En
  • دکتری (1389)

    سازه های هوایی

    صنعتی امیرکبیر، تهران، ایران

  • کارشناسی‌ارشد (1382)

    سازه های هوایی

    صنعتی شریف، تهران، ایران

  • کارشناسی (1380)

    طراحی جامدات

    فردوسی، مشهد، ایران

  • مكانيك مواد مركب و مود‌های خرابی در مواد مرکب شامل مطالعه و تحليل ترک‌‌های عرضی درون‌لايه‌ای در مواد مرکب لايه‌ای، مطالعه ترک‌های بين‌لايه‌ای، بررسی و تحليل ضربه سرعت پایین بر مواد مرکب لايه‌ای
  • مطالعه رفتار کمانش و پس کمانش در مواد مركب لايه‌اي تحت بارهاي فشاري و بررسي رشد جداشدگي بين‌لايه‌اي در مواد مرکب
  • ناپایداری استاتیکی و دینامیکی در سیستمهای الکترو مکانیکال
  • مکانیک خرابی محیطهای پیوسته و تحليل المان محدود غيرخطی سازه‌های مواد مرکب

    تحصیلات: دکترا: مهندسی هوافضا گرایش سازه های هوایی- دانشگاه صنعتی امیرکبیر، ایران 1385- 1389 کارشناسی ارشد: مهندسی هوافضا گرایش سازه های هوایی - دانشگاه صنعتی شریف، ایران، 1380-1382 کارشناسی: مهندسی مکانیک- دانشگاه فردوسی مشهد، ایران، 1375-1380 وضعیت اشتغال - عضو هیئت علمی (استادیار) دانشکده مکانیک، گروه هوافضا، دانشگاه تربیت مدرس ، تهران ، بزگراه جلال آل احمد، از سال 1393 تاکنون - مدیر گروه هوافضا، از سال 1395 تا کنون.

    In situ strength analysis of cross‐ply composite laminates containing defects and interleaved woven layer using a computational micromechanics approach

    Alireza Rafie, Hamidreza Madadi, Amin Farrokhabadi, Miguel Herr?ez
    Journal PapersFatigue & Fracture of Engineering Materials & Structures , 2021 January 31, {Pages }

    Abstract

    The transverse strength of 90? plies located in cross‐ply laminates subjected to transverse tension is investigated numerically. To reach this aim, it is assumed that the transverse cracking is formed by coalescence of fiber–matrix debonding, which propagates along the planes parallel to the fibers. The two‐dimensional finite element model (FEM) investigates the dominant micromechanical damage mechanisms, fiber–matrix debonding, and matrix cracking using the cohesive zone model (CZM) and plasticity, respectively. The numerical simulation is according to the extended computational micromechanics (ECMM) approach, which can be applied as a useful virtual test method instead of performing costly characterization tests. The results obta

    The Effect of Core Shape on the Bending Response of Sandwich Panels with Filled and Unfilled Sine and Square Corrugated Cores

    Faezeh Hamidin, Amin Farrokhabadi, Hamed Ahmadi
    Journal PapersJournal of Failure Analysis and Prevention , 2021 January 2, {Pages 10-Jan }

    Abstract

    This paper aims to construct a lightweight and durable structure with different designs and construction methods using materials with low-weight characteristics and appropriate strength. In this regard, sandwich panels were made in filled and unfilled sine and square corrugated core, and for comparison of some mechanical behaviors of made specimens with each other, three-point bending tests were performed. Obtained results indicated that the use of polyurethane foam will significantly increase the energy absorption of the structure and extend the life of the structure. The amounts of absorbed energy of the foam-filled samples are 2 and 2.5 times of the foam-free ones for sine and square corrugated cores, respectively. Finally, a numerical a

    Experimental investigation of Buckling after impact strength of grid stiffened composite panels

    Ahmad Ataei, Hamed Ahmadi, Amin Farrokhabadi
    Journal PapersIranian Journal of Manufacturing Engineering , Volume 7 , Issue 11, 2021 January 20, {Pages 34-41 }

