Cantera 2025a - Revision history

Marherna: Marherna moved page Review 535961494455 to Cantera 2025a

2025-08-18T08:30:38Z

Marherna moved page Review 535961494455 to Cantera 2025a

Marherna at 08:27, 18 August 2025

2025-08-18T08:27:47Z

Asuncantera: Fig 1,2and 3 have been updoaded

2025-08-14T10:54:37Z

Fig 1,2and 3 have been updoaded

Asuncantera at 10:49, 14 August 2025

2025-08-14T10:49:04Z

Asuncantera at 10:35, 14 August 2025

2025-08-14T10:35:25Z

Asuncantera: Asuncantera moved page Draft Cantera 614497791 to Review 535961494455

2025-07-25T07:43:28Z

Asuncantera moved page Draft Cantera 614497791 to Review 535961494455

Scipediacontent: Scipediacontent moved page Review 274938092986 to Draft Cantera 614497791 without leaving a redirect

2025-07-25T07:36:55Z

Scipediacontent moved page Review 274938092986 to Draft Cantera 614497791 without leaving a redirect

Asuncantera: Asuncantera moved page Draft Cantera 370995223 to Review 274938092986

2025-05-21T12:32:15Z

Asuncantera moved page Draft Cantera 370995223 to Review 274938092986

Asuncantera: grammar review

2025-05-21T12:27:23Z

grammar review

Asuncantera at 12:20, 21 May 2025

2025-05-21T12:20:36Z

@@ Line 66: / Line 66: @@
 =3. Results=
-To compare the stiffness of different types of composites, natural and non-natural the same dimensionless parameter can be used. All values show a linear relationship on a double logarithmic scale, with different slope ssad CoV a  it is shown in Figure2  .The ratio of the tensile normalized modulus of different lay-ups with [0/90] as the baseline is shown in Figure 2b, for the synthetic and natural fibers listed in Table1
+To compare the stiffness of different types of composites, natural and non-natural the same dimensionless parameter can be used. All values show a linear relationship on a double logarithmic scale, with different slope ssad CoV a  it is shown in Figure 2  .The ratio of the tensile normalized modulus of different lay-ups with [0/90] as the baseline is shown in Figure 2b, for the synthetic and natural fibers listed in Table 1.
 a)
@@ Line 76: / Line 76: @@
 [[File:Review_535961494455_8302_Fig2b EX 0 90.jpg|1132x1132px]]
-Figure 2a The linear relationship between the longitudinal tensile modulus and its trace for natural and non-natural composites. b) Comparison of trace-normalized longitudinal modulus and their ratio respect to [0/90].
+Figure 2: a) The linear relationship between the longitudinal tensile modulus and its trace for natural and non-natural composites. b) Comparison of trace-normalized longitudinal modulus and their ratio respect to [0/90].
-The Table 1 shows the values and coefficients of variation for the trace normalised modulus and the ratio of material properties of different composites. The CoV of the is are reasonable, considering the typical scatter of mechanical properties in NFs. It is noteworthy that the relative mechanical behaviour of the unidirectional NFRP with respect to the cross-ply is very similar to that of human-made composites, and  ratio<span style="text-align: center; font-size: 75%;"> [[Image:Draft_Cantera_370995223-image14.png|96px]] </span>is better than synthetic composites.
+Table 1 shows the values and coefficients of variation for the trace normalised modulus and the ratio of material properties of different composites. The CoV of the is are reasonable, considering the typical scatter of mechanical properties in NFs. It is noteworthy that the relative mechanical behaviour of the unidirectional NFRP with respect to the cross-ply is very similar to that of human-made composites, and  ratio<span style="text-align: center; font-size: 75%;"> [[Image:Draft_Cantera_370995223-image14.png|96px]] </span>is better than synthetic composites.
-Table 1 Trace-normalized tensile mechanical properties of common composite families, the CoV is given in parentheses.
+Table 1. Trace-normalized tensile mechanical properties of common composite families, the CoV is given in parentheses.
 {| style="width: 100%;margin: 1em auto 0.1em auto;border-collapse: collapse;"
@@ Line 176: / Line 176: @@
 :* Finally, the experimental relationship between the R* value and the average tensile and compressive strengths was found for all the NFRPs investigated, as it is shown in Figure 3c
-:1)
+:a)
 [[File:Review_535961494455_6293_Fib3a stress enveloppes.jpg|1135x1135px]]
-:2)
+:b)
 [[File:Review_535961494455_6756_Fib3b equivalent circle.jpg|1151x1151px]]
-:3)
+:c)
 [[File:Review_535961494455_8323_Fib3c R normal.jpg|1163x1163px]]
 <span id='_GoBack'></span>
-Figure 3 a) The Omni Stress Envelope of different Flax composites with the same lay-up, b) equivalent circle of radius R with the same area as the stress envelope, c) linear relation between the trace normalize parameters of Radius and major Diameter
+Figure 3: a) The Omni Stress Envelope of different Flax composites with the same lay-up, b) equivalent circle of radius R with the same area as the stress envelope, c) linear relation between the trace normalize parameters of Radius and major Diameter.
 =4. Discussion=

