attempt component tree

2 files changed, 9 insertions, 10 deletions

diff --git a/creator/base.py b/creator/base.py
index c46b297..24b452c 100644
--- a/creator/base.py
+++ b/creator/base.py
@@ -12,25 +12,24 @@ logging.basicConfig(filename='log.txt',
 
 class Aircraft:
     """This class tracks all sub-components and is fed to the evaluator."""
-    def __init__(self, parent, name):
-        self.parent = parent
+    def __init__(self, evaluator, name):
+        evaluator.tree.update({"aircraft": self})
+        self.evaluator = evaluator
         self.name = name
-        parent.aircrafts.append(name)
+        self.tree = []  # Nested list of subcomponents
 
 
 class Component:
-    """Basic component providing coordinates and tools."""
+    """Basic component providing coordinates, tools and a component tree."""
     def __init__(self, parent, name):
-        self.parent = None
+        self.tree = [name]
+        parent.tree.append(self.tree)
         self.name = name
         self.x = np.array([])
         self.z = np.array([])
         self.material = None
         self.mass = float()
 
-    def __str__(self):
-        return self.name
-
     def set_material(self, material):
         """Set the component bulk material."""
         self.material = material
diff --git a/creator/wing.py b/creator/wing.py
index 59f5bbe..cc7d29a 100644
--- a/creator/wing.py
+++ b/creator/wing.py
@@ -24,7 +24,7 @@ import resources.materials as mt
 class Airfoil(base.Component):
     """This class represents a single NACA airfoil.
 
-    The coordinates are saved as two lists
+    The coordinates are saved as two np.arrays
     for the x- and z-coordinates. The coordinates start at
     the leading edge, travel over the airfoil's upper edge,
     then loop back to the leading edge via the lower edge.
@@ -141,9 +141,9 @@ class Spar(base.Component):
         super().__init__(parent, name)
         super().set_material(material)
         self.cap_area = float()
-        loc = loc_percent * parent.chord
         # bi.bisect_left: returns index of first value in parent.x > loc
         # This ensures that spar geom intersects with airfoil geom.
+        loc = loc_percent * parent.chord
         # Spar upper coordinates
         spar_u = bi.bisect_left(parent.x, loc) - 1
         self.x = np.append(self.x, parent.x[spar_u])