Questions related to Composite Material
I'm currently working with fe-safe and noticed that it predominantly features a metal material database. I'm interested in analyzing composite materials in my project. Could anyone guide me on how to add a composite material database to fe-safe? Any help or resources would be greatly appreciated.
Thank you in advance for your assistance!
For example. Coir or coconut husk fibers are short. How can make a continuous fiber out of it. Idea is to prepare unidirectional continuous coir fiber polymer composite.
Dear predecessors, I am applying different constitutive relationships to the fibers and matrix of composite materials through umat. The matrix is subjected to cyclic plastic coupling damage, and both constitutive relationships can be verified by individual units. Two umats make up a single umat that cannot converge. What is the problem? I hope everyone can provide some guidance
Finite element method will be used to determine the stress-strain of a 3D composite material made structure.
Effect of fibers in composite materials on its strenght
I am writing a thesis on this topic.
What references do you recommend? What theory should I use to model unsteady aerodynamics? Is it better to use software or coding? Please share some insights.
more description of phenomenen is for the limits of human body ,and the acceptation of resistance composante of differents fonction of the part of body, such us ;in accident the many people to lost in part of body and the medecine not have any idea for complete the human body ,so choce the composite material's for complete the humain body. another example is in dental medecine after the body lost the tooth not have a solution to rebuilt another tooth artificielle in zironuim or composite material mixed.
I hope to understand my question, because the many problem due to of the fact,and many player ,actor,populary people suffer from the illness which human body not complete! may be the interesting of medecine and artificielle intellegence is doing a good work in different field in life ,but the mechanical is the specialist in fiel of comptability of resistance ,so i not have the thing a add ,lookin forward to tho question soon
For my research purpose I need a Composite 3D printing filament.
Please share the cost details to manufacture a 1Kg filament using a twin screw extruder.
And share the combination of filament already fabricated using a twin screw extruder.
And Share the detail of twin screw extruder availability in India. My location is Vellore, Tamilnadu, India. Please share the nearest availability of twin screw extruder.
I am working on magnetoelectric multiferroic composite materials. When I did ME measurements, I'm getting this type of invert behavior for one composite material. what could be the reason for this invert behavior? Please tell if anybody have any idea about this ..
Thank you in advance for your explanation
I have older version of x'pert highscore software and what to do for pdf2, pdf 4? Please suggest me or share the link of x'pert highscore software latest version (free)/ free pdf2, pdf4.
Respected all Researcher.. I hope everything is okay with you all. Actually, we are developing a medical component for use with a CT scanner, and we are looking for a radiolucent composite or plastic material to build the component. Could you kindly direct us to where & how we may obtain this material?
I require few tips regarding matching the numerical model of drop weight test with the experimentally obtained data.
I will briefly discuss the drop weight model here. I have modeled a drop weight test on ANSYS workbench. The impact velocity is 2.653 m/s. The impact is happening on a rubber/jute epoxy composite which consists of 2 layers. The upper layer is rubber with modulus of 10 MPa. The lower layer is Jute epoxy composite.
The experimental drop weight curve is already obtained. The material properties of jute epoxy composite are obtained using U20MM software. Some of the stress limits of jute composite (Tensile strength, compressive and shear strength) are obtained using literature. The jute epoxy composite and rubber is modeled as solid plate. The current mesh is coarse. Please note rubber is not modeled using hyperelastic model to avoid complexity. Please see the attached file to see the force vs time curve and the difference in experimental and numerical data. Blue curve is obtained numerically.
Can anyone provide few tips in tuning the material properties/model to match the numerical data with experimental curve.
There are articles that belong to me, but you attributed them to someone else :
- Study by genetic algorithm of the role of alfa natural fibre in enhancing the mechanical properties of composite materials based on epoxy matrix
Ziani, N., Boudali, A., Mokaddem, A., ...Beldjoudi, N., Boutaous, A.