@@ Line 17: / Line 17: @@
 The experimental data with relevant information on the elastic properties of unidirectional flax, hemp, and kenaf composites are obtained from scientific publications, dissertations, and published reviews [5-7]. They are classified according to the type of load,  and the presence or absence of chemical modification. Logically, each composite is manufactured with a different percentage by volume. Applying the normalization methodology used in the Composite Materials Handbook [9,10], a normalizing volume fraction of 0.4% was chosen, assuming that stiffness properties have a linear relationship with volume fraction as a first approximation. Then, a metadata analysis of unidirectional NFRC was carried out. The following scheme, Figure 1, illustrates the working process applied to the experimental data.
-[[File:Review_535961494455_8445_FIG1 Esquema_3.gif]]
+[[File:Review_535961494455_8445_FIG1 Esquema_3.gif|1131x1131px]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
@@ Line 70: / Line 70: @@
 a)
-[[File:Review_535961494455_2102_Fig2a natural non natural.jpg]]
+[[File:Review_535961494455_2102_Fig2a natural non natural.jpg|1148x1148px]]
 b)
-[[File:Review_535961494455_8302_Fig2b EX 0 90.jpg]]
+[[File:Review_535961494455_8302_Fig2b EX 0 90.jpg|1132x1132px]]
 Figure 2a The linear relationship between the longitudinal tensile modulus and its trace for natural and non-natural composites. b) Comparison of trace-normalized longitudinal modulus and their ratio respect to [0/90].
@@ Line 178: / Line 178: @@
 :1)
-[[File:Review_535961494455_6293_Fib3a stress enveloppes.jpg]]
+[[File:Review_535961494455_6293_Fib3a stress enveloppes.jpg|1135x1135px]]
 :2)
-[[File:Review_535961494455_6756_Fib3b equivalent circle.jpg]]
+[[File:Review_535961494455_6756_Fib3b equivalent circle.jpg|1151x1151px]]
 :3)
-[[File:Review_535961494455_8323_Fib3c R normal.jpg]]
+[[File:Review_535961494455_8323_Fib3c R normal.jpg|1163x1163px]]
 <span id='_GoBack'></span>

@@ Line 17: / Line 17: @@
 The experimental data with relevant information on the elastic properties of unidirectional flax, hemp, and kenaf composites are obtained from scientific publications, dissertations, and published reviews [5-7]. They are classified according to the type of load,  and the presence or absence of chemical modification. Logically, each composite is manufactured with a different percentage by volume. Applying the normalization methodology used in the Composite Materials Handbook [9,10], a normalizing volume fraction of 0.4% was chosen, assuming that stiffness properties have a linear relationship with volume fraction as a first approximation. Then, a metadata analysis of unidirectional NFRC was carried out. The following scheme, Figure 1, illustrates the working process applied to the experimental data.
-[[File:Review_535961494455_4405_FIG1 Esquema.gif]]
+[[File:Review_535961494455_8445_FIG1 Esquema_3.gif]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">

