a comparative
Indla, Veneil Sai, REDDY, NEERATI, Kopparapu, Laxmi kanth
Composite Secondary and Tertiary Structure for Landing Gear AIR6827 (Current)11/26/2025
This document will contain guidance and considerations for the use of composite materials on non-primary structure for landing gear systems. Content to include design considerations, conditions and applications where composites are feasible/beneficial, high-level descriptions of various manufacturing processes, and certification/validation considerations.
A-5B Gears, Struts and Couplings CommitteeNEW
Development and Qualification of Composite Landing GearsAIR5552A (Current)11/26/2025
This information report provides general guidance for the design considerations, qualification in endurance, strength and fatigue of landing gear using composite components as principle structural elements. The information discussed herein includes the development and evaluation of design data considering: the potential for imbedded manufacturing defects, manufacturing process variations, the component operating environment, potential damage threats in service, rework and overhaul, and inspection processes. This AIR mainly discusses the use of thick composites for landing gear structural components. Considerations and recommendations provided in this AIR may therefore differ greatly from considerations and recommendations found in widely accepted composite design references such as CMH-17 and Advisory Circulars such as AC 20-107(B).
A-5B Gears, Struts and Couplings CommitteeNEW
Cast Aluminum Alloy Composite 4.6Cu - 3.4Ti - 1.4B - 0.75Ag - 0.27Mg (205.0/TiB2/3p-T7P) Sand Cast, Solution, and Precipitation Heat TreatedAMS4482B (Current)11/25/2025
This specification covers a dilute aluminum/TiB2 metal matrix composite in the form of sand castings.
AMS D Nonferrous Alloys Committee
Cast Aluminum Alloy Composite, 4.6Cu - 3.4Ti - 1.4B - 0.75Ag - 0.27Mg (205.0/TiB2/3p-T7P), Investment Cast, Solution and Precipitation Heat TreatedAMS4471C (Current)11/25/2025
This specification covers a dilute aluminum/TiB2 metal matrix composite in the form of investment castings.
AMS D Nonferrous Alloys Committee
Selection of suitable lightweight materials for various Automotive Vehicles and their components through Advanced Computational Investigations 2022-01-040703/29/2022
Generally, most of the fractions are occurred because of a lack of resistivity knowledge in internal structure level at abnormal loading conditions such as shock load, impact load, aerodynamic load, etc. Aforesaid loads drastically affect the structural performance of a component. The detailed pre-defined study about aforesaid loading environments and their side effects can provide the details of withstanding capability at peak loading conditions. This work examined the behavior of composite materials, which are subjected to sudden loading conditions at different real-time applications. Automotive vehicles and their components such as four-wheeler bumper, main bike stand, and automotive passenger bus are predominantly imposed these comprehensive investigations. The three primary different composites such as CFRP [Carbon Fiber Reinforced Polymer], GFRP [Glass Fiber Reinforced Polymer], and KFRP [Kevlar Fiber Reinforced Polymer] are selected and implemented under crash analysis with the
R, Vijayanandh, Gnanasekaran, Raj Kumar, Kulandaiyappan, Naveen Kumar, Raji, Arul Prakash, Madasamy, Senthil Kumar, Kesavan, Kandasamy, Subramaniam, Indira Prasanth
Moisture absorption behavior and hygrothermal aging life prediction for CFRP adhesive-bonded joints2022-01-038903/29/2022
Effects of moisture absorption on the strength degradation, energy absorption and failure mechanism of CFRP laminates and the adhesive-bonded joints in hygrothermal environment were investigated in this work. Experiments of accelerated moisture absorption, uniaxial tension and three-point bending were performed. SEM observations on the CFRP laminates and the fracture surfaces of the CFRP bonded joints were conducted. Strength degradation and failure mechanism induced by moisture absorption were discussed in detail. The results showed that the strength degradation in tension and in three-point bending of the CFRP laminate due to moisture absorption reached 7.4% and 17.1%, respectively. Different response of CFRP laminate and adhesive layer to the moisture determined the failure mode of the adhesive-bonded joints. Suitable match of CFRP laminate and adhesive was very important to make the failure mode of the joint under control.
