Delamination Crack Research Articles

Investigation Of Mode II Interlaminar Fracture Toughness Of Silicon-Di-Oxide Filled Glass Fiber Reinforced Epoxy Composites

Fracture is a new failure mode due to unstable propagation of a delamination crack growth in composite structures caused by applied load. The efficient characterization of the crack growth in composite structures enhances to estimate the duration of life. This paper mainly focusses on characterization of the fracture toughness of GFRP/epoxy matrix with SiO<sub>2</sub> filler form of composites and studying the crack behaviour in the (Mode II) ENF specimen which leads to interlaminar fracture in structural applications. The laminates are arranged to specify the Mode II interlaminar fracture toughness and interlaminar shear strength of GFRP/ epoxy matrix, GFRP/5% wt SiO2, GFRP/10% wt SiO<sub>2</sub>, using ASTM D7905 M-14 and JIS test methods. The results show that unfilled SiO<sub>2</sub> GFRP/epoxy matrix composites are of more facture toughness; the result reveals that the JIS methods in plane shear Mode II test were lower value of fracture toughness than that of ASTM D7905 M-14 Mode II test. As recommend in ASTM standard, ENF (shear pre-cracked) specimen is applicable to measure Mode II fracture toughness.

Flexural tests and analysis of notched specimens of glass fiber reinforced composite

Fracture of notched Specimens of laminar glass fiber reinforced composite is quasi-brittle and with noticeable delamination crack growth around the notch tip, as indicated by the non-linear load–deflection curve close to the peak fracture load. In order to analyze the fracture performance of the composite with highly heterogeneous and anisotropic microstructures, the boundary effect model (BEM) considering the composite layered structures and damage along and perpendicular to the notch was adopted in this study. Around 90 notched three-point bending specimens with the span from 40 to 90 mm, plate thickness around 10 mm, the initial notch depth from 3 to 6 mm were tested and the maximum load Pmax values were recorded. The average fiber ply or layer thickness Cch was the characteristic microstructure modelled by BEM for both the crack-tip damage zone length (crack-bridging) and width (delamination). Both the tensile strength ft and fracture toughness KIC were determined from the notched bending tests. Direct tensile tests were also conducted and the measured tensile strength ft was close to the measurement from the three-point bending tests with the relative error < 6 %.

Characterization of Used A123 LiFePO4 Cells from a Hybrid-Bus Battery Pack

As the battery market grows, developing a battery waste management economy becomes imperative. After primary use, the main options for discarded batteries are recycling, refurbishment, reuse, or disposal. Recycling involves extracting valuables materials from ground-up battery cells, while reuse and refurbishment involve direct use of packs or their components, with or without maintenance adjustments. Recycling and disposal are the most common battery waste pathways, while reuse and refurbishment practices require further understanding of battery degradation before being implemented on a large scale. Furthermore, relatively high recycling costs are motivation to pursue more cost-efficient recycling methods like direct recycling.This work expands on previous studies on the statistical distribution of the state-of-health (SOH) of used LiFePO4 (LFP) cells extracted from a hybrid-bus battery pack.1 We characterize samples from used and pristine A123 M1-A and M1-B 26650 cells using XRD and SEM. We will compare the cell materials’ morphologies and structure to their electrochemical performance in two diagnostic tests: a constant-current cycling test and an electrochemical impedance spectroscopy test.Preliminary data have been collected from used M1-A cells that demonstrated starkly different states-of-health during electrochemical testing—ranging in residual capacities from 2.2 Ah to 0.30 Ah. The low-SOH M1-A cell had severe anode delamination and morphological cracks in the center of the cylinder cross-section. Cathode delamination in the cell also increased towards the center of the cylinder. The high-SOH M1-A cell’s electrodes had a consistent morphology throughout the cell, but delamination was worst at the center of the cylinder’s cross-section.In this presentation, we will summarize our x-ray diffraction and scanning electron microscopy data for the cells described in Table 1. We will also discuss technical pathways for direct recycling of active materials from LFP battery waste. Ramirez-Meyers and J. Whitacre. “(Invited) Statistical Distribution and Feasibility for Re-Use of A123 LiFePO4 Cells from a Hybrid-Bus Battery Pack.” ECS Meeting s, no. 6, p. 1052. IOP Publishing, 2020. Figure 1