Fibres and Textiles in Eastern Europe, 2016, 24(3), pp. 58–62
- Prediction by a Genetic Algorithm of the Fiber–Matrix Interface Damage for Composite Material. Part 2. Study of Shear Damage in Graphite/Epoxy Nanocomposites
Mokaddem, A., Alami, M., Ziani, N., Beldjoudi, N., Boutaous, A.
Strength of Materials, 2014, 46(4), pp. 548–552
I am currently studying the effects of mechanical properties of GO and rGO on PC/ABS. However, after analysing the data, I found that the tensile strength decreasing, but, for the flexural strength, the data shows and increment when the compatibilizer added into the system.
I have not yet found any answer on this matter. Is there any scientific reasons that can cause this or is it because of the equipment error?
Currently reading a paper about silicone rubber/filler material composite. The paper says the PHR of the prepared composite is 5. Later, the paper explains that composite having the PHR value of 5 is also having the value of 5wt% filler material. Is it possible for PHR and wt% to have a same numerical value in a single composite like this?
To produce a composite material, how will I weigh the components mentioned above if I want to make this mixture?
I have changed the code of the unifiber.for which is given by abaqus, for obtaining the CDM. Only the code of stiffness and the criterion, I have changed and I use the strain to replace the stress for the hashin 3d ，but the model don't run well . In my prediction, only the tensile damage for the matrix is very serious .in fat ,the deletion of the element is very serious, the result is wrong. I don't know what is wrong with my code. I hope somebody who is good at the vumat , can give me a hand, I will really really thank you .
this is my code.
How do you calculate the electrical and mechanical properties like shear modulus, electrical resistivity, and conductivity of graphene and carbon nanotube composite materials?
What are the critical rules to pay attention during manufacturing masterbatch especially when working with inorganic nanoparticles? What should be considered in order to achieve the homogenously dispersion in the polymer matrix without destroying the screw and the polymer?
Nanoindentation is a attachment with AFM or it is a separate testing procedure? Nanoindentation gives property at nanolevel? Young's modulus, Hardness, Stiffness, Load vs Depth, Load Vs Hardness properties alone cane be obtained using nanoindentation or any other properties can also be known using nanoindentation? Where I can get all these things done in India? Please share your suggestions. Many of the prestigious institutions saying machine under maintenance, machine not working or operator not available.
How one can design a course on composite material with machine learning and/or artificial intelligence?
What will be the course content?
I study the delamination of laminates upper and bottom skins of honeycomb composite structure simple supported from two sides and under bending stress.
I consider the developed tension on the bottom skin as the main peeling force that cause delamination.
Is my thinking correct?
Also, do you suggest textbooks?
Is it compulsory that the specimen has to fail exactly at the center or gage length ? In my case out of 12 specimen only 2 fail within the grip area, but remaining fail in the gage length area but not exactly at the center.
I'm doing a compression test on four self-reinforced composites
1- PET / PET
2- PLA / PLA
3- CARBON / PET
4- GLASS / PET
fabric style 2x2 twill weave woven
I need the required properties to add them in Ansys library for analysing
I am writing UMAT subroutine in ABAQUS to analyze the damage of the microscale RVE model(Fig.1 including fiber and matrix).However, the calculation to the damaged part doesn't converge or no results are output, even the DSTRAN appears NAN(Fig.2).
The UMAT.for has been judged by adding " IF...THEN END IF " statements of multiple materials according to the Abaqus help documentation(Fig.3). The two subroutines, including Fiber damage & Matrix damage, have been verified to work. I'm not quite sure if this flow is correct.
Could someone please tell me how to use one UMAT subroutine to correctly analyze the damage of the different components of the RVE model ? Or please provide some relevant solutions about realization of multiscale analysis of composites. Thanks all for your help.
In tensile testing, how is percentage elongation at break which is measure of ductility is expressed as universally ? Is it (displacement/gage length)*100 or (change in length/gage length)*100 ? Say, displacement is 2 mm and gage length is 130 mm, then according to former equation, percentage elongation is 1.5% and as per latter, it is 101.5%.