Xu, Xianghe, Yu, HaiYan, Xing, Ping
Residual Stress Prediction of a Thermoformed Carbon Fiber Reinforced Polymer Structure Through a Novel Manufacturing to Response Pathway2022-01-032103/29/2022
Thermoforming of thermoplastic-based continuous carbon fiber reinforced polymer (CFRP) offers major advantage in reducing cycle times for large scale productions, but it inevitably induces certain undesirable effects in the formed parts. One such effect is residual stress. For a complex CFRP structure, the magnitude and state (tension/compression) of the residual stress could vary at different locations on the part. Several researchers have developed a number of techniques to experimentally measure the magnitude of these residual stresses, which have shown that these residual stresses could have considerable impact on the mechanical performance of complex CFRP structures, especially developed using thick laminates. However, the degree of impact of the residual stresses on the structural performance of the part still represents a knowledge gap. Experimental investigations could be performed to study the impact of residual stresses on mechanical performance but they are tedious and time
Limaye, Madhura, Pradeep, Sai Aditya, Kothari, Anmol, Agha, Akshat, Li, Gang
Effect of Material Anisotropy on Thermal-Mechanical Instabilities in Metal-Free Friction Materials2021-01-128910/11/2021
An anisotropic ceramic matrix composite (CMC), which consists of a silicon carbide (SiC) based ceramic matrix reinforced with carbon (C) fibers, is considered as a metal-free friction material replacement in brake and clutch applications. The fibers are assumed to have a circular cross-section, arranged unidirectionally and packed in a rectangular array without the presence of voids. The rule of mixture showed the C-SiC composite to be transversely isotropic with the circumferential plane as the plane of isotropy. A set of parametric studies have been performed to computationally investigate the dominant parameters that affect thermal-mechanical instabilities. It is found that the chance of thermal buckling in the friction disc can be minimized by reducing the elastic moduli in the radial and circumferential directions, or by reducing the coefficient of thermal expansion in the same directions. Meanwhile, the material properties in the axial direction do not have a significant effect
Shaahu, Joseph-shaahu, Koranteng, Kingsford, Yi, Yun-Bo
Mechanical and microstructural behaviour of friction stir welded Al6061/Cr2O3 metal matrix composite.2021-28-022410/01/2021
Aluminium metal matrix composite are widely used in various field like aerospace, marine and automobile application. The application of composites necessitates joining process and its difficult due to different materials. To address the considering difficulties the present study is, Cr2O3 was reinforced in Al 6061 matrix in 2% to 6% in the incremental step of 2%. The stir casting technique was used to fabricate the composites with 300rpm stirring speed and the stirring time duration was 3min throughout the fabrication process. The PCBN tool is used for prepared friction stir welded (FSW) joints and tool having 6.7mm pin diameter and 6mm pin height. The fabrication process is conducted by 1000rpm tool rotational speed and 25mm/min welding speed. The atmospheric and underwater environmental conditions was preferred to perform friction stir welding. The mechanical properties of the joint, such as tensile strength (ASTM E8), hardness (ASTM E18) and impact strength (ASTM E23) are
K, Senthilraj, Govindasamy, Rajamurugan, Krishnasamy, Prabu, Uday, KN
Assessment of tribological characteristics of stir cum Squeeze cast AlSi7Mg with 3wt % MoS2 and xwt % Flyash Hybrid Metal Matrix Composites2021-28-026010/01/2021
This research work aims to investigate the effect of SiCp and MoS2 lubricant particles on the tribological properties of AlSi7Mg alloy fabricated through stir casting and stir cum squeeze casting process. AlSi7Mg alloy is a supreme favourable industrial aluminium alloy owing to its exceptional casting ability, corrosion resistance and good strength to weight ratio. Stir casting is an effective and capable processing route for making aluminum composites with enhanced properties. Further to obtain improvised properties and pore-free structure aluminium matrix composites were fabricated through stir cum squeeze casting processing route. During the experimental investigation, AlSi7Mg alloy reinforced with 3 wt % MoS2 and 0, 5, 10 wt % of flyash is processed through stir casting and stir cum squeeze casting processing route. Tribological responses like wear rate and coefficient of friction were measured using Pin-on-Disc tribometer apparatus under dry sliding condition of load 10, 20, 30
A, Sathishkumar, R, Soundararajan, Siva krishna, Sneha, Ranjan prabakaran, Badma Rani
Evolution of A356 with flyash composites on metallurgical mechanical and tribological behaviour under dry and wet conditions2021-28-027210/01/2021
Among all metal matrix composites, A356 is the most applicable matrix due to its low density and exhibits nominal strength with soft nature. This proposed study is concerned with examination of mechanical and tribological behaviour of virgin A356 alloy and A356 reinforcement with 10wt.% power plant waste flyash particles composites were processed by liquid metallurgy stir casting technique. The fabricated composites expose enhanced higher hardness and compare the virgin A356 alloy due to presents of flyash particles in the matrix. The wear and friction behaviour of casted samples was tested in pin on disk tribometer apparatus under dry and wet sliding environment at the presence of lubricant (SAE 80W-90) by varying sliding load of 10N-40N and sliding velocity of 1-3 m/s respectively. Wear rate increase with the increasing load and sliding velocity. The usage of lubricant tends to decrease the wear rate by reducing the friction when compared to dry sliding method. This was ascribed due
R, Soundararajan, A, Sathishkumar, Kalaiarasan, Kaviyarasan, Kumar K, Sathish
Analytical Methods for Aircraft Seat Design and EvaluationARP5765B (Current)03/30/2021
This SAE Aerospace Recommended Practice (ARP) defines a means of assessing the credibility of computer models of aircraft seating systems used to simulate dynamic impact conditions set forth in Title 14, Code of Federal Regulations (14 CFR) Parts 23.562, 25.562, 27.562, and 29.562. The ARP is applicable to lumped mass and detailed finite element seat models. This includes specifications and performance criteria for aviation specific virtual anthropomorphic test devices (v-ATDs). This document provides a recommended methodology to evaluate the degree of correlation between a seat model and dynamic impact tests. This ARP also provides best practices for testing and modeling designed to support the implementation of analytical models of aircraft seat systems. Supporting information within this document includes procedures for the quantitative comparison of test and simulation results, as well as test summaries for data generated to support the development of v-ATDs and a sample v-ATD
Aircraft SEAT Committee
Carbon Fiber and Fiberglass Epoxy/Prepreg Products with 350 °F (177 °C) Cure for Aerospace Applications: Type 34, Class 4, Grade 294, Style 7781AMS6891/3 (Current)03/10/2021
The intent of this specification is for the procurement of the material listed on the QPL and, therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the quality assurance section of this base specification, AMS6891.