@@ Line 1: / Line 1: @@
@@ Line 18: / Line 17: @@
 The experimental data with relevant information on the elastic properties of unidirectional flax, hemp, and kenaf composites are obtained from scientific publications, dissertations, and published reviews [5-7]. They are classified according to the type of load,  and the presence or absence of chemical modification. Logically, each composite is manufactured with a different percentage by volume. Applying the normalization methodology used in the Composite Materials Handbook [9,10], a normalizing volume fraction of 0.4% was chosen, assuming that stiffness properties have a linear relationship with volume fraction as a first approximation. Then, a metadata analysis of unidirectional NFRC was carried out. The following scheme, Figure 1, illustrates the working process applied to the experimental data.
+[[File:Review_535961494455_4405_FIG1 Esquema.gif]]
-[[Image:Draft_Cantera_370995223-picture-Lienzo 16.svg|center|600px]]
 <div class="center" style="width: auto; margin-left: auto; margin-right: auto;">
@@ Line 72: / Line 70: @@
 a)
-[[Image:Draft_Cantera_370995223-image12.png|432px|alt='b)'|b)]]
+[[File:Review_535961494455_2102_Fig2a natural non natural.jpg]]
 b)
-[[Image:Draft_Cantera_370995223-image13.png|510px]]
+[[File:Review_535961494455_8302_Fig2b EX 0 90.jpg]]
 Figure 2a The linear relationship between the longitudinal tensile modulus and its trace for natural and non-natural composites. b) Comparison of trace-normalized longitudinal modulus and their ratio respect to [0/90].
@@ Line 180: / Line 178: @@
 :1)
-[[Image:Draft_Cantera_370995223-image20.png|402px|alt=':2) '|:2) ]]
+[[File:Review_535961494455_6293_Fib3a stress enveloppes.jpg]]
 :2)
-:3)   [[Image:Draft_Cantera_370995223-image21.png|336px]]
+[[File:Review_535961494455_6756_Fib3b equivalent circle.jpg]]
-<span id='_GoBack'></span>   [[Image:Draft_Cantera_370995223-image22.png|402px]]
+<span id='_GoBack'></span>
 Figure 3 a) The Omni Stress Envelope of different Flax composites with the same lay-up, b) equivalent circle of radius R with the same area as the stress envelope, c) linear relation between the trace normalize parameters of Radius and major Diameter