I am doing an Explicit Impact Analysis on GFRP component. I am getting an error message saying "Minimum Time Step too small". Can anyone please tell me how I should solve this error? According to the Ansys manual, I tried to change the Erosion Controls by changing the Geometric Strain Limit. The problem is solved temporarily, but I am not understanding what exactly this Geometric Strain Limit signifies. What happens when I increase or decrease the value of the Geometric Strain Limit?
Hi Guys, I want to conduct the material nonlinear analysis of composite laminate , which is carbon fiber reinforced epoxy composite materials, using ABAQUS .However, in abaqus only have elastic linear properties for composite material. the question is, how to manually input/write the properties of nonlinear material in terms of shear stress and shear strain in abaqus input file? Thank you
Compression test to composite materials needed to be simulated by Ansys but the material doesn’t exist in Ansys library
I have immersed some composite material specimen in artificial seawater. I need to check if the material is leaching into the water. Basically to check if some hydrocarbon of epoxy is present in the artificial seawater. Which technique should I use ?
Let's discuss an interesting topic and share ideas on the following question:
which method do you prefer to track damage in a composite material or a bonded joint?
There are different known methods such as strain measurement by the strain gauges, piezoelectric sensors, DIC, optical fibers, and X-ray tomography.
So, please give a feedback on your opinion about the advantages, disadvantageous, and any challenges faced with each method. Tell me about your experience...
I am trying to do a static analysis of a torque box using shell elements and I have the following issue.
I have modeled the Boeing 737 wing (torque box) in Autodesk Inventor using surfaces.
Then I transferred it in Ansys Workbench to start the FEA analysis.
However, I want the inner structure of the wing to be made using composite materials.
So, I opened an ACP module. In that module, I cannot hide some surfaces and here's where the problem is.
If I can't hide them, then I cannot select the ribs and apply an Oriented Selection Set.
I tried, also, making three different ACP modules and then assembling them in static structural (transferring shell data) however that results into an error.
I have attached my project file, without the ACP module.
I have tested a sample of bulk fill dental composite for mechanical features and the results are confusing. The compressive strength should be lower than the flexural strength in majority of materials including dental composites and it has been reported in previous researches. Testing conditions are mentioned below. have anyone faced this problem? does anyone know how to fix it?
3 point flexural test: (as mentioned in ISO4049)
sample dimensions: 2*2*25mm
distance between fixtures: 20mm
cross head speed: 1mm/min
curing protocol: 9 points on each side, each 15s
sample dimensions: cylinder d=4, h=6
cross head speed: 1mm/min
curing protocol:15s on each side, 15s on two points of lateral sides
Hi, I am working micro mechanical analysis of the composite material by using GTN model. I am encountering the macroscopic and microscopic local phenomenon in the composite is completely depends on the type and arrangement of element. I would like to suppress this mesh dependency of solution in the GTN, could you please let me know is there is any possible method to over this issuse, without using UMAT or UEL. If possible , could any one share their UEL or UMAT code for nonlocal GTN model
I am using different cement composites as backplate and simulating the functional layer matrix using SCAPS 1D. The only parameter for the backplate I have is the Conductivity of composite material. The scaps require input parameters as attached file. How should I be able to input the values?
Many analytical approaches have been developed over the years , and comprehensive bibliographic studies have been published on the prediction of E2,G12,Poisson's ratio of unidirectional composites. in The Halpin-Tsai equation 𝜉 is an empirical factor, which measures the reinforcement of the fibers of the composite material which depends on the geometry of the fiber, the arrangement of the fibers and the loading conditions. In generally, 𝜉 may vary from zero to infinity. taking 𝜉=2 to calculate E2 and 𝜉=1 to calculate the shear modulus G12
I am looking for the value or the equation to determine 𝜉 to determine the Poisson's ratio v23 ?
