Correction of SolidMotor

Clean comments and cleared code

Author: ayoubdsp

rocketpy/motors/solid_motor.py

@@ -7,7 +7,7 @@
 from ..plots.solid_motor_plots import _SolidMotorPlots
 from ..prints.solid_motor_prints import _SolidMotorPrints
 from .motor import Motor
-from os import path
+
 
 class SolidMotor(Motor):
     """Class to specify characteristics and useful operations for solid motors.
@@ -195,7 +195,6 @@ class SolidMotor(Motor):
         It will allow to obtain the net thrust in the Flight class.
     """
 
-    
     def __init__(
         self,
         thrust_source,
@@ -321,20 +320,22 @@ class Function. Thrust units are Newtons.
         """
         self.rse_motor_data = None
         self.description_eng_file = None
-        
+
         if isinstance(thrust_source, str):
             if thrust_source.endswith(".eng"):
-               
-                comments, description, thrust_source_data = Motor.import_eng(thrust_source)
+
+                comments, description, thrust_source_data = Motor.import_eng(
+                    thrust_source
+                )
                 self.description_eng_file = description
                 self.comments_eng_file = comments
-                thrust_source = thrust_source_data 
+                thrust_source = thrust_source_data
             elif thrust_source.endswith(".rse"):
-                
+
                 rse_data, thrust_source_data = Motor.import_rse(thrust_source)
                 self.rse_motor_data = rse_data
-                thrust_source = thrust_source_data 
-      
+                thrust_source = thrust_source_data
+
         super().__init__(
             thrust_source=thrust_source,
             dry_inertia=dry_inertia,
@@ -348,12 +349,10 @@ class Function. Thrust units are Newtons.
             coordinate_system_orientation=coordinate_system_orientation,
             reference_pressure=reference_pressure,
         )
-        
-       
+
         self.throat_radius = throat_radius
         self.throat_area = np.pi * throat_radius**2
 
-        
         self.grains_center_of_mass_position = grains_center_of_mass_position
         self.grain_number = grain_number
         self.grain_separation = grain_separation
@@ -362,7 +361,6 @@ class Function. Thrust units are Newtons.
         self.grain_initial_inner_radius = grain_initial_inner_radius
         self.grain_initial_height = grain_initial_height
 
-       
         self.grain_initial_volume = (
             self.grain_initial_height
             * np.pi
@@ -372,7 +370,6 @@ class Function. Thrust units are Newtons.
 
         self.evaluate_geometry()
 
-        
         self.prints = _SolidMotorPrints(self)
         self.plots = _SolidMotorPlots(self)
         self.propellant_I_11_from_propellant_CM = self.propellant_I_11
@@ -393,45 +390,44 @@ class Function. Thrust units are Newtons.
 
         propellant_com_func = self.center_of_propellant_mass
 
-      
         propellant_com_vector_func = Function(
             lambda t: Vector([0, 0, propellant_com_func(t)]),
-            inputs="t", outputs="Vector (m)"
+            inputs="t",
+            outputs="Vector (m)",
         )
 
         # Utiliser les nouvelles fonctions PAT
         self.propellant_I_11 = parallel_axis_theorem_I11(
             self.propellant_I_11_from_propellant_CM,
             self.propellant_mass,
-            propellant_com_vector_func
+            propellant_com_vector_func,
         )
         self.propellant_I_22 = parallel_axis_theorem_I22(
             self.propellant_I_22_from_propellant_CM,
             self.propellant_mass,
-            propellant_com_vector_func
+            propellant_com_vector_func,
         )
         self.propellant_I_33 = parallel_axis_theorem_I33(
             self.propellant_I_33_from_propellant_CM,
             self.propellant_mass,
-            propellant_com_vector_func
+            propellant_com_vector_func,
         )
         self.propellant_I_12 = parallel_axis_theorem_I12(
-            self.propellant_I_12_from_propellant_CM, 
+            self.propellant_I_12_from_propellant_CM,
             self.propellant_mass,
-            propellant_com_vector_func
+            propellant_com_vector_func,
         )
         self.propellant_I_13 = parallel_axis_theorem_I13(
-            self.propellant_I_13_from_propellant_CM, 
+            self.propellant_I_13_from_propellant_CM,
             self.propellant_mass,
-            propellant_com_vector_func
+            propellant_com_vector_func,
         )
         self.propellant_I_23 = parallel_axis_theorem_I23(
             self.propellant_I_23_from_propellant_CM,
             self.propellant_mass,
-            propellant_com_vector_func
+            propellant_com_vector_func,
         )
 
-    
         self.I_11 = Function(lambda t: self.dry_I_11) + self.propellant_I_11
         self.I_22 = Function(lambda t: self.dry_I_22) + self.propellant_I_22
         self.I_33 = Function(lambda t: self.dry_I_33) + self.propellant_I_33