Exploded views demo in caps2tacs (smdogroup#285)

* demonstrate exploded views

* remove autosave csm and merge

examples/caps_wing/1_steady_analysis.py

@@ -20,7 +20,9 @@
 
 print(f"proc on rank {comm.rank}")
 
-tacs_model = caps2tacs.TacsModel.build(csm_file="simple_naca_wing.csm", comm=comm, active_procs=[0])
+tacs_model = caps2tacs.TacsModel.build(
+    csm_file="simple_naca_wing.csm", comm=comm, active_procs=[0]
+)
 tacs_model.mesh_aim.set_mesh(
     edge_pt_min=15,
     edge_pt_max=20,

examples/caps_wing/4_sizing_and_shape.py

@@ -12,7 +12,9 @@
 # Setup CAPS Problem
 # --------------------------------------------------------------#
 comm = MPI.COMM_WORLD
-tacs_model = caps2tacs.TacsModel.build(csm_file="large_naca_wing.csm", comm=comm, active_procs=[0])
+tacs_model = caps2tacs.TacsModel.build(
+    csm_file="large_naca_wing.csm", comm=comm, active_procs=[0]
+)
 tacs_model.mesh_aim.set_mesh(  # need a refined-enough mesh for the derivative test to pass
     edge_pt_min=15,
     edge_pt_max=20,

examples/caps_wing/7_multiproc_post_analysis.py

@@ -36,7 +36,9 @@
 # Setup CAPS Problem
 # --------------------------------------------------------------#
 comm = MPI.COMM_WORLD
-tacs_model = caps2tacs.TacsModel.build(csm_file="large_naca_wing.csm", comm=comm, active_procs=[0,1])
+tacs_model = caps2tacs.TacsModel.build(
+    csm_file="large_naca_wing.csm", comm=comm, active_procs=[0, 1]
+)
 tacs_model.mesh_aim.set_mesh(  # need a refined-enough mesh for the derivative test to pass
     edge_pt_min=15,
     edge_pt_max=20,
@@ -115,4 +117,4 @@
 naims = len(tacs_model.active_procs)
 if comm.rank == 0:
     print(f"Elapsed time with {naims} procs is {mins_elapsed} mins using 4 shape vars.")
-    print(f"Also each post analysis took {post_analysis_time/60.0:.4f} min", flush=True)
+    print(f"Also each post analysis took {post_analysis_time/60.0:.4f} min", flush=True)

