deploy: 61e9a66

.buildinfo

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+# Sphinx build info version 1
+# This file hashes the configuration used when building these files. When it is not found, a full rebuild will be done.
+config: 7770ac101390891c9405bb100244e8be
+tags: 645f666f9bcd5a90fca523b33c5a78b7

_sources/contents/changelog.rst.txt

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+Change log
+==========
+
+**VERSION 1.4**
+
+- 1.4.3 (2022/01/11)
+
+  - Fixed the issue of plotting element stress and strain results.
+  - Fixed the issue of plotting dehomogenization results with quadratic elements.
+  - Added groups for different stress and strain plots.
+  - Added alternative tag names for material strength properties.
+  - Added visualization for initial failure analysis results.
+  - Added a new example for initial failure analysis (ex\_uh60a\_f).
+  - Simplifed and unified material strength inputs for different types of materials.
+  - Updated the section of material strength property input in the documentation.
+
+- 1.4.2 (2021/11/05)
+
+  - Fixed an issue related with layer generation.
+
+- 1.4.1 (2021/09/01)
+
+  - Fixed an issue in assigning theta1 and theta3 for filling components.
+
+- 1.4.0 (2021/06/16)
+
+  - Added a new command option to run integrated VABS.
+  - Added new inputs for the rotor blade specific parameterization.
+  - Added new inputs for strength property of 'lamina' type materials.
+  - Added new inputs for assigning orientations for filling materials.
+  - Added a new input option for recover analysis in VABS. The default is linear beam theory.
+  - Added a new input option for setting the tolerance used in geometric computation.
+  - Added the capability of failure analysis using VABS.
+  - Updated the logging system.
+  - Changed the default element type to 'quadratic'.
+  - Unified the input syntax of recovery/dehomogenization of VABS/SwfitComp.
+  - Fixed the issue of incorrectly parsing numbers with more than one spaces between numbers.
+  - Fixed an issue in transforming an arc defined by center, start and radius.
+
+**VERSION 1.3**
+
+* 1.3.0 (2021/02/25)
+
+  * Added a new capability to create base points using normalized parametric locations on a base line.
+  * Added a new capability to assign local mesh size for filling components.
+
+
+**VERSION 1.2**
+
+* 1.2.0 (2020/11/10)
+
+  * Added a new capability to create layups from sublayups.
+  * Added a new capability to create segments using normalized parametric locations on a base line.
+
+
+**VERSION 1.1**
+
+* 1.1.1 (2020/10/28)
+
+  * Fixed the problem of unable to read recover analysis result files on Linux.
+  * Fixed a problem when the segment is too short while the laminate is too thick.
+
+* 1.1.0 (2020/10/15)
+
+  * Added a new format for the input file. Now baselines and layups data are merged into the main input file, to reduce the number of input files needed.
+  * Added a new material type 'lamina' accepting four numbers for elastic properties.
+  * Added default small numbers for elastic properties for isotropic materials.
+  * Updated the fill-type component for non-structural mass.
+
+
+**VERSION 1.0** (2019/07/01)
+
+* Added capability to create quadratic triangle elements. In the main input file, under the xml element `<general>`, create a sub element `<element_type>` and set it to `quadratic` or `2`. Default is `linear`.
+* Added a new output file `*.txt` storing all running messages.
+* Changed one of the layup methods tag name from 'explict list' ('el') to 'layer list' ('ll').
+* Fixed the crashing issue caused by zero number of layers.
+* Fixed the bug that sectional loads were read and written to the distributed loads when doing recovery using VABS.
+* Fixed the bug that local lamina data does not overwrite global data.
+
+
+**VERSION 0.6** (2018/07/01)
+
+* Added xml elements in the main input file for various options of VABS/SwiftComp execution.
+* Added xml elements in the main input file for failure analysis of SwiftComp.
+* Added a `<basepoints>` element in the baseline file. Now for simple shapes, users do not need to use an extra basepoint file, which can still be included for long point list.
+* Added a material database file along with the executable. Now PreVABS will look for materials in this file by default.
+* Changed Gmsh library to dynamic/shared library.
+
+
+**VERSION 0.5** (2018/01/31)
+
+* Added the capability to create nose mass in an airfoil type cross section.
+* Added the post-processing function to visualize the recovered strains and stresses in Gmsh.
+
+
+**VERSION 0.4** (2017/12/04)
+
+* Added the capability to read stacking sequence code.
+* Added the parameter to set the number of straight lines to approximate an arc or circle.
+* Changed the Gmsh input file name to `*.msh`, where `*` is the cross section name.
+
+
+**VERSION 0.3** (2017/11/27)
+
+* Updated the manual.
+* Changed the default behaviour of the command with input file specified only to preparing VABS input (without running VABS).
+* Changed the element tag `<origin>` to `<translate>`. Now the two numbers in this element moves base points and base lines, instead of the origin.
+* Changed the element tag `<rotation>` to `<rotate>`.
+* Changed the 'level' of a segment from an element to an attribute, with default 1.
+* Changed the 'layup_direction' of a segment from an element to an attribute of the layup, with default 'right'.
+* Changed the material type 'engineering constants' to 'orthotropic'.
+* Set the default element type as 'quadratic'.
+* Set the default mesh size to the smallest layer thickness.
+