    Abstract

    Composite lattice structures are widely used in the aerospace, automobile and marine industries due to their benefits such as high stiffness and strength with light weight. In this study buckling strength after impact of grid stiffened composite panels was investigated experimentally. For this purpose, grid stiffened composite panels with iso-grid reinforced lattice and three types of skin thickness of 6, 12 and 18 layers were designed, fabricated and tested. E-glass fibers and epoxy resin was used for both ribs and skin. At first, the specimens were subjected to a low velocity impact and then the buckling test was carried out. From results it is concluded that with increasing the thickness of skin, failure mechanisms such as fiber breakage

    Assessment of Delamination Growth due to Matrix Cracking in Hybrid Glass-Kevlar Composite Laminates Using Experimental, Numerical and Analytical Methods

    Amin Farrokhabadi, Sara Neyestani, Davood Akbari, Reza Sarkhosh
    Journal PapersEngineering Fracture Mechanics , 2021 March 18, {Pages 107691 }

    Abstract

    In this study, the growth of induced delamination in off axes composite laminates has been investigated. Glass-Epoxy composite laminates and Glass-Kevlar-Epoxy hybrid composite laminates with cross-ply [04/90n]s and angle-ply [304/90n]s and [454/90n]s composite layup, containing a low density matrix crack in 90? layers have been made. Then they have been subjected to tensile loading in experimental tests in order to investigate the growth delamination from the location of the matrix cracking and to measure the stiffness degradation. The experimental observations reflect the effects of hybridization and staking sequences on the induced delamination growth for the first time. In addition, the growth of delamination in the considered composite

    Investigation of novel multi-layer sandwich panels under quasi-static indentation loading using experimental and numerical analyses

    Seyed Ahmad Taghizadeh, Mohsen Naghdinasab, Hamidreza Madadi, Amin Farrokhabadi
    Journal PapersThin-Walled Structures , Volume 160 , 2021 March 1, {Pages 107326 }

    Abstract

    In this study, the effect of multi-layering in sandwich panel composite structures with different configurations of corrugated cores under the effect of quasi-static indentation loading is investigated experimentally and numerically. Composite plates and corrugated cores with equal weight fraction were manually made using ML506 epoxy resin with 15% hardener and the overall volume fraction of 45% for woven glass fibers. Experiments were performed using a cylindrical indenter with a diameter of 20?mm and a semi-spherical nose shape, and the behavior of the composite structure was evaluated in the case of energy absorption, contact force, and fracture mechanisms for different corrugated cores (rectangular, trapezoidal and triangular). Progress

    Anticipating the induced delamination formation in composite laminates subjected to bending loads

    Mohammad Bahrami, Mohsen Malakouti, Amin Farrokhabadi
    Journal Papers , 2021 April 10, {Pages }

    Abstract

    In this research, the effects of induced delamination on the variation of the mechanical properties of composite laminates subjected to bending loads are investigated using a micromechanical model. For this purpose, the variation of the mechanical properties of delaminated laminates is determined using stress analysis of damaged ply and classical laminate theory (CLT) relationships. Using the proposed model and CLT, the fracture toughness due to induced delamination formation is presented in cross-ply laminates. Subsequently, the variation of strain energy release rate (SERR) is calculated in terms of crack density using analytical and finite element models to detect dominant failure modes in different crack densities. The results are compa

    Evaluation of the equivalent mechanical properties in a novel composite cruciform honeycomb using analytical and numerical methods

    A Farrokhabadi, MM Ashrafian, H Gharehbaghi, R Nazari
    Journal Papers , , {Pages }

    Abstract

    Experimental and Analytical Studies of Mechanical Properties of Additively Manufactured Lattice Structure Based on Octagonal Bipyramid Cubic Unit Cell

    M Sadeghzade, H Gharehbaghi, A Farrokhabadi
    Journal Papers , , {Pages }

    Abstract

    The effect of staggered matrix crack induced delamination growth on the mechanical properties of cross-ply laminates

    SR Jafari, A Farrokhabadi, J Montesano
    Journal Papers , , {Pages }

    Abstract

    Micromechanical investigation of cross-ply carbon composite laminates with glass microtubes using CZM and XFEM

    A Farrokhabadi, H Madadi, M Naghdinasab, A Rafie, SA Taghizadeh, ...
    Journal Papers , , {Pages }

    Abstract

    Determination of static strength and fracture of aged aircraft structure using non-destructive quasi-static indentation test