On the R-curve behaviour of carbon/epoxy laminates with core-shell rubber nanoparticle and micro-fibre veil hybrid toughening: Carbon vs PPS veils

This paper investigates the effect of non-hybrid and hybrid toughening, via core-shell rubber (CSR) nanoparticles and non-woven micro-fibre veils, on the delamination resistance and crack migration in carbon fibre/epoxy laminates under mode-I and mode-II conditions—with an emphasis on the effect of veil fibre properties on toughening mechanisms and fracture energies. Core-shell rubber particles, varying in size from 100 nm to 3 μm, with 0–10 wt% content, are dispersed within the epoxy resin. Two non-woven veils with contrasting fibre properties (i.e. one with ∼6 mm (50 wt%) and ∼12 mm (50 wt%) short carbon fibres and another with ∼6 mm short polyphenylene sulfide (PPS) fibres) with 10 g/m2 areal weights are used to introduce hybrid toughening at the interlaminar region. Carbon fibre/epoxy laminates with five different toughening routes (i.e. CSR toughening, carbon veil toughening, PPS veil toughening, carbon veil and CSR hybrid toughening, and PPS veil and CSR hybrid toughening) are manufactured with a two-part resin using vacuum infusion and out-of-autoclave curing. Double cantilever beam (DCB) and four-point end-notch-flexure (4-ENF) specimens are tested for mode-I and mode-II fracture energies and R-curves. Fracture surfaces are investigated to characterise crack migration and energy dissipation mechanisms. The results indicate that mode-I and mode-II fracture energies are significantly enhanced (e.g. ∼275% in initiation and propagation under mode-I) with the combined core-shell rubber nanoparticle and veil toughening investigated—significantly altering micro-failure mechanisms, crack paths and R-curves. It is shown that the low modulus PPS fibre veils together with CSR particles provide stable crack growth, while high modulus carbon fibre veils with CSR particles lead to unstable crack growth.

Symmetric and asymmetric intercalation effect on the low-velocity impact behavior of carbon/Kevlar hybrid woven laminates

Hybrid fiber composite laminates with the same materials, manufacturing methods and molding processes may present different mechanical behaviors. In this paper, the effect of intercalation sequence on the mechanical performance of carbon/Kevlar plain laminates were studied. According to different intercalation methods, the hybrid layout was divided into symmetric and asymmetric configurations. It is found that the symmetric intercalation structures (KCCK and CKKC) possess better load-bearing and resilience capacity compared with asymmetric structures (CCKK and CKCK), even better than pure carbon structure (CCCC) under high energy impact. The impact damage volume of symmetric specimens was significantly smaller than that of asymmetric specimens by quantitative micro-CT analysis. The apparent damage index (df and dr) can be used to estimate the internal damage data (dCT, H and V). KCCK, a typical symmetric sandwich-like structure, presented the most slight damage among all symmetric and asymmetric configurations, with shear cracks observed at the brittle carbon fiber core layers, while the delamination cracks between Kevlar-carbon interlayers were away from the central damaged region. In CKCK, interlaminar cracks were formed at each carbon-Kevlar interlayers, which shared and relieved the primary interlaminar crack at the core layers compared with CCKK.

Investigation on fatigue crack propagation behaviors in the thickness direction of 2519A aluminum alloy thick plate

2519A aluminum alloy thick plate is a promising structural material in the military industries, owing to its low density, high tensile strength and excellent ballistic performance. However, the delamination crack in the thickness direction (ND) of this alloy restricts its further application in light armors. The fracture mechanism of the alloy under the thickness direction fatigue load (ND fatigue load) remained unclear. In this work, the influence of microstructures on the fatigue crack propagation (FCP) behavior in the thickness direction of the alloy was investigated. Compared with the alloy subjected to rolling direction fatigue load (RD fatigue load), the alloy under the ND fatigue load is more susceptible to fracture with weak FCP resistance due to the effect of the coarse second phase. The FCP mode of the alloy under the ND fatigue load is mainly intergranular crack propagation. The fracture mechanism of the alloy under ND fatigue load mainly has three aspects. Firstly, due to the bridging effect of the second phase, the FCP of the alloy is accelerated under the ND fatigue load, and the delamination cracks occur easily. Secondly, the crack tends to expand along grain boundaries (GBs) due to the large percentage of GB when the alloy is subjected to ND fatigue load. Thirdly, the crack is inclined to propagate grains with a small twist angle of GB and a high Schmid factor. Moreover, when the orientation factor difference between two grains is large, the crack is more likely to extend along the GB of the grains.