AMS P17 Polymer Matrix Composites Committee
Carbon Fiber and Fiberglass Epoxy/Prepreg Products with 350 °F (177 °C) Cure for Aerospace Applications: Type 42, Class 4, Grade 48, Style 108AMS6891/4 (Current)03/10/2021
The intent of this specification is for the procurement of the material listed on the QPL and, therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the Quality Assurance section of this base specification, AMS6891.
AMS P17 Polymer Matrix Composites Committee
Thermodynamic Analysis of Aeroderivative Gas Turbine Engine Featuring Ceramic Matrix Composite Rotating Blades2021-01-003303/02/2021
The quest for achieving more efficient gas turbine engine systems (GTESs) has led the researchers to try getting into many new dimensions of research. Simple Brayton cycle-based GTESs were coupled with recuperators, regenerators and reheaters to avoid/recoup heat energy from being wasted and these were designated as complex GTESs. Multistage compression (multi-casing) in axial compressors and multistage (two-cylinder) expansions in turbines paved the path to optimize the plant design for greater thrust to weight ratio and greater efficiency of the GTESs. Since the increase in efficiency of any power plant is directly or indirectly related to temperatures at which the plant cycle is being operated, this thermodynamic constraint had led to the development of high temperature materials such as single crystal nickel-based superalloys. To further achieve the increment in operating temperature, different blade cooling techniques were adopted and thermal barrier coatings were applied on
Rathore, Souvik Singh, Kar, Vishesh, S, Sanjay, Mishra, Shivam
Carbon Fiber and Fiberglass Epoxy Prepreg Products with 350 °F (177 °C) Cure for Aerospace ApplicationsAMS6891 (Current)12/30/2020
The intent of this specification is for the procurement of carbon fiber and fiberglass epoxy prepreg products with 350 °F (177 °C) cure for aerospace applications; therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the production quality assurance section (4.3) of this base specification, AMS6891.
AMS P17 Polymer Matrix Composites Committee
Carbon Fiber and Fiberglass Epoxy Prepreg Products with 350 °F (177 °C) Cure for Aerospace ApplicationsAMS6891-TEST-REC (Historical)12/30/2020
The intent of this specification is for the procurement of carbon fiber and fiberglass epoxy prepreg products with 350 °F (177 °C) cure for aerospace applications; therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the production quality assurance section (4.3) of this base specification, AMS6891.
AMS P17 Polymer Matrix Composites Committee
Carbon Fiber and Fiberglass Epoxy/Prepreg Products with 350 °F (177 °C) Cure for Aerospace Applications: Type 40, Class 1, Grade 196, Style 6K-PWAMS6891/2 (Current)12/29/2020
The intent of this specification is for the procurement of the material listed on the QPL; therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the Quality Assurance section of this base specification, AMS6891.
AMS P17 Polymer Matrix Composites Committee
Carbon Fiber and Fiberglass Epoxy Prepreg Products with 350 °F (177 °C) Cure for Aerospace Applications: Type 35, Class 1, Grade 191AMS6891/1 (Current)12/29/2020
The intent of this specification is for the procurement of the material listed on the QPL; therefore, no qualification or equivalency threshold values are provided. Users that intend to conduct a new material qualification or equivalency program must refer to the Quality Assurance section of this base specification, AMS6891.
AMS P17 Polymer Matrix Composites Committee
Design, Manufacturing, and Performance Standard for Composite Materials Used on Aircraft Seat StructuresARP6337-TEST-REC (Historical)11/18/2020
This SAE Aerospace Recommended Practice (ARP) defines additional documentation, environmental considerations, in-service damage limits, test and evaluation criteria necessary to support certification of aircraft seats manufactured using composite materials, in addition to requirements in AS8049 and ARP5526. This document is limited to aircraft seat composite parts in the seat primary load path from the occupant to the attachments of the seat to the aircraft. The term “composite” is inclusive of any fiber-reinforced polymer matrix materials such as carbon fiber-reinforced plastics, sandwich panels and bonded structure.
