enh: create nosecone, fins and tail attribute

rocketpy/AeroSurfaces.py

@@ -11,7 +11,7 @@
 
 
 class AeroSurfaces:
-    """Class used to hold multiple aerodynamic surfaces and their positions."""
+    """Class used to hold multiple aerodynamic surfaces."""
 
     def __init__(self):
         self._aeroSurfaces = []
@@ -25,17 +25,25 @@ def remove(self, aeroSurface):
                 self._aeroSurfaces.remove(aeroSurface)
 
     def pop(self, index=-1):
-        return self._aerosurfaces.pop(index)
-    
+        return self._aeroSurfaces.pop(index)
+
     def __repr__(self):
-        return self._aeroSurfaces.__str__
+        if len(self._aeroSurfaces) == 1:
+            return self._aeroSurfaces[0].__repr__()
+        return self._aeroSurfaces.__repr__()
 
     def __len__(self):
         return len(self._aeroSurfaces)
 
     def __getitem__(self, index):
         return self._aeroSurfaces[index]
 
+    def __getattr__(self, name):
+        if len(self._aeroSurfaces) == 1:
+            attr = getattr(self._aeroSurfaces[0], name)
+            return attr
+        return getattr(self._aeroSurfaces, name)
+
     def __iter__(self):
         return iter(self._aeroSurfaces)
 
@@ -78,7 +86,13 @@ class NoseCone:
     """
 
     def __init__(
-        self, length, kind, position, baseRadius=None, rocketRadius=None, name="Nose Cone"
+        self,
+        length,
+        kind,
+        position,
+        baseRadius=None,
+        rocketRadius=None,
+        name="Nose Cone",
     ):
         """Initializes the nose cone. It is used to define the nose cone
         length, kind, center of pressure and lift coefficient curve.
@@ -284,7 +298,7 @@ def allInfo(self):
         -------
         None
         """
-        self.geometricalInfo()        
+        self.geometricalInfo()
         self.aerodynamicInfo()
 
         return None
@@ -1642,7 +1656,9 @@ class Tail:
 
     """
 
-    def __init__(self, topRadius, bottomRadius, length, position, rocketRadius, name="Tail"):
+    def __init__(
+        self, topRadius, bottomRadius, length, position, rocketRadius, name="Tail"
+    ):
         """Initializes the tail object by computing and storing the most
         important values.
 

rocketpy/Rocket.py

@@ -214,6 +214,9 @@ def __init__(
 
         # Aerodynamic data initialization
         self.aerodynamicSurfaces = AeroSurfaces()
+        self.nosecone = AeroSurfaces()
+        self.fins = AeroSurfaces()
+        self.tail = AeroSurfaces()
         self.cpPosition = 0
         self.staticMargin = Function(
             lambda x: 0, inputs="Time (s)", outputs="Static Margin (c)"
@@ -482,8 +485,9 @@ def addTail(
         # Create new tail as an object of the Tail class
         tail = Tail(topRadius, bottomRadius, length, position, radius, name)
 
-        # Add tail to aerodynamic surfaces list
-        self.aerodynamicSurfaces.append(aeroSurface=tail)
+        # Add tail to aerodynamic surfaces and tail list
+        self.aerodynamicSurfaces.append(tail)
+        self.tail.append(tail)
 
         # Refresh static margin calculation
         self.evaluateStaticMargin()
@@ -522,6 +526,7 @@ def addNose(self, length, kind, position, name="Nose Cone"):
 
         # Add nose to the list of aerodynamic surfaces
         self.aerodynamicSurfaces.append(nose)
+        self.nosecone.append(nose)
 
         # Refresh static margin calculation
         self.evaluateStaticMargin()
@@ -634,6 +639,7 @@ def addTrapezoidalFins(
 
         # Add fin set to the list of aerodynamic surfaces
         self.aerodynamicSurfaces.append(finSet)
+        self.fins.append(finSet)
 
         # Refresh static margin calculation
         self.evaluateStaticMargin()
@@ -703,10 +709,13 @@ def addEllipticalFins(
         radius = radius if radius is not None else self.radius
 
         # Create a fin set as an object of EllipticalFins class
-        finSet = EllipticalFins(n, rootChord, span, position, radius, cantAngle, airfoil, name)
+        finSet = EllipticalFins(
+            n, rootChord, span, position, radius, cantAngle, airfoil, name
+        )
 
         # Add fin set to the list of aerodynamic surfaces
         self.aerodynamicSurfaces.append(finSet)
+        self.fins.append(finSet)
 
         # Refresh static margin calculation
         self.evaluateStaticMargin()