examples/caps_wing/8_make_exploded_views.py

@@ -0,0 +1,110 @@
+"""
+Sean Engelstad, Febuary 2023
+GT SMDO Lab, Dr. Graeme Kennedy
+Caps to TACS example
+
+December 1, 2023
+Run this with conda-mpirun -n 3 python 8_make_exploded_view.py
+    Then process the f5 files which are moved to the exploded folder.
+"""
+
+from tacs import caps2tacs
+from mpi4py import MPI
+import os, shutil
+
+# run a steady elastic structural analysis in TACS using the tacsAIM wrapper caps2tacs submodule
+# -------------------------------------------------------------------------------------------------
+# 1: build the tacs aim, egads aim wrapper classes
+
+comm = MPI.COMM_WORLD
+
+print(f"proc on rank {comm.rank}")
+
+tacs_model = caps2tacs.TacsModel.build(
+    csm_file="large_naca_wing.csm",
+    comm=comm,
+    problem_name="capsExploded",
+    active_procs=[_ for _ in range(3)],
+)
+tacs_model.mesh_aim.set_mesh(
+    edge_pt_min=15,
+    edge_pt_max=20,
+    global_mesh_size=0.25,
+    max_surf_offset=0.01,
+    max_dihedral_angle=15,
+).register_to(tacs_model)
+
+# set the exploded views to 1,2,3 for each of the 3 separate procs
+tacs_aim = tacs_model.tacs_aim
+exploded_view = comm.rank + 1
+tacs_aim.set_config_parameter("exploded", exploded_view)
+
+aluminum = caps2tacs.Isotropic.aluminum().register_to(tacs_model)
+
+# setup the thickness design variables + automatic shell properties
+# choose pattern based dv1 values
+nribs = int(tacs_model.get_config_parameter("nribs"))
+nspars = int(tacs_model.get_config_parameter("nspars"))
+nOML = nribs - 1
+
+if exploded_view == 2:  # only make these internal struct variables on proc 1 tacs model
+    for irib in range(1, nribs + 1):
+        caps2tacs.ThicknessVariable(
+            caps_group=f"rib{irib}", value=0.1 - 0.01 * irib, material=aluminum
+        ).register_to(tacs_model)
+    for ispar in range(1, nspars + 1):
+        caps2tacs.ThicknessVariable(
+            caps_group=f"spar{ispar}", value=0.1 - 0.01 * irib, material=aluminum
+        ).register_to(tacs_model)
+
+if exploded_view in [
+    1,
+    3,
+]:  # only make these OML struct variables on procs 0,2 tacs model
+    for iOML in range(1, nOML + 1):
+        caps2tacs.ThicknessVariable(
+            caps_group=f"OML{iOML}", value=0.1 - 0.01 * iOML, material=aluminum
+        ).register_to(tacs_model)
+
+# add constraints and loads
+caps2tacs.PinConstraint("root").register_to(tacs_model)
+caps2tacs.GridForce("OML", direction=[0, 0, 1.0], magnitude=100).register_to(tacs_model)
+
+# run the pre analysis to build tacs input files
+# alternative is to call tacs_aim.setup_aim().pre_analysis() with tacs_aim = tacs_model.tacs_aim
+tacs_model.setup()
+
+comm.Barrier()
+
+SPs = tacs_model.createTACSProbs(addFunctions=True)
+
+# make a directory for the exploded views
+exploded_dir = os.path.join(os.getcwd(), "exploded")
+if not os.path.exists(exploded_dir) and comm.rank == 0:
+    os.mkdir(exploded_dir)
+
+# create a mesh of each of the exploded views
+names = ["upperOML", "int-struct", "lowerOML"]
+for rank in range(3):
+    # create tacs problems in the tacs directory of this proc
+    SPs = tacs_model.createTACSProbs(root=rank)
+    # then write solution using all procs
+    for caseID in SPs:
+        SPs[caseID].writeSolution(
+            baseName=names[rank], outputDir=tacs_model.analysis_dir(proc=rank), number=0
+        )
+
+    # move the file to the exploded view directory
+    filename = names[rank] + "_000.f5"
+    src = os.path.join(tacs_model.analysis_dir(proc=rank), filename)
+    dest = os.path.join(exploded_dir, filename)
+
+    if comm.rank == 0:
+        shutil.copy(src, dest)
+
+    comm.Barrier()
+
+print("Done creating exploded views for the large_naca_wing.csm..")
+print(
+    "\tGoto the exploded/ folder and process the f5 files to create an exploded view visualization!"
+)

examples/caps_wing/large_naca_wing.csm

@@ -8,6 +8,7 @@
 # number of ribs and spars
 cfgpmtr nribs 10
 cfgpmtr nspars 2
+cfgpmtr exploded 0 # 0 - non-exploded, 1 upperOML, 2 internalStruct, 3 - lowerOML
 
 # root and tip chord
 despmtr chord0 2.0
@@ -58,7 +59,7 @@ rotatex 90 0 0
 translate xf -sspan zf
 
 # loft the solid wing and store it
-loft 0
+rule
 
 # attribute the solid wing
 select face
@@ -67,14 +68,22 @@ attribute capsLoad $OML
 attribute _color $blue
 
 # make root and tip caps the ribs
-select face 5
+select face 4
 attribute capsGroup $rib1
+attribute tagComp $rib
 attribute _color $green
 
-select face 4
+select face 5
 attribute capsGroup !$rib+nribs
+attribute tagComp $rib
 attribute _color $green
 
+select face 1
+attribute tagComp $OMLtop
+
+select face 2
+attribute tagComp $OMLbot
+
 store solidWing
 
 ### 2. Internal Structure ###
@@ -101,7 +110,7 @@ patbeg ispar nspars
    # add caps attributes
    select face
    attribute capsGroup !$spar+ispar
-   attribute has_group $yes
+   attribute tagComp $spar
    attribute _color $green
 patend
 
@@ -121,7 +130,7 @@ patbeg index ninnerRibs
    # add caps attributes
    select face
    attribute capsGroup !$rib+irib
-   attribute has_group $yes
+   attribute tagComp $rib
    attribute _color $green
 