@@ Line 12: / Line 12: @@
 The invariants-based design theory used can be applied not only to man-made composites, but also to any orthotropic laminate [3]. Mathematically, the stiffness tensor trace, Tr, is a property of each material, regardless of the lay-up of the composite [4]. In this sense, the trace can be used to scale the stiffness of different materials and to rank them in a hierarchy.
-This study first establishes an empirical relationship between the trace Tr and the longitudinal, transversal, and shear modulus of elasticity for flax [5], hemp [6] ,and kenaf [7]. This means that knowing one parameter such as the trace, enables the others to be determined. This is achieved for tension in the present study. Secondly, parameters related to the area of the Omni are proposed. These parameters are then used to calculate the empirical relationship in 14 configurations of Double-Double[8] with longitudinal tensile strength (X<sub>T</sub>) and longitudinal compressive strength (X<sub>C</sub>). Thirdly, it provides a means of comparing the NFRCs with each other and with other composites.
+This study first establishes an empirical relationship between the trace Tr and the longitudinal, transversal, and shear modulus of elasticity for flax [5], hemp [6], and kenaf [7]. This means that knowing one parameter, such as the trace, enables the others to be determined. This is achieved for tensile in teensileii the present study. Secondly, parameters related to the area of the Omni are proposed. These parameters are then used to calculate the empirical relationship in 14 configurations of Double-Double[8] with longitudinal tensile strength (X<sub>T</sub>) and longitudinal compressive strength (X<sub>C</sub>). Thirdly, it provides a means of comparing the NFRCs with each other and with other composites.
 =2. Materials and Methods=
@@ Line 36: / Line 36: @@
 |}
+Some exact values of the trace-normalised values will be calculated by equation 2 for the longitudinal, transversal and shear moduli [5-7].
-Some exact values of the trace-normalised values will be calculated in accordance with equation 2 for the longitudinal, transversal and shear moduli [5-7].
 {| class="formulaSCP" style="width: 100%;margin: 1em auto 0.1em auto;border-collapse: collapse;width: 100%;text-align: center;"
@@ Line 61: / Line 60: @@
 |}
-If the longitudinal tensile modulus (𝐸x) is plotted against the trace, a unique property of NFRPs are revealed: the trace normalized modulus  [[Image:Draft_Cantera_370995223-image11.png|78px]] with a very low Coefficient Of Variation (CoV). Similarly, this can be done with transversal and shear moduli.
+The concept of Master Ply [3] is be used to simplify the design by representing the average values of all laminates in a family and obtaining normalised values. These values are used to represent a specific family of composites, taking into account a scaled material factor (stiffness and strength). Tsai and Melo [3] proposed the Omni Strain Failure Envelopes. The area of the failure envelopes in both stress and strain space is an important parameter for representing the strength of a material/laminate and generating master envelopes. In strain space, the failure envelope of a ply is invariant, independent of the presence of adjacent plies. In a generic multidirectional laminate, the inner envelope covers any lay-up configuration and is controlled by the [0] and [90] plies. Therefore, it is a material prrtyty . To avoid scatter, these radius values can be normalized
-−
-The concept of Master Ply [3] is be used to simplify the design by representing the average values of all laminates in a family and obtaining normalised values. These values are used to represent a specific family of composites, taking into account a scaled material factor (stiffness and strength). Tsai and Melo [3] proposed the Omni Strain Failure Envelopes. The area of the failure envelopes in both stress and strain space is an important parameter for representing the strength of a material/laminate and generating master envelopes. In strain space, the failure envelope of a ply is invariant, independent of the presence of adjacent plies. In a generic multidirectional laminate, the inner envelope covers any lay-up configuration and is controlled by the [0] and [90] plies. Therefore, it is a material propety . To avoid scatter, these radius values can be normalized
 by dividing by the Master Ply radius, R<sub>MasterPly</sub> which is the average radius of all the Unidirectional composites considered in this study. The major diameter of the stress space envelopes D can also be used as a parameter for the strength of the composites.
@@ Line 70: / Line 68: @@
 =3. Results=
-To compare the stiffness of different types of composites, natural and non-natural the same dimensionless parameter can be used. All values show a linear relationship on a double logarithmic scale, with different slope ssnd CoV a s it is shown in Figure2   The ratio of the tensile normalized modulus of different lay-ups with [0/90] as the baseline is shown in Figure 2b, for the synthetic and natural fibers listed in Table1
+To compare the stiffness of different types of composites, natural and non-natural the same dimensionless parameter can be used. All values show a linear relationship on a double logarithmic scale, with different slope ssad CoV a  it is shown in Figure2  .The ratio of the tensile normalized modulus of different lay-ups with [0/90] as the baseline is shown in Figure 2b, for the synthetic and natural fibers listed in Table1