A Two‐Step Thermomechanical Process for Improving High‐Angle Grain Boundary Proportion and Achieving Delamination Toughening in Hot‐Rolled Steel with a Limited Slab‐to‐Plate Ratio

A Two‐Step Thermomechanical Process for Improving High‐Angle Grain Boundary Proportion and Achieving Delamination Toughening in Hot‐Rolled Steel with a Limited Slab‐to‐Plate Ratio

Mechanical Response and Fracture of Pultruded Carbon Fiber/Epoxy in Various Modes of Loading

Pultrusion is a continuous process of forming constant cross-sections of unidirectional composites with a significant long length. This unique process is implemented widely in the composites industry due to its continuous, automated, and highly productive nature. The current research focused on mechanical response characterization at three modes of loading: tensile, compression, and shear loading of coupons made from a graphite/epoxy 1 mm sheet. In addition, the effects of holes and notches were examined in terms of mechanical properties. The mechanical behavior was assessed through stress–strain curves with careful attention on the curve profile, macroscopic fracture modes observations, and optical microscopic tracking with continuous video records. The mechanical tests follow standards with some critiques on the shear test. Finite element analysis (FEA) was used to accurately determine the shear modulus, and for other mechanical investigations. By nature, under tension, the unidirectional fiber composite at 0° orientation exhibits high strength (2800 MPa), with very low strength at 90° orientation (40 MPa). Both orientations display linear mechanical behavior. Under compression, 0° orientation exhibits low strength (1175 MPa), as compared to tension due to the kinking phenomena, which is the origin in the deviation from linear behavior. Under shear, both orientations exhibit approximately the same shear strength (45 MPa for 0° and 47 MPa for 90°), which is mainly related to the mechanical properties of the epoxy resin. In general, in the presence of holes, the remote fracture stress in the various modes of loading did not change significantly, as compared to uniform coupons; however, some localized delamination crack growth occurred at the vicinity of the holes, manifested by load drops up to the final fracture. This behavior is also attributed to the tension of notched coupons. FEA shows that the shear values were unaffected by manufacturing imperfections, coupon thickness, and by asymmetrical gripping up to 3 mm, with minor effect in the case of a small deviation from the load line. Selected experimental tests support the FEA tendencies.

An adaptive floating node based formulation for the analysis of multiple delaminations under high cycle fatigue loading

A novel efficient numerical formulation for the analysis of multiple fatigue-driven delamination cracks is presented. A cohesive zone model is used in combination with an Adaptive Refinement Scheme (ARS) and an Adaptive Floating Node Method (A-FNM) element that refine the model effectively during the analysis. Novel techniques are proposed to track the positions of multiple crack tips and calculate the mode decomposed energy release rates for the individual crack tips using the J-integral. The method has been implemented in a Matlab finite element code and validated with single and multiple delamination cases with varying mode mixities. Comparisons with theoretically based predictions and available experimental data showcase the high accuracy of the method. The presented method lowers the computational time compared to standard, fully refined finite element models by a factor of 4–5.

Experimental investigation of three-point bending behavior of assembled hybrid composite tubes before and after the fire endurance test

This work presents an experimental investigation of the post-fire flexural strength of Filament-wound Glass Fiber Reinforced Polymer (GFRP) tubes manufactured by CTRA Company. These tubes are assembled according to both the NFT57-900 and DIN-16966 standards’ recommendations. To this end, flexural tests have been carried out on butt-to-butt assembled tubes, before and after fire endurance tests. To gain a better insight into fire-induced damage mechanisms, thermal analysis (DSC and TGA), FTIR analysis tests, as well as Scanning Electron Microscope (SEM) observations have been conducted. The experimental results revealed that a water leakage was observed prior to the recommended threshold time by the International Maritime Organization (IMO) resolution. It has been also confirmed that flexural properties of the GFRP tube are degraded after the fire tests. Furthermore, a quantitative comparison for both filament tubes assembled according to the NFT and DIN standards confirms that the NFT ones depict higher resistance. Finally, damage investigation reveals that the main observed forms of damage occurring during this experiments are delamination and matrix cracking phenomena. The main novelties of this work are (a) extending the classic analysis carried out on simple composite plate to cover water-filled GFRP assembled tubes subject to fire endurance test, and (b) the experimental investigation of DIN and NFT butt welded joined pipes under three point loading prior and post fire endurance test.