Aircraft SEAT Committee
Design, Manufacturing, and Performance Standard for Composite Materials Used on Aircraft Seat StructuresARP6337 (Current)11/18/2020
This SAE Aerospace Recommended Practice (ARP) defines additional documentation, environmental considerations, in-service damage limits, test and evaluation criteria necessary to support certification of aircraft seats manufactured using composite materials, in addition to requirements in AS8049 and ARP5526. This document is limited to aircraft seat composite parts in the seat primary load path from the occupant to the attachments of the seat to the aircraft. The term “composite” is inclusive of any fiber-reinforced polymer matrix materials such as carbon fiber-reinforced plastics, sandwich panels and bonded structure.
Aircraft SEAT Committee
All-composite EV wheel heads to production20AUTP10_1210/01/2020
Designed for EV and niche applications, the first commercially viable, low cost, lightweight, all-composite wheel moves to the next phase of development with a pilot production run. The product-development consortium, made up of Carbon ThreeSixty, Far-UK, Composite Integration and CNC Robotics, along with Bitrez Ltd as the preferred resin formulator, says it will manufacture 50 ACRIM (All Composite Reduced Inertia Modular) wheels by the end of 2020. The consortium announced three full vehicle sets are scheduled for proving on MOTIV, a unique and versatile autonomous vehicle (AV). The AV uses Gordon Murray Design's iStream Superlight technology (see www.sae.org/news/2020/02/motiv-av-pod for more on the gullwing AV prototype) and two sets of world-first overmolded RTM (resin transfer molding) wheels, which are headed for qualification testing. The consortium appears ready to challenge the world's most prominent source of production-vehicle carbon-fiber wheels, Australian outfit Carbon
Shuttleworth, Jennifer
Development and Qualification of Composite Landing GearsAIR5552 (Historical)09/17/2020
This information report provides general guidance for the design considerations, qualification in endurance, strength and fatigue of landing gear using composite components as principle structural elements. The information discussed herein includes the development and evaluation of design data considering: the potential for imbedded manufacturing defects, manufacturing process variations, the component operating environment, potential damage threats in service, rework and overhaul, and inspection processes. This AIR mainly discusses the use of thick composites for landing gear structural components. Considerations and recommendations provided in this AIR may therefore differ greatly from considerations and recommendations found in widely accepted composite design references such as CMH-17 and Advisory Circulars such as AC 20-107(B).
A-5B Gears, Struts and Couplings Committee
Executive Roundtable: 3D PrintingTBMG-3683705/01/2020
Process Development of Dissimilar Clinch Joints in Cross-Tension Specimens of AA5052 and TP-CFRP Sheets2020-01-022504/14/2020
This paper studied the process development of dissimilar clinch joints in cross-tension specimens of aluminum alloy 5052-H32 (AA5052-H32)/thermoplastic carbon fiber reinforced plastic (TP-CFRP) sheets. The AA5052-H32 and TP-CFRP sheets with a thickness of 1.6 mm were used. The important processing parameters for AA5052/TP-CFRP clinch joints, such as the punching load, heating mode, heating temperature, and die depth, were considered. The failure loads, failure modes, and metallographic micrographs of AA5052/TP-CFRP clinch joints were analyzed to determine an available processing parameter set for fatigue tests. Finally, the fatigue performance and failure mode of AA5052/TP-CFRP clinch joints were obtained.