As a kind of renewable non-metallic material with excellent performance, polymer has been increasingly widely used in the design and manufacture of parts in various industries. Traditional metal parts are increasingly replaced by polymer parts with the same performance. In the automotive, aerospace, transportation and other industries, the demand for lightweight is particularly strong, which has spawned a variety of polymer products to replace metal, and also put forward higher requirements on the connection technology and quality between polymer parts. Welding has always been the most effective way to permanently connect polymer components. Traditional polymer welding processes are mostly ultrasonic welding, vibration friction welding, hot plate welding, etc. The problem lies in certain limitations of welding methods, such as: Poor welding quality, low production efficiency, difficult to achieve complex shape welding, serious environmental pollution, short life, follow-up treatment and other problems have been plaguing people in the polymer industry.
Nowadays, with the continuous innovation of laser processing technology and the continuous development of composite materials, the emergence of polymer laser welding just makes up for the defects in this aspect, and will gradually replace the traditional polymer connection with its obvious advantages.
However, material limitations remain an important issue in polymer welding. The researchers are looking at LTW in polymer combinations that are difficult to weld due to varying degrees of incompatibility.
Is there any new progress in the understanding of laser welding polymer?
A composite material comprises both non-conducting and conducting parts then how to measure the current density of 10 ul of the solution of the composite material to carry out the Galnostatic charge and discharge experiment.
In order to analyze the effect of moisture absorption on mechanical properties of composites, need to follow ASTM D5229 and immerse in water till the composites saturate with moisture. This consumes time, 2-3 or even 6 months. Is there any other accelerated water absorption process which simulates the normal water absorption but at a different scale ? I cannot increase the water temperature beyond 40 degree celsius because ASTM recommends the water temperature to be 25 degree celsius less than the glass transition temperature.
I have tried to cure the CNSL resin with a Hot air oven of 180 degrees Celsius. Still, I am not getting the proper solidification of the resin, the specimen which is kept in a Hot air oven is in a spongy state. I want to know the process/ steps/ procedure for curing the CNSL resin?
I need Pineapple leaf fiber to fabricate composite material for research purpose. Where can I buy it from ?
I'm a currently searching what effects does the environment humidity during manufacturing have on the composite final properties. Most recommendation gives a 40-60% humidity, and I see how a humid environment could corrupt the matrix integrity but i don't see the problems a dry environment could cause.
Is anyone familiar with this subject ?
In the literature pertaining to sandwich panels, we often come across terms like "sandwich panels with a stiff core" and "sandwich panels with a soft core". How do we formally differentiate between these two? While the name itself suggests that for a stiff core the ratio of the shear modulus of the core to that of the face sheet is higher than the same ratio for a soft core. But is there any well-defined condition wherein which we can differentiate between a sandwich panel having a stiff core and one having a soft core?
I would also appreciate your suggestions/corrections on another point. As per my understanding for a stiff core, equivalent single layer theories based on FSDT or Reddy's Third Order Theory may give sufficiently accurate results. But for a soft core, refined higher-order theories usually with layerwise displacement assumption may be required for an accurate analysis.
The weaved fiber I have is plain weaved bi-directional natural fiber. I need find its tensile strength. The ASTM standard D3039 applicable to PMCs is not applicable to weaved fibers, fiber mats, etc. D5587 − 15 trapezoidal method of determining tear strength applies to most fabrics including woven fabrics, air bag fabrics, blankets, napped fabrics, knitted fabrics, layered fabrics, pile, and nonwoven fabrics. Am I technically correct in using this standard ? Have anyone used this standard before ? Please share your experience.
How do I find chemical composition of natural fiber. Since cellulose, hemicellulose are all organic containing C, H and O elementally, how to find the chemical composition not elemental which can be determined from SEM-EDX.
Can you recommend the Journal name with Sci index for the Natural composite materials for short period publication ?
In the near future some non-biodegradable materials will be replaced in production processes for other, biodegradable. For example, plastics in the European Union until 2021 are to be withdrawn from packaging and replaced with other biodegradable materials such as paper or packaging produced from food, eg from cereals. But this is just the beginning of the revolution in the development of pro-ecological material innovations. This is only the first step towards the withdrawal of plastic as one of the main factors of littering the natural environment.