 a)
@@ Line 80: / Line 78: @@
 [[Image:Draft_Cantera_370995223-image13.png|510px]]
-Figure 2 a) The linear relationship between the longitudinal tensile modulus and its trace for natural and non-natural composites. b) Comparison of trace-normalized longitudinal modulus and their ratio respect to [0/90].
+Figure 2a The linear relationship between the longitudinal tensile modulus and its trace for natural and non-natural composites. b) Comparison of trace-normalized longitudinal modulus and their ratio respect to [0/90].
-The Table 1 shows the values and coefficients of variation for the trace normalised modulus and the ratio of material properties of different composites. The CoV of the Nis are reasonable, considering the typical scatter of mechanical properties in NFs. It is noteworthy that the relative mechanical behaviour of the unidirectional NFRP with respect to the cross-ply is very similar to that of human-made composites, and the ratio<span style="text-align: center; font-size: 75%;"> [[Image:Draft_Cantera_370995223-image14.png|96px]] </span>is better than synthetic composites.
+The Table 1 shows the values and coefficients of variation for the trace normalised modulus and the ratio of material properties of different composites. The CoV of the is are reasonable, considering the typical scatter of mechanical properties in NFs. It is noteworthy that the relative mechanical behaviour of the unidirectional NFRP with respect to the cross-ply is very similar to that of human-made composites, and  ratio<span style="text-align: center; font-size: 75%;"> [[Image:Draft_Cantera_370995223-image14.png|96px]] </span>is better than synthetic composites.
 Table 1 Trace-normalized tensile mechanical properties of common composite families, the CoV is given in parentheses.
@@ Line 174: / Line 172: @@
 :* First, superposition in strain space is used to define an envelope that is independent of the lay-up.
-:* Second, convert it into the stress space. The Omni Stress Envelope The Last Ply Failure (LPF) of Omni Envelope depends on the tensile and compressive strength ,XT and XC.  Assuming that, after matrix Degradation in the LPF hdoes not influencethe transverse and shear properties. The shape of the failure envelopes depends on the configuration of the laminate, as it is shown in Figure 3a
+:* Second, convert it into the stress space. The Omni Stress Envelope The Last Ply Failure (LPF) of the Omni Envelope depends on the tensile and compressive strength,X T and XC.  Assuming that, after matrix Degradation in the LPF does not influence the transverse and shear properties. The shape of the failure envelopes depends on the configuration of the laminate, as it is shown in Figure 3a
 :* Third, to simplify the structures, the largest diameter D and the area was identified for each case. To unify the area of all the envelopes, a radius R of a circle of equivalent area was calculated, as it is shown in Figure 3b. The average radius is related to the radius of the Master Ply and the absolute values and normalized to the radius of the Master Ply radius, giving R*.
@@ Line 190: / Line 188: @@
 <span id='_GoBack'></span>   [[Image:Draft_Cantera_370995223-image22.png|402px]]
-Figure3 a) The Omni Stress Envelope of different Flax composites with the same lay-up, b) equivalent circle of radius R with the same area than the stress envelope, c) linear relation between the trace normalize parameters of Radius and major Diameter
+Figure 3 a) The Omni Stress Envelope of different Flax composites with the same lay-up, b) equivalent circle of radius R with the same area as the stress envelope, c) linear relation between the trace normalize parameters of Radius and major Diameter
 =4. Discussion=
@@ Line 204: / Line 202: @@
 Having a single parameter, R, that is directly connected with the area of the Omni Stress Envelope is also a great advantage in terms of strength.
-<strong style="text-align: left;">Acknowledgments</strong>  The author is particularly grateful to Professor Steve Tsai for the intensive exchange, many valuable discussions on this subject and beyond, and also for providing access to the Stanford’s Composites Workshop in various years.The author would like to thank  Arushi Surve, Bruno Pech of the Alliance for European Flax-Linen & Hemp, and their reviewers for their time and useful comments. The author gratefully acknowledges the financial support of the University of the Basque Country (UPV/EHU) in the Research Group GIU21/015 “Mechanics of Materials”
+<strong style="text-align: left;">Acknowledgments</strong>  The author is particularly grateful to Professor Steve Tsai for the intensive exchange, many valuable discussions on this subject and beyond, and also for providing access to the Stanford’s Composites Workshop in various ye ars.The author would like to thank  Arushi Surve, Bruno Pech of the Alliance for European Flax-Linen & Hemp, and their reviewers for their time and useful comments. The author gratefully acknowledges the financial support of the University of the Basque Country (UPV/EHU) in the Research Group GIU21/015 “Mechanics of Materials”
 =6.    Biography=

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