Lin, Pai-Chen, Fang, Gavin, Lin, Chia-Wei, Ching, Yern Chee
Composite Suspension Leaf Springs: The Smart Solution2020-01-099104/14/2020
2020 SAE Congress - Technical Paper Abstract "Smart Solutions for Electric Vehicle Suspensions" Session: Steering, Chassis and Suspension Authors: Peter Kuhn, SGL Technologies GmbH, Meitingen, Germany William D. Pinch, SGL Technologies LLC, Charlotte, NC USA Abstract: Battery Electric Vehicles (BEVs) Programs are becoming the vehicle of choice globally. This is driven by heightened vehicle emissions requirements and improved fuel economy performance. Vehicle requirements will be rolled down to Subsystems and Components. Subsystem requirements will be divided into upper and lower control planes with Kinematic performance targets discussed. Various types of front and rear suspensions will be identified and analyzed including MacPherson & Chapman Strut, Short-Long Arm (SLA), and various Multi-link arrangements. At the component level the use of innovative, lightweight composite materials provides a significant advantage. Besides ensuring technical feasibility, implementation on high
Pinch, William, Kuhn, Peter
AFP Processing of Dry Fiber Carbon Materials (DFP) for Improved Rates and Reliability2020-01-003003/10/2020
Automated fiber placement of pre-impregnated (pre-preg), thermoset carbon materials has been industrialized for decades whereas dry-fiber carbon materials have only been produced at relatively low rates or volumes for large aerospace structures. This paper explores the differences found when processing dry-fiber, thermoset, carbon materials (DFP) as compared to processing pre-preg, thermoset materials with Automated Fiber Placement (AFP) equipment at high rates. Changes to the equipment are required when converting from pre-preg to dry fiber material processing. Specifically, the heating systems, head controls, and tow tension control all must be enhanced when transitioning to DFP processes. Although these new enhancements also require changes in safety measures, the changes are relatively small for high performance systems. Processing dry fiber material requires a higher level of heating, tension control and added safety measures. However, once these are achieved, processing rates and
Assadi, Michael, Field, Tyler
Effects of Helical Carbon Nanotubes on Mechanical Performance of Laminated Composites and Bonded Joints2020-01-002903/10/2020
Most composite assemblies and structures generally fail due to weak interlaminar properties and poor performance of their bonded joints that are assembled together with an adhesive layer. Adhesive failure and cohesive failure are among the most commonly observed failure modes in composite bonded joint assemblies. These failure modes occur due to the lack of reinforcement within the adhesive layer in transverse direction. In addition, the laminated composites fail due to the same reason that is the lack of reinforcement through the thickness direction between the laminae. The overall performance of any composite structures and assemblies largely depends on the interlaminar properties and the performance of its bonded joints. Various techniques and processes were developed in recent years to improve mechanical performance of the composite structures and assemblies, one of which includes the use of nanoscale reinforcements in between the laminae and within the adhesive layer. However
Sritharan, Ramanan, Askari, Davood
Advances in Drilling with PCD (Polycrystalline Diamond)2020-01-003503/10/2020
PCD properties were optimized to drill stacks of CFRP/Ti using an accelerated wear test milling gray cast iron. The optimized PCD was then used to prepare PCD drills. Tests were made to determine the best drilling conditions for the optimized PCD. The results yielded a significant improvement in cycle times as compared to earlier studies using PCD drills. Notched PCD cutting edges were found to eliminate oversizing of the CFRP near the interface of the two materials.
Bunting, Jeremy, Bunting, John
Advances in Drilling with PCD (Polycrystalline Diamond)2020-01-003503/10/2020
PCD properties were optimized to drill stacks of CFRP/Ti using an accelerated wear test milling gray cast iron. The optimized PCD was then used to prepare PCD drills. Tests were made to determine the best drilling conditions for the optimized PCD. The results yielded a significant improvement in cycle times as compared to earlier studies using PCD drills. Notched PCD cutting edges were found to eliminate oversizing of the CFRP near the interface of the two materials.
Bunting, Jeremy, Bunting, John
Silicon Carbide Fiber TowsTBMG-3597002/01/2020
Innovators at NASA's Glenn Research Center have developed a rapid processing method that produces stronger, tailored silicon carbide (SiC) tows and even heals damaged or otherwise low-quality fibers. Never before could poor-quality SiC fibers be healed and improved by this magnitude. This simple microwave process enables SiC tows and parts made from SiC fibers to be integrated in previously impossible applications while significantly saving costs.
Characterization of Friction Stir Processed Aluminum-Graphene Nanoplatelets Composites05-13-02-000701/23/2020
The present study deals with the investigation on microstructural and mechanical properties of friction stir processed (FSPed) pure Aluminum (Al)-Graphene Nanoplatelets (GNPs) composites. Composite specimens such as castings were made by blending 0.5 wt.%, 1.0 wt.%, 1.5 wt.%, and 2.0 wt.% of GNPs in pure Al matrix using the ultrasonic-assisted stir casting technique (UASCT). Also for enhancement of mechanical properties via grain refinement the friction stir processing (FSP) has been employed, as well as mechanical properties like tensile strength and microhardness were evaluated. Moreover, the microstructural analysis were done using Scanning Electron Microscope (SEM), Field Emission Scanning Electron Microscope (FESEM), transmission electron microscopy (TEM), and X-Ray Diffraction (XRD) examination were also performed for inspecting the changes occurred during synthesis of the fabricated composites after FSP. After FSP, the experimental studies exposed that a uniform plastic
Prakash, P. Bhanu, Krishnamachary, P.C., Varaprasad, K.C.
Thin Heat Shield for Superfast AircraftTBMG-3579101/01/2020
The world of aerospace increasingly relies on carbon fiber-reinforced polymer composites to build the structures of satellites, rockets, and jet aircraft. But the life of those materials is limited by how they handle heat. Researchers have developed a heat shield that better protects those extremely fast machines.