_sources/contents/examples.rst.txt

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+Examples
+========
+
+.. toctree::
+   :maxdepth: 1
+   :caption: Table of Contents
+
+   examples/example_box
+   examples/example_pipe
+   examples/example_tube
+   examples/example_channel
+   examples/example_airfoil
+   examples/example_airfoil_recover
+   examples/example_uh60a_fi
+
+.. example_ibeam

_sources/contents/examples/example_airfoil.rst.txt

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+.. _section-airfoil:
+
+Airfoil (MH-104)
+================
+
+Problem description
+-------------------
+
+.. figure:: /figures/examplemh1040.png
+  :name: fig_mh104_draw
+  :width: 5.5in
+  :align: center
+
+  Sketch of a cross section for a typical wind turbine blade [CHEN2010]_.
+
+This example demonstrates the capability of building a cross section having an airfoil shape, which is commonly seen on wind turbine blades or helicopter rotor blades.
+This example is also studied in [CHEN2010]_.
+A sketch of a cross section for a typical wind turbine blade is shown in :numref:`Fig. %s <fig_mh104_draw>`.
+The airfoil is MH 104 (http://m-selig.ae.illinois.edu/ads/coord_database.html#M).
+In this example, the chord length :math:`CL=1.9` m.
+The origin O is set to the point at 1/4 of the chord.
+Twist angle :math:`\theta` is :math:`0^\circ`.
+There are two webs, whose right boundaries are at the 20% and 50% location of the chord, respectively.
+Both low pressure and high pressure surfaces have four segments.
+The dividing points between segments are listed in :numref:`Table %s <table_div_pts>`.
+Materials are given in :numref:`Table %s <table_mh104_materials>` and layups are given in :numref:`Table %s <table_mh104_layups>`.
+A complete :math:`6\times 6` stiffness matrix is given in :numref:`Table %s <table_airfoil_result>`.
+Complete input files can be found in ``examples\ex_airfoil\``, including ``mh104.xml``, ``basepoints.dat``, ``baselines.xml``, ``materials.xml``, and ``layups.xml``.
+
+.. csv-table:: Dividing points
+  :name: table_div_pts
+  :header-rows: 2
+  :align: center
+
+  "Between segments", "Low pressure surface", "High pressure surface"
+  , ":math:`(x, y)`", ":math:`(x, y)`"
+  "1 and 2", "(0.004053940, 0.011734800)", "(0.006824530, -0.009881650)"
+  "2 and 3", "(0.114739930, 0.074571970)", "(0.126956710, -0.047620490)"
+  "3 and 4", "(0.536615950, 0.070226120)", "(0.542952100, -0.044437080)"
+
+.. figure:: /figures/examplemh1041.png
+  :name: fig_mh1041
+  :width: 6.5in
+  :align: center
+
+  *Base point*\ s of the tube cross section.
+
+.. figure:: /figures/examplemh1042.png
+  :name: fig_mh1042
+  :width: 6.5in
+  :align: center
+
+  *Base line*\ s of the tube cross section.
+
+.. figure:: /figures/examplemh1043.png
+  :name: fig_mh1043
+  :width: 6.5in
+  :align: center
+
+  *Segment*\ s of the tube cross section.
+
+.. figure:: /figures/examplemh1044.png
+  :name: fig_mh104
+  :width: 6.5in
+  :align: center
+
+  Meshed cross section viewed in Gmsh.
+
+.. csv-table:: Material properties
+  :name: table_mh104_materials
+  :header-rows: 2
+  :align: center
+
+  "Name", "Type", "Density", |e1|, |e2|, |e3|, |g12|, |g13|, |g23|, |nu12|, |nu13|, |nu23|
+   , , |den_si_k|, |mod_si_g|, |mod_si_g|, |mod_si_g|, |mod_si_g|, |mod_si_g|, |mod_si_g|, , ,
+  "Uni-directional FRP", "orthotropic", 1.86, 37.00, 9.00, 9.00, 4.00, 4.00, 4.00, 0.28, 0.28, 0.28
+  "Double-bias FRP", "orthotropic", 1.83, 10.30, 10.30, 10.30, 8.00, 8.00, 8.00, 0.30, 0.30, 0.30
+  "Gelcoat", "orthotropic", 1.83, 1e-8, 1e-8, 1e-8, 1e-9, 1e-9, 1e-9, 0.30, 0.30, 0.30
+  "Nexus", "orthotropic", 1.664, 10.30, 10.30, 10.30, 8.00, 8.00, 8.00, 0.30, 0.30, 0.30
+  "Balsa", "orthotropic", 0.128, 0.01, 0.01, 0.01, 2e-4, 2e-4, 2e-4, 0.30, 0.30, 0.30
+
+.. csv-table:: Layups
+  :name: table_mh104_layups
+  :header-rows: 2
+  :align: center
+
+  "Name", "Layer", "Material", "Ply thickness", "Orientation", "Number of plies"
+  , , , |len_si|, :math:`\circ`,
+  "layup_1", 1, "Gelcoat",         0.000381, 0, 1
+  ,          2, "Nexus",           0.00051, 0, 1
+  ,          3, "Double-bias FRP", 0.00053, 20, 18
+  "layup_2", 1, "Gelcoat",         0.000381, 0, 1
+  ,          2, "Nexus",           0.00051, 0, 1
+  ,          3, "Double-bias FRP", 0.00053, 20, 33
+  "layup_3", 1, "Gelcoat",             0.000381, 0, 1
+  ,          2, "Nexus",               0.00051, 0, 1
+  ,          3, "Double-bias FRP",     0.00053, 20, 17
+  ,          4, "Uni-directional FRP", 0.00053, 30, 38
+  ,          5, "Balsa",               0.003125, 0, 1
+  ,          6, "Uni-directional FRP", 0.00053, 30, 37
+  ,          7, "Double-bias FRP",     0.00053, 20, 16