    H Zarei, R Sarkhosh, A Farrokhabadi, H Morshedi
    Journal Papers , , {Pages }

    Abstract

    Reliability analysis of the delamination onset and growth due to the matrix cracking in general composite laminates

    A Delbariani-Nejad, A Farrokhabadi, M Fotouhi
    Journal Papers , , {Pages }

    Abstract

    Finite Element Reliability Analysis of Edge Delamination Onset Due to the Interlaminar Stresses in General Composite Laminates

    A Delbariani-Nejad, A Farrokhabadi, H Haddad Khodaparast, M Fotouhi
    Journal Papers , , {Pages }

    Abstract

    Cumulative acoustic emission energy for damage detection in composites reinforced by carbon fibers within low-cycle fatigue regime at various displacement amplitudes and rates

    M Azadi, M Alizadeh, SM Jafari, A Farrokhabadi
    Journal Papers , , {Pages }

    Abstract

    Numerical investigation of matrix cracking propagation in cross‐ply laminated composites subjected to three‐point bending load using concurrent multiscale model

    Hamidreza Madadi, Mohsen Naghdinasab, Amin Farrokhabadi
    Journal PapersFatigue & Fracture of Engineering Materials & Structures , Volume 43 , Issue 6, 2020 June , {Pages 1159-1169 }

    Abstract

    The purpose of the present study is to analyze fiber‐matrix debonding and induced matrix cracking formation as two major micromechanical damage modes in cross‐ply composite laminates using a two‐dimensional numerical approach. To this aim, the cross‐ply laminates containing 90‐degree layers are modeled, where the fibers are arranged randomly in transverse plies. Damage modes in this numerical model are simulated by the cohesive surface method. The performed analyses reveal that in the laminates with 90‐degree layers located in the outer positions, the primary micro damage mode is micro matrix cracking which is initiated from the fiber‐matrix debonding damage mode and will be followed by matrix cracking. The main benefit of th

    Investigation of debonding growth between composite skins and corrugated foam-composite core in sandwich panels under bending loading

    Hossein Malekinejad Bahabadi, Amin Farrokhabadi, Gholam Hossein Rahimi
    Journal PapersEngineering Fracture Mechanics , 2020 March 10, {Pages 106987 }

    Abstract

    This study investigates experimentally and numerically the resistance to separation between composite skins and different complex geometries of the corrugated core filled with PVC foam. To this purpose, three different geometries including simple foam core without any corrugated composite, longitudinal trapezoid, and square cores are considered and manufactured as waved (corrugated) composite core. In each specimen, an artificial pre-crack is located between the skin and core and then the effect of the skin's thickness and the core shaped on the debonding growth are examined for the first time. Three-point bending tests are carried out using ENS (End Notch Shear) fixture. Furthermore, the nonlinear response due to separation initiation and

    Experimental and numerical analysis of novel multi-layer sandwich panels under three point bending load

    Amin Farrokhabadi, Seyed Ahmad Taghizadeh, Hamidreza Madadi, Hossein Norouzi, Ahmad Ataei
    Journal PapersComposite Structures , 2020 June 17, {Pages 112631 }

    Abstract

    In this study, mechanical behavior of multilayer corrugated core laminated composite sandwich panel subjected to quasi-static three-point bending is investigated experimentally as well as numerically. Parameters such as contact force, energy absorption and specific absorbed energy (unit mass energy) for different geometries of corrugated core (rectangular, trapezoidal and triangular) studied during loading process and failure. Composite plates and corrugated cores have been manually made using ML506 epoxy resin with 15% hardener and 45% volumetric woven glass fibers. Experimental results show that multilayer sandwich composite panels not only strengthen the structure in the quasi-static three-point bending process, but also make the absorbe

    Prediction of debonding growth in two-dimensional RVEs using an extended interface element based on continuum damage mechanics concept

    Ramzan Babaei, Amin Farrokhabadi
    Journal PapersComposite Structures , Volume 238 , 2020 April 15, {Pages 111981 }