Environmental Barrier Coatings for Ceramic Matrix CompositesTBMG-3579501/01/2020
Innovators at NASA's Glenn Research Center have developed two durable environmental barrier coatings (EBCs) for use with ceramic matrix composite (CMC) components. CMCs are lightweight composites used to reduce fuel consumption in advanced gas turbines and other high-temperature, high-stress environments (up to 1482 °C). Glenn's breakthrough EBCs are the only coatings that can withstand such temperatures, protecting CMCs from increased wear and corrosion, oxidation, and water vapor recession in extreme environments. In addition, these EBCs can be fabricated with simpler and lower-cost methods than conventional coating processes such as plasma spraying.
Washable Sensor Can Be Woven Into MaterialsTBMG-3572612/01/2019
A low-cost sensor was developed that can be interlaced into textiles and composite materials, paving the way for smart clothing that can monitor human movement. The embedded microscopic sensor is able to recognize local motion through the stretching of woven yarns treated with graphene nanoplatelets that can read the body's activity.
Aerospace & Defense Technology: December 201919AERP1212/01/2019
Engineered Solutions for Enclosure Sealing and Insulation Tips for Reducing Error When Using Eddy Current Measuring Techniques Reducing the High Cost of Titanium Streamlining Post-Processing in Additive Manufacturing Software-Defined Analog Filters: A Paradigm Shift in Radio Filter Performance and Capability SDR Interface for the NeXtRAD Multistatic Radar System Electrodeposition of Metal Matrix Composites and Materials Characterization for Thin-Film Solar Cells Metal matrix composites, which consist of silver-multiwalled carbon nanotube-silver, layer-by-layer stacks, can electrically bridge the cracks (>40 μm) that appear in semiconductor substrates and the composite grid lines. Sensing Applied Load and Damage Effects in Composites with Nondestructive Techniques Comparing and correlating piezoelectrically induced guided waves, acoustic emission, thermography, and X-ray imaging to determine the effects of applied load on a composite structure. Technology Impact Forecasting for Multi
Electrodeposition of Metal Matrix Composites and Materials Characterization for Thin-Film Solar CellsTBMG-3566912/01/2019
The current trend in both space and terrestrial photovoltaics is to implement high-efficiency, thin-film-based solar cells to reduce weight and materials cost while improving performance. For space photovoltaics, multi-junction (MJ) solar cells have been used almost exclusively due to their high efficiency and high radiation hardness. The efficiency of state-of-practice triple-junction (TJ) cells used in space today is approximately 30% under 1-sun Air Mass 0 (AM0) spectrum.
Electrodeposition of Metal Matrix Composites and Materials Characterization for Thin-Film Solar Cells19AERP12_0712/01/2019
Metal matrix composites, which consist of silver-multiwalled carbon nanotube-silver, layer-by-layer stacks, can electrically bridge the cracks (>40 μm) that appear in semiconductor substrates and the composite grid lines. Air Force Research Laboratory, Kirtland Air Force Base, New Mexico The current trend in both space and terrestrial photovoltaics is to implement high-efficiency, thin-film-based solar cells to reduce weight and materials cost while improving performance. For space photovoltaics, multi-junction (MJ) solar cells have been used almost exclusively due to their high efficiency and high radiation hardness. The efficiency of state-of-practice triple-junction (TJ) cells used in space today is approximately 30% under 1-sun Air Mass 0 (AM0) spectrum. Multijunction technology involves stacking different bandgap subcells electrically and optically in series, connected by tunnel junctions, to effectively capture and utilize the solar spectrum. State-of-practice TJ cells consist of
Fabrication and Wear Characteristics Basalt Fiber Reinforced Polypropylene Matrix Composites2019-28-257011/21/2019
Generally brake pads are manufacturing by use of asbestos materials, that materials are chemically harmful and toxic nature to affect the human health. The present investigation is to fabricates polypropylene composites with mixing constant volume [5 vol.%] of alumina nano particles and different volume percentages [0%, 5%, 10% & 15%] of basalt Fiber by hand layup compression technique. The wear characteristics of polypropylene matrix composites were tested by dry sliding condition. The test was carried out pin on disc apparatus, configured with hardened steel counter-face at elevated temperature. The load was applied 10 N to 30 N with the interval of 10 N and varying of sliding speed 300 rpm to 900 rpm with the interval of 300 rpm for the time period of 0-180 sec. The wear rate was decreases with addition of alumina nano particle and the frictional force was increases due to basalt Fiber content present in the composites. The co-efficient of friction was increases 0.1 to 0.66 under
M, Krishnaraj, T, Thirugnana Sambandha, R, Arun, T, Vaitheeswaran
2019 'Create the Future' Aerospace & Defense Category Winner: A Morphing, Foldable DroneTBMG-3542611/01/2019
Experimental Investigation on Turning Characteristics of TiC/MoS 2 Nanoparticles Reinforced Al7075 Using TiN Coated Cutting Tool2019-28-016510/11/2019