+  "layup_4", 1, "Gelcoat",         0.000381, 0, 1
+  ,          2, "Nexus",           0.00051, 0, 1
+  ,          3, "Double-bias FRP", 0.00053, 20, 17
+  ,          4, "Balsa",           0.003125, 0, 1
+  ,          5, "Double-bias FRP", 0.00053, 0, 16
+  "layup_web", 1, "Uni-directional FRP", 0.00053, 0, 38
+  ,            2, "Balsa",               0.003125, 0, 1
+  ,            3, "Uni-directional FRP", 0.00053, 0, 38
+
+
+
+
+
+Result
+------
+
+.. table:: Effective Timoshenko stiffness matrix
+   :name: table_airfoil_result
+
+   =================================== =================================== =================================== =================================== =================================== ===================================
+   :math:`\phantom{-}2.395\times 10^9` :math:`\phantom{-}1.588\times 10^6` :math:`\phantom{-}7.215\times 10^6` :math:`-3.358\times 10^7`           :math:`\phantom{-}6.993\times 10^7` :math:`-5.556\times 10^8`
+   :math:`\phantom{-}1.588\times 10^6` :math:`\phantom{-}4.307\times 10^8` :math:`-3.609\times 10^6`           :math:`-1.777\times 10^7`           :math:`\phantom{-}1.507\times 10^7` :math:`\phantom{-}2.652\times 10^5`
+   :math:`\phantom{-}7.215\times 10^6` :math:`-3.609\times 10^6`           :math:`\phantom{-}2.828\times 10^7` :math:`\phantom{-}8.440\times 10^5` :math:`\phantom{-}2.983\times 10^5` :math:`-5.260\times 10^6`
+   :math:`-3.358\times 10^7`           :math:`-1.777\times 10^7`           :math:`\phantom{-}8.440\times 10^5` :math:`\phantom{-}2.236\times 10^7` :math:`-2.024\times 10^6`           :math:`\phantom{-}2.202\times 10^6`
+   :math:`\phantom{-}6.993\times 10^7` :math:`\phantom{-}1.507\times 10^7` :math:`\phantom{-}2.983\times 10^5` :math:`-2.024\times 10^6`           :math:`\phantom{-}2.144\times 10^7` :math:`-9.137\times 10^6`
+   :math:`-5.556\times 10^8`           :math:`\phantom{-}2.652\times 10^5` :math:`-5.260\times 10^6`           :math:`\phantom{-}2.202\times 10^6` :math:`-9.137\times 10^6`           :math:`\phantom{-}4.823\times 10^8`
+   =================================== =================================== =================================== =================================== =================================== ===================================
+
+.. table:: Results from reference [CHEN2010]_
+   :name: table_airfoil_result_ref
+
+   =================================== =================================== =================================== =================================== =================================== ===================================
+   :math:`\phantom{-}2.389\times 10^9` :math:`\phantom{-}1.524\times 10^6` :math:`\phantom{-}6.734\times 10^6` :math:`-3.382\times 10^7`           :math:`-2.627\times 10^7`           :math:`-4.736\times 10^8`
+   :math:`\phantom{-}1.524\times 10^6` :math:`\phantom{-}4.334\times 10^8` :math:`-3.741\times 10^6`           :math:`-2.935\times 10^5`           :math:`\phantom{-}1.527\times 10^7` :math:`\phantom{-}3.835\times 10^5`
+   :math:`\phantom{-}6.734\times 10^6` :math:`-3.741\times 10^6`           :math:`\phantom{-}2.743\times 10^7` :math:`-4.592\times 10^4`           :math:`-6.869\times 10^2`           :math:`-4.742\times 10^6`
+   :math:`-3.382\times 10^7`           :math:`-2.935\times 10^5`           :math:`-4.592\times 10^4`           :math:`\phantom{-}2.167\times 10^7` :math:`-6.279\times 10^4`           :math:`\phantom{-}1.430\times 10^6`
+   :math:`-2.627\times 10^7`           :math:`\phantom{-}1.527\times 10^7` :math:`-6.869\times 10^2`           :math:`-6.279\times 10^4`           :math:`\phantom{-}1.970\times 10^7` :math:`\phantom{-}1.209\times 10^7`
+   :math:`-4.736\times 10^8`           :math:`\phantom{-}3.835\times 10^5` :math:`-4.742\times 10^6`           :math:`\phantom{-}1.430\times 10^6` :math:`\phantom{-}1.209\times 10^7` :math:`\phantom{-}4.406\times 10^8`
+   =================================== =================================== =================================== =================================== =================================== ===================================
+
+.. note:: The errors between the result and the reference are caused by the difference of modeling of the trailing edge. If reduce the trailing edge skin to a single thin layer, then the difference between the trailing edge shapes is minimized, and the two resulting stiffness matrices are basically the same, as shown in :numref:`Fig. %s <fig_mh104_comparison>`.
+
+.. figure:: /figures/examplemh104_comparison.png
+  :name: fig_mh104_comparison
+  :width: 6in
+  :align: center
+
+  Comparison of stiffness matrices after modifying the trailing edge.
+