Influence of inclusion defects on bending properties and failure modes of composites

A comparison test was carried out between the simulated inclusion sample and the normal sample, and the test section was subjected to pure bending loading by three-point bending loading method. The influence of different inclusion positions on the bending mechanical properties of the composite was analyzed. The fracture surface of the specimen was observed macroscopically and by scanning electron microscopy, and the load transfer and failure mechanism of the specimen were studied from macroscopically and microscopically. The results show that the distance of the simulated inclusions and the position of loading surface have great influence on the bending properties of the composites. When the simulated inclusion is far from the loading surface, delamination cracking does not occur in the simulated inclusion area, and the bending property of the simulated inclusion sample is improved rather than decreased, that is, the presence of inclusion does not necessarily reduce the bending property of the composite.

On mode-I and mode-II interlaminar crack migration and R-curves in carbon/epoxy laminates with hybrid toughening via core-shell rubber particles and thermoplastic micro-fibre veils

This study investigates the influence of hybrid toughening—via core-shell rubber (CSR) particles and non-woven thermoplastic veils—on the delamination resistance, crack migration and R-curve behaviour in carbon fibre/epoxy laminates under mode-I and mode-II conditions. Core-shell rubber particles, varying in size from 100 nm to 3 μm, with 0–10 wt% content, are dispersed within the epoxy resin, and thermoplastic micro-fibre veils with polyphenylene sulfide (PPS) fibres, with 5–20 g/m 2 areal weight, are introduced at the interlaminar region to achieve hybrid toughening. Carbon fibre/epoxy laminates are manufactured with a two-part resin using vacuum infusion and out-of-autoclave curing. Double cantilever beam (DCB) and four-point end-notch-flexure (4ENF) specimens are used to obtain mode-I and mode-II fracture energies and R-curves. Damage mechanisms and crack paths are characterised using fractography that provide understanding of energy dissipation. The results show that the hybrid toughening significantly improves fracture initiation and propagation energies ( i.e . mode I initiation by ∼245% and propagation by ∼275%, and mode-II initiation by ∼64% and propagation ∼215%) by extrinsic and intrinsic toughening mechanisms. Moreover, it is shown that rising R-curves can be achieved with hybrid toughening when compared with falling R-curves obtained with just thermoplastic veil toughening. Fractography revealed that the hybrid toughening constrained the crack predominantly within the veil region, making it harder to grow and absorb more energy.

Distribution of axial yarns on the localized deformation and damage mechanism of triaxial braided composite tubes

Localized deformation and damage mechanism of triaxial braided composite tubes, with different quantities and positions of axial yarns, were experimentally studied under transverse low-velocity impact. A high-speed infrared thermography was applied to analyze the transient thermo-mechanical failure process and afterwards verified by the external and internal damage characterization. It is found that the distribution of axial yarns has a significant effect on the mechanical behavior of braided composite tubes. The bending stiffness and peak force of the tubes were enhanced with the increased quantity of axial yarns, while the impact lasting time and displacement presented an opposite trend. And the more axial yarns assembled at the impact side, the greater force oscillatory of the tubes under low-velocity impact, accompanied by the decreased heat generation in small-angle braided tubes and the alleviated fiber tows fracture, delamination and in-plane shear cracks inside the wall of large-angle braided tubes. On the premise of the same quantity of axial yarns, the position effect plays a key role. Axial yarns concentrated at the impact side could restrain the damages spreading to the non-impact side by changing the damage mode of large-angle braided tubes. If a larger force is needed at the early stage, axial yarns could be inserted at the local position most probably to be impacted; Otherwise, it is highly suggested to braid at least one axial yarn in each layer at the impact side and non-impact side respectively to reinforce localized strength and prevent the impact-side indentation and non-impact-side delamination.