    # union with previous ribs/spars
@@ -155,6 +164,9 @@ union
 select face $capsGroup $rib1
 attribute capsConstraint $root
 
+select face $capsGroup $*
+attribute has_group $yes
+
 # add the constraint attribute to adjacent edges, nodes
 # otherwise they can pop out of the mesh in the structural analysis
 udprim editAttr filename <<
@@ -173,11 +185,23 @@ udprim editAttr filename <<
  patend
 >>
 
+# extract only certain faces for the exploded view
+ifthen exploded EQ 1
+   select face $tagComp $OMLtop
+   extract @sellist
+elseif exploded EQ 2
+   select face $tagComp $rib
+   select add $tagComp $spar
+   extract @sellist
+elseif exploded EQ 3
+   select face $tagComp $OMLbot
+   extract @sellist
+endif
 
 # add AIM attribute to specify the analyses to use
 select body
 attribute capsAIM $egadsTessAIM;tacsAIM
 
 end
 |||||
-|||
+||||||||||

examples/caps_wing/simple_naca_wing.csm

@@ -59,7 +59,7 @@ rotatex 90 0 0
 translate xf -sspan zf
 
 # loft the solid wing and store it
-loft 0
+rule
 
 # attribute the solid wing
 select face

tacs/caps2tacs/tacs_aim.py

@@ -108,7 +108,9 @@ def get_proc_with_shape_var(self, shape_var: ShapeVariable or str):
                 if shape_var.name == this_shape_var.name:
                     return rank
         # if not found in for loop trigger error
-        raise AssertionError(f"failed to find shape var {shape_var} on rank {self.comm.rank}")
+        raise AssertionError(
+            f"failed to find shape var {shape_var} on rank {self.comm.rank}"
+        )
 
     @property
     def local_shape_vars(self) -> list:
@@ -130,7 +132,7 @@ def setup_aim(
         self,
         large_format: bool = True,
         static: bool = True,
-        barrier:bool=True,
+        barrier: bool = True,
     ):
         # make sure there is at least one material, property, constraint, etc.
         assert len(self._materials) > 0

tacs/caps2tacs/tacs_model.py

@@ -63,7 +63,7 @@ def build(
         active_procs: list = [0],
         problem_name: str = "capsStruct",
         mesh_morph: bool = False,
-        verbosity:int=0,
+        verbosity: int = 0,
     ):
         """
         make a pyCAPS problem with the tacsAIM and egadsAIM on serial / root proc
@@ -79,7 +79,7 @@ def build(
         tacs_project: str
             project name for all ESP/CAPS work directory files (affects filenames)
         active_procs: list
-            list of active procs for parallel tacsAIM instances. Ex: if you want to use 5 
+            list of active procs for parallel tacsAIM instances. Ex: if you want to use 5
             parallel tacsAIMs you can choose active_procs=[_ for _ in range(5)] or
             equivalently active_procs=[0,1,2,3,4]
         problem_name: str
@@ -93,7 +93,7 @@ def build(
         assert 0 in active_procs
         caps_problem = None
         assert mesh in cls.MESH_AIMS
-        assert max(active_procs)+1 <= comm.Get_size()
+        assert max(active_procs) + 1 <= comm.Get_size()
 
         for iproc in active_procs:
             if comm.rank == iproc:
@@ -291,19 +291,18 @@ def update_design(self, input_dict: dict = None):
 
         return changed_design
 
-    @property
-    def fea_solver(self) -> pyTACS:
+    def fea_solver(self, root=0) -> pyTACS:
         """
         build pyTACS from nastran dat file on the root proc
         """
-        return pyTACS(self.tacs_aim.dat_file_path(self.root_proc_ind), self.comm)
+        return pyTACS(self.tacs_aim.dat_file_path(root), self.comm)
 
-    def createTACSProbs(self, addFunctions: bool = True):
+    def createTACSProbs(self, root=0, addFunctions: bool = True):
         """
         creates TACS list of static, transient, or modal analysis TACS problems from the TacsAim class
         most important call method from the tacsAim class: SPs = tacs_aim.createTACSProbs
         """
-        fea_solver = self.fea_solver
+        fea_solver = self.fea_solver(root)
         fea_solver.initialize()
         SPs = fea_solver.createTACSProbsFromBDF()
         self.SPs = SPs  # store the static problems as well