In recent years, aluminum metal matrix composites (Al-MMC) are found as a potential material for numerous applications owing to its excellent tribological and mechanical properties. In this work, the machining characteristics of aluminum alloy (Al7075) reinforced with TiC/MoS2 having nanoparticle has been studied. The samples of aluminum metal matrix composites by varying TiC in 0, 2 and 4 and MoS2 in 0 and 2 of the percentage weight of aluminum alloy (Composite 1(Al7075), Composite 2 (Al7075/2TiC/2MoS2) and composite 3 (Al7075/4TiC/2MoS2), respectively) are fabricated by the stir-casing method. The turning characteristics of the developed metal matrix composites are studied at various parameters such as cutting velocity (30 m/min, 60 m/min and 90 m/min), cutting depth (0.5 mm, 1.0 mm and 1.5 mm) and composites (1, 2 and 3) using TiN coated cutting tool by dry turning at 0.05 mm/rev feed rate. The turning characteristics of the prepared samples are compared each other under L20
Kannan, Vetri Velmurugan, Kannan, Venkatesan, Sundararajan, Devendiran, Uday Kumar, Budireddy, Anvesh, Dhulipalla, Akhil, Varupula
Experimental Investigation of Silicon Carbide Nanoparticles Reinforced Magnesium Alloy (AZ91E) Metal Matrix Composite by Vacuum Stir Casting Method2019-28-016910/11/2019
In the present investigation silicon carbide nanoparticles reinforced magnesium alloy [AZ91E] composites were prepared by vacuum stir casting process in an inert atmosphere. Required amount of silicon carbide nanoparticles with grain size of 50nm was added into AZ91E molten melt with constant stir speed of 600 rpm and vacuum pressure of 1 lpm to obtain magnesium alloy composite containing 0, 5, 7.5 and 10 wt.% SiCp nanoparticles. The prepared composites were subjected to mechanical and microstructure studies. The mechanical properties were found to increase with the addition of silicon nanoparticles compared to unreinforced magnesium alloy. The maximum impact strength, yield strength and tensile strength were found to be 29.13J, 156 MPa and 401.13 MPa respectively. Microstructure studies reveal uniform distribution of silicon carbide in magnesium alloy matrix.
Thangavel, Thirugnana Sambandham, Jeyaseelan, Chandradass, Paramathma, Baskara Sethupathi, Mahadevan, Kannan
Surface Modification of Aluminium Alloy 5083 Reinforced with Cr 2 O 3 /TiO 2 by Friction Stir Process2019-28-017910/11/2019
The surface properties have a vital role in the overall performance of the parts like brake shoe pad and other frame system. The mechanical and residual stress measurements of aluminium alloy 5083 were investigated on friction stir processed plates using the reinforcements of chromium oxide (Cr2O3) and titanium dioxide (TiO2) separately as well as combination of these powders. A comparative study was made to analyze the effects of reinforcements, tool type (cylindrical and threaded), parameters and the volume fraction of the reinforcements. The mechanical properties such as surface hardness and residual stress of the friction stir processed specimens were investigated. The experimental results shows that there was a significant increase in surface hardness (118 HRC) as well as a decrease in residual stress compare to the base metal. This study also reveals that the threaded tool with a reinforcement of Cr2O3 and TiO2 reflected better mechanical properties than the cylindrical tool. The
Singh, Adarsh, Rajamurugan, Govindasamy, Krishnasamy, Prabu, Dhanabalan, Dinesh
A Comparative Study on Microstructures and Mechanical Properties of Al-GNPs Composites Fabricated by Casting Method2019-28-013910/11/2019
This paper describes an investigation on microstructures as well as mechanical properties of pure aluminium graphene nano platelets (GNPs) metal matrix composites prepared via novel based stir casting technique combined with ultrasonic treatment. The proportion of graphene changes from 0.5 to 2.0 wt. % in aluminium with 99% purity. The investigations on composites revealed that Al with combination of 1.0 % graphene composite showcased enhanced mechanical properties with 48.49 % (~49%) increase in tensile strength and 34.53 % (~35%) increase in micro hardness compared to test results of composites produced by traditional stir casting technique. FESEM analysis was done to examine the surface morphology of produced composite and fracture surface of tested composites where as XRD analysis was to inspect the phase analysis of produced composites. It reveals that, through cavitational effect there was a uniform distribution of graphene in aluminium matrix and composites were casted with less
Palampalle, Bhanu Prakash, Chinna, Krishnamachary Pattipati, Selvi, Binoj Joseph
Mechanical and Corrosion Behaviour of Al 7075 Composite Reinforced with TiC and Al 2 O 3 Particles2019-28-009410/11/2019
Various research regarding new types of fabrication and modifications of Aluminium alloy to improve the existing properties are going on. The wide range application of aluminium alloy is in aerospace and Automobile Industries. The demand for this material improved by mechanical properties with little to zero increment in weight. The current work is based on the fabrication of hybrid aluminium metal matrix composites with the addition of TiC (Titanium Carbide) and Al2O3 (Aluminium Oxide) reinforcement particle using stir casting technique. Three types of hybrid composite samples were prepared based on the weight percentage 5% Al2O3+0% TiC (sample-1), 8% Al2O3 + 12% TiC (sample-2), 20% Al2O3+15% TiC (sample-3). The objective of the study is to analyze the mechanical and corrosion properties of the hybrid composite with the influence of the reinforcement and varying the weight fraction of the particles. Overall, It is observed that a gradual increase in the hardness value in sample-1(83