Do you know other types of examples already implemented or planned to implement projects to replace plastics with biodegradable materials?
Which biodegradable materials will be replaced in the future by plastic that is being phased out of production?
Please, answer, comments. I invite you to the discussion.
Dewetting point is the limit after which any further increase in strain will result in permanent damage (plastic behavior).
Polymer matrix laminate composites are lightweight ant strong, and probably with some metal cladding/sandwiching of Aluminium or Titanium alloys may be used for Airplane outer body, especially the upper side. Now, the immense-sized and curved upper surface of airplane seems not to be feasible to be made as a one-piece laminar composite, owing to this vast size. So, there are likely needs to attach the composite panels with one another to make the outer body of airplane. So, how these panels are joined? and how provisions to attach wings and propeller as well as metallic contacts are provided in the composite panels. That is, what are composite-to-composite and composite-to-metal joining techniques from outer body of airplane, especially the upper half?
I intend simulating a composite material of CaO added with nano Al2O3. I'm wondering if it is feasible to create the Al2O3 nanoparticles in LAMMPS. Can someone give some insight please?
I have developed a particle reinforced metal matrix composite for a specific application that require a static,dynamic and couple field analysis. May I know the procedure to perform these modelling and analysis of MMC products using Ansys or any other specific software.
please suggest me the Q1/Q2 journals having high acceptance ration and deals with the synthesis and characterization work under material science, composite materials and manufacturing domain.
Can anyone suggest some useful methods for preparing PEEK based or PEEK reinforced composite materials?
I hope you're doing well and safe...
i have some doubts about the area of the composite material.....
in the composite material making process there are several reinforcement techniques they are using so please share what are the reinforcement methods using and its effectiveness
As every keyword have certain experts associated with it, based on their area of expertise. Can we initiate a devoted section for research collaboration, especially for the calls requiring bilateral or multinational collaborator?
Presently, My group is looking for a German collaborator in the area of " High performance based C-C composites" on following call "http://www.dst.gov.in/sites/default/files/DST-DFG-JointCall-10AUG2018.pdf"
Finding it difficult to have a relevant and interested group from Germany. kindly text me if anyone finds this call interesting.
Please share how I should proceed to search for interested researchers from Germany, My present approach is searching research papers on said area and mailing to the researcher if find relevant.
Peak values over a broad range of 2theta is obtained. This is to obtain d spacing values for layered silicate in a polymer. Now to find d spacing which value of 2theta should I consider ? What could be the reason for this phenomenon ?
Hi! When I read the paper Progressive damage modeling in fiber-reinforced materials by I Lapczyk, JA Hurtado, I am wondering why Hashin failure is evaluated in the effective space instead of true stress space. What is the consideration here? Besides, I found that many other papers focusing on meso-scale modelling of composite laminate are ambiguous on their choice between these two stress spaces? Any thought? Thx!
Do works exist about magnetic permeability calculation of ferromagnetic composite materials such as SMC or mixe of iron powder and epoxy at lower density of iron than SMC?
Inquiry regarding the reduction of hardness value at the center of nugget for friction stir welded SiC particle reinforced Al matrix composite material.
Here I have attached the variation of hardness of samples (hardness taken through out the center of the nugget from one side of the base material to the other side. An unusual observation is made here that at the center of nugget there is a steep decrease in hardness, which is contrary to the general observation with increase in hardness value at the center of nugget. Kindly suggest me some possibilities behind such observation. Your valuable advises will be very much helpful for me to proceed further.
Could you please suggest me some rapid publication ISI journal list in nanotechnology, thinfilm (namely composite material, compound semiconductor thinfilm) with impact factor range from 1.5 to 4.0 (rapid publication)? I know some journals such as Journal of Material (Hindawi), Journal of Materials Science (Springer), JNN, Journal of Alloys and Compounds, Thin solid film and two lists:
However, I still can not find the suitable journal in these lists.