Experimental study on the low-velocity impact and post-impact flexural properties of curved CFRP laminates reinforced by pre-hole Z-pinning (PHZ) technique

This paper presents an experimental investigation into the effect of Z-pin on the low-velocity impact response and flexural properties after impact of the curved CFRP laminates. The Z-pinned specimens are produced using a low-damage pre-hole Z-pinning (PHZ) technique. Unpinned and Z-pinned [0/45/–45/90]4S specimens are both subjected to low-velocity impacts. Nondestructive inspection technique is used to evaluate the internal damage after impact. Subsequently, three-point bending tests are performed to characterize the flexural properties of the impacted specimens. Experimental results indicate that Z-pinned laminate, due to the bridging traction across the delamination cracks provided by pins, can provide an efficient crack arrest mechanism both in impact and bending after impact tests. Compared with the unpinned specimens, the delamination damage projection area (DDPA) is reduced by 28.5–63.5%, depending on the diameter and volume fraction of Z-pin. In addition, Z-pin could improve the residual flexural strength significantly. The specimens with a high Z-pin volume fraction have excellent damage tolerance, leading to an 18.1–76.1% improvement in the residual flexural strength compared with unpinned specimens.

Interfacial delamination of a sandwich layer by aqueous corrosion

The mechanism of aqueous delamination of a methyl methacrylate -based adhesive layer, sandwiched between two steel plates, is investigated by a systematic series of critical tests. These tests include starving the specimen of oxygen, varying the aqueous environment from de-ionised water to water with a high concentration of salt, and varying the mechanical constraint imposed by the sandwich. Sandwich construction starves the delamination crack tip of oxygen, and delamination occurs by water attack of the interface. In contrast, an adhesive coating on a steel substrate undergoes cathodic delamination when oxygen is present at the crack tip and the delamination crack is filled with salt water.

Prediction of fracture toughness due to delamination in cross-ply composite laminates considering interlaminar and intralaminar cracking and inhomogeneous fiber-matrix modeling

In this study, a finite element strategy is implemented for more accurate simulation of nonlinear failure behavior in multidirectional laminated composites. The considered approach is based on the parameters which could affect the SERR2. Accordingly, interaction between delamination and matrix cracking as well as mixed stress distribution around the fiber due to mismatch in properties of adjacent plies with different fiber angle orientation influence the strain energy release rate. Thus, in the present research the prediction of the damage behavior of cross-ply laminates is improved considering the effects of matrix cracking and inhomogeneous fiber-matrix modeling. For simulation of the delamination and the matrix cracking damage, cohesive interface elements are implemented. They have been used perpendicularly inside the 90o plies for the matrix cracking. CZM3 approach, ABAQUS subroutine and Python programming were utilized for automatic modeling of matrix cracking. The resultant load–displacement curve in DCB4 test of cross-ply laminates indicated that by considering delamination and matrix cracking simultaneously, load–displacement curve of cross-ply laminates became nonlinear earlier and the obtained results had an acceptable compatibility with experimental results. The obtained results for double cantilever beam (DCB) test specimen with cross-ply lay-up indicate that the numerically reproduced GIc parameter of 90/0 interface can be improved about 20% using this simulation. Moreover, by simulating periodic matrix cracking inside 90o plies, crack jumping, stick-slip phenomenon and local hardening behavior are anticipated such as experiments.

Correlation between Microstructure and Mechanical Properties of Welded Joint of X70 Submarine Pipeline Steel with Heavy Wall Thickness

This paper aims to study the relationship between the microstructure and the mechanical properties of X70 submarine pipeline steel with 40.5 mm thickness. The microstructure was examined by using optical microscopy, scanning electron microscopy and an electron backscattered diffractometer, while the mechanical properties were examined by using a hardness test, a tensile test, a Charpy impact test and a drop weight tear test (DWTT), respectively. The results show that the base metal (BM) of the pipe has a low yield ratio of 0.83 and an excellent elongation of more than 45%. The DWTT shear area of the steel plate reaches 87%, showing excellent low-temperature toughness. The Charpy impact energy increases when the distance from the fusion line increases, and it reaches a maximum at the BM near the heat-affected zone (HAZ) due to the small martensite-austenite (MA) constituents and fine grains. The concentrated distribution of blocky/slender MA constituents along the prior austenite grain boundaries of the intercritically reheated coarse-grained HAZ and the large MA constituents are the main reasons for the deteriorating impact toughness. Delamination cracks in the DWTT fracture surface only occurred in the midthickness of a sample with a small opening width that spread about 2.1 mm perpendicular to the DWTT fracture surface and were finally arrested at the acicular ferrite clusters containing a high density of high-angle boundaries.