_sources/contents/examples/example_airfoil_recover.rst.txt

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+.. _example-airfoil-recover:
+
+Airfoil (Recover)
+=================
+
+Problem description
+-------------------
+
+This example continues from the  previous one to demonstrate the
+dehomogenization analysis. It is assumed that a 1D beam analysis has
+been finished, and data of global deformations and loads have been
+added to the main input file correctly
+(:ref:`See the recover section <section-recover>`). Suppose that the
+results in :numref:`Table %s <table_mh104_1dresults>` are used and
+default values are kept for others. All files generated from the VABS
+homogenization analysis are kept in the same place as input files.
+Final visualization is required and the contour plot of one of the
+stress components is shown in :numref:`Fig. %s <fig_mh104r>`.
+Complete files can be found in ``examples\ex_airfoil_r\``, including
+``mh104.xml``, ``basepoints.dat``, ``baselines.xml``, ``materials.xml``,
+``layups.xml``, ``mh104.sg``, ``mh104.sg.ech``,
+``mh104.sg.K``, ``mh104.sg.opt``, ``mh104.sg.v0``,
+``mh104.sg.v1S``, and ``mh104.sg.v22``.
+
+.. csv-table:: Sectional forces and moments
+  :name: table_mh104_1dresults
+  :header-rows: 1
+  :align: center
+
+  Quantity, Value
+  ":math:`F_1`, N", 1
+  ":math:`F_2`, N", 2
+  ":math:`F_3`, N", 3
+  ":math:`M_1`, Nm", 4
+  ":math:`M_2`, Nm", 5
+  ":math:`M_3`, Nm", 6
+
+
+
+
+
+Result
+------
+
+.. figure:: /figures/examplemh104r.png
+  :name: fig_mh104r
+  :width: 6in
+  :align: center
+
+  Contour plot of recovered nodal stress SN11.
+