Jaiswal, Subham, Rajamurugan, Govindasamy, Krishnasamy, Prabu, Shaswat, Yashwardhan, Kaushik, Mishra
Characterization of Areca and Tamarind Fiber Reinforced Hybrid Polymer Composites for Structural Applications2019-28-016810/11/2019
Recently, owing to the noteworthy properties like biodegradable, low cost, readily available, easy processing, less toxic and eco-friendly nature natural fibers reinforced composites are used in different engineering applications. Nevertheless, the traditionally used synthetic E-glass fiber composite shows inverse features than that of reported natural fiber composites. Hence, in the current investigation discarded areca and tamarind fibers was collected, extracted and characterized for its overall performance and to implement it as a better alternative for artificial fiber composites. Composite coupons were made with different magnitudes of fiber/matrix and inspected for their potentiality by exploring its mechanical and thermal assets as per standard techniques. The developed areca and tamarind hybrid composite results shown better part than their individual composites and also in par with the prevailing synthetic fiber products. Hence, the tested results shown that the fabricated
Joseph Selvi, Binoj, Natarajan, Manikandan, Palampalle, Bhanu Prakash
Damage Analysis of Composite Laminates2019-28-009210/11/2019
The favorable mechanical properties of Composite materials are excellent stiffness/weight and strength/weight ratios, easy formability and corrosion resistance. The application of composites in structural components is still limited by the difficulty in predicting their service lives. The objective of this research paper is to develop and evaluate damage initiation or delamination onset and growth in a C-C composite 8 layered pre-preg material 3D laminate model (dimension 25x3.4x85mm and ply thickness 1mm) under loading conditions without crack using ANSYS Autodyne tool subjected to a uni-axial load of 40N at the free end. Mapped quadrilaterals mesh is generated with 2610 nodes and 1792 elements. Cohesive Zone Model (CZM) formulations are more powerful than Fracture Mechanics approaches because they allow the prediction of both initiation and crack propagation. The composite laminate plate is thus bent due to Poisson effect, and crack opens up due to the heavy normal stress at the
Rajamani, Palaniammal, Kumar, Nathi Venu
Investigation of Dry Sliding Wear Behavior of AA8011 Reinforced with Zirconium Oxide and Aluminium Oxide Hybrid Composites Processed through Multi-Direction Forging2019-28-005710/11/2019
The Cardinal goal of this research work is to fabricate hybrid composites of AA8011 with reinforcement particles of Zr2O3 and Al2O3 which was taken in equal (5wt%) weight percentage. The hybrid composites were cast in a square shape (50x50x50 mm size) under the optimal stir casted process parametric condition, further, it was taken for the forging process. The prepared specimens were induced for uni-direction (x), bi-direction (x and y) and multi-direction (x,y, and z) forging route and the response of microhardness of 53, 68, 81 and 96 VHN were obtained respectively due to microstructural phase changes with an even distribution of particles in the matrix. Thus, the tribological properties of prepared specimens were tested using pin-on-disc Tribometer at room temperature under dry sliding condition of load 5,10,15,20 N and by adjusting the sliding speed as 266 and 531 rpm respectively. The outcomes uncovered all the specimens that the wear rate increments with an increase in load and
Kuppuraj, Sathishkumar, Ranganathan, Soundararajan, Aruchamy, Sathishkumar, Gopal, Shanthosh
Fabrication and Machinability Study of Al2219 Metal Matrix Composites Reinforced with SiN/MoS 2 Nanoparticles2019-28-017010/11/2019
Composites materials are substituting constituents for traditional materials due to their remarkable properties, and the addition of nanoparticles gives a new development in the material domain. The nanoparticles influence on fabrication and machinability investigation study is essential as the composites to be used in applications like automotive and aerospace. The current study investigates the machinability characteristics of Al2219 based metal composites reinforced with nanoparticles of SiN/MoS2. Al2219- reinforcements (SiN and MoS2) composites are fabricated by the method of stir casting. Four different compositions (Al2219/SiN (2 wt% and 4 wt%), , Al2219/2 wt.% SiN/ 2 wt.% MoS2, Al2219/2 wt.% MoS2) are fabricated by varying the different weight percentages of nanoparticles reinforcements. An attempt is made to study the investigation analysis of force, surface roughness, and tool wear using CNC machine lathe to consider the effect of cutting speed, cutting depth, and samples. The
Kannan, Vetri Velmurugan, Kannan, Venkatesan, Sundararajan, Devendiran, Seth, Akshay, Sood, Navya, Babu, Aditya
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