Investigation of microstructural changes of Pt-Al-7% YSZ coating during high-temperature hot corrosion and its effect on tensile properties of coated Rene-80 superalloy at 950 °C

In the present study, the microstructural changes in Pt-Al-7%YSZ coating on Rene-80 superalloy after 10, 20, and 40 cycles of hot corrosion and the effect of hot corroded coating on the tensile properties of Rene-80 substrate at 950 °C were investigated. For this purpose, the cross-section and fracture surface of the coating, substrate, and coating/substrate interface, were studied and the correlation between tensile behavior and microstructural changes of substrate and coating was evaluated. It was found that the effect of coating's microstructural changes on the tensile properties is less than the effect of microstructural changes on the substrate. As the cycles of hot corrosion increased, yield strength and tensile strength changed. This event was attributed to the γ' precipitates and volume fraction and the average size of voids in the substrate. The intergranular cracks were nucleated in the substrate from micro-voids in the adjacent areas to MC carbides, grew, and coalesced. However, the most influential factors in the coating on the tensile properties of coated samples were thermally grown oxide (TGO) stresses and thermal stresses due to the difference in thermal expansion coefficients between the coating layers and substrate and increasing the release rates of these stresses. The strain energy release rate (GC) was highest in TGO/Pt-Al, and coating degradation occurred through nucleation of delamination and longitudinal cracks in the TGO/Pt-Al interface and propagation of some of these cracks to the substrate.

Modeling of flip-chip underfill delamination and cracking with five input manufacturing variables

The chip corner geometry and the mismatch of the coefficient of thermal expansion cause a local stress concentration in the underfill near the chip corner area. Delamination at the chip-underfill interface and cracks in the underfill often originate from the chip corner and might develop throughout the assembly. This paper presents a modeling approach that allows the estimation of the initial moment of delamination, the growth of delamination and the cracking profiles in flip-chip packages. The reliability model in this work includes five input variables: kerf width, dicing type, laser outrigger presence, sealband material and sealband shape. Thirteen test cells of flip-chip experimental samples were first prepared according to these input variables and were subjected to deep thermal cycling (DTC). C-mode scanning acoustic microscopy (C-SAM), infrared microscopy (IR) and cross-sectioning were used to estimate the underfill failure moments, delamination areas and crack profiles as a reference for subsequent numerical modeling. An artificial neural network (ANN) model was trained to estimate the number of cycles to delamination for cells in the test dataset. The predicted numbers of cycles for all 6 cells in the test dataset were consistent with experimental observations. A finite element model was built to describe the growth of delamination. When the model reached the same delamination area as measured by C-SAM, the difference between the predicted number of cycles and the C-SAM inspection moment were smaller than the inspection interval (250 cycles) for 5 out of 6 cells in validation; the delamination growth model was thus consistent with the experimental observations. The extended finite element method (XFEM) was used to model the underfill cracks without predefined paths. One of the cracks propagated along the diagonal direction, and the other two cracks were along the edges of the die. The directions of edge cracks were in good agreement with the experimental observations, with an error of less than 2.5° for the edge cracks. Overall, with five input manufacturing variables, this modeling approach is able to provide reasonable predictions of the number of cycles to chip-underfill delamination initiation, area of delamination and underfill crack paths in flip-chip packages.

Durability of Shape Memory Polymer Composite Laminates under Thermo-Mechanical Cycling

Shape memory polymer composites (SMPCs) have been manufactured by press moulding of carbon fibre-reinforced (CFR) prepregs with SMP interlayers. SMPC laminates have been produced with different numbers of CFR plies (i.e., 2, 4, 6, and 8) and different thicknesses of the SMP interlayers (i.e., 100 and 300 µm) for a sum of eight combinations. Co-curing of the prepreg plies and the SMP interlayers has led to an optimal adhesion of structural and functional plies, which has been confirmed by following testing. Single thermo-mechanical cycles at increasing strains (i.e., 0.06%, 0.12%, and 0.18%) and multiple cycling have been performed to test SMPC laminate durability. Delamination and fibre cracking were not observed during testing, and laminates showed a reproducible SM behaviour after 10 consecutive thermo-mechanical cycles. SM properties have been extracted from tests in terms of residual and memory loads as well as shape fixity and shape recovery. These data may be used for comparison of the performances of the different laminates, and as a first base for designing SMPC structures. Thin laminates exhibit lower recovery loads but higher shape fixity than thick ones, but the shape recovery is very high for all the SMPCs, with an average of 98%.