    Abstract

    In the present study, a new interface model based on continuum damage mechanics (CDM) is developed to investigate the fiber-matrix interfacial debonding in the composite material. This model differs from Voronoi cell finite element and cohesive zone element method. To this purpose, a 2D classical elasticity formulation with non-interactive strength-based criteria and complex variable method with non-interactive energy-based criteria are applied for the analysis of the debond onset and propagation in an RVE with a single fiber, respectively. Then, the CDM approach is used to bridge between analytical and numerical methods. The developed model based on CDM is implanted into ANSYS commercial software to compare the accuracy of the proposed met

    Determining of a closed-form relation for evolution of crack density and induced delamination in off-axis composite laminates under uniaxial loading condition

    Maryam Aghaebrahimi Samani, Amin Farrokhabadi, Saeed Homayoni Boora
    Journal PapersMechanics of Advanced Materials and Structures , Volume 27 , Issue 11, 2020 June 1, {Pages 859-868 }

    Abstract

    In this study a crack density based micromechanics methods in the framework of shear lag approach will be presented. This method is able to establish a dependent relationship for calculating the stiffness degradation and crack density evolution in each applied remote loading. Using this method by considering the effects of out of plane shear stresses, the stress-strain fields, displacement as well as the strain energies of different off-axis composite laminates with the stacking sequences of [?θ/904]s will be calculated. Furthermore, the damage parameters of each damage modes including the matrix cracking and induced delamination will be applied. Using an appropriate fracture criterion, a closed-form analytical relationship will be derived

    Investigation of the equivalent material properties and failure stress of the re-entrant composite lattice structures using an analytical model

    Hossein Veisi, Amin Farrokhabadi
    Journal PapersComposite Structures , 2020 October 22, {Pages 113161 }

    Abstract

    In the present study, a novel theoretical model is developed, based on classical laminate theory, to predict the equivalent mechanical properties of the re-entrant lattice structures, which composed of continuous fiber reinforced composite struts. Three main mechanism of stretching, flexing and hinging are considered and a general closed-form formulation is derived to estimate the auxetic honeycomb’s elastic and shear modulus as well as Poisson’s ratios. In spite of previous studies in which the response of honeycomb structures is modeled using beam theory, here, each strut of unit cell is expressed as a composite laminate with orthotropic mechanical properties and classical laminate theory is implemented to calculate the mechanical con

    /pro/academic_staff/amin-farrokh/publication

    دروس نیمسال جاری

    • دكتري
      مكانيك آسيب در سازه هاي كامپوزيتي ( واحد)
      دانشکده مهندسی مکانیک، گروه هوافضا
    • كارشناسي ارشد
      مكانيك مواد مركب ( واحد)
    • كارشناسي ارشد
      مكانيك مواد مركب ( واحد)
    • كارشناسي ارشد
      طراحي پيشرفته سازه هاي هوا فضايي ( واحد)
    • كارشناسي ارشد
      طراحي پيشرفته سازه هاي هوا فضايي ( واحد)

    دروس نیمسال قبل

    • كارشناسي ارشد
      ديناميك سازه ( واحد)
      دانشکده مهندسی مکانیک، گروه هوافضا
    • كارشناسي ارشد
      ديناميك سازه ( واحد)
    • كارشناسي ارشد
      تحليل پيشرفته سازه هاي هوافضايي ( واحد)
    • كارشناسي ارشد
      تحليل پيشرفته سازه هاي هوافضايي ( واحد)
    • 1399
      موسوي, سيدعلي
      بررسي خواص مكانيكي و حرارتي يك فراسازه پيكاني شكا دوگانه از جنس كامپوزيت پلي لاكتيك اسير شيشه به روش تجربي، عددي و تحليلي
    • 1400
      بهمن قمصري, سعيد
    • 1396
      رضايي جعفري, سپيده
      بررسي تحليلي و تجربي رشد لايه لايه شدگي ناشي از ترك ماتريسي با الگوي نامتقارن درچند لايه كامپوزيتي متعامد تحت بار خستگي
    • 1397
      استادحسين, نيايش
    • 1399
      توكلي طرئي, حميده
    • 1399
      حميدين, فائزه
    • 1399
      قباد, يوسف
    • مدیرگروه هوافضا
    • معاون آموزشی-پژوهشی دانشکده مهندسی مکانیک
    • ریاست دانشکده مهندسی مکانیک
      داده ای یافت نشد

    مهم

    جدید

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