MNT: fixes pylint code after Stano's review

Author: Gui-FernandesBR

.pylintrc

@@ -227,6 +227,8 @@ good-names=FlightPhases,
            M3_damping,
            CM_to_CDM,
            CM_to_CPM,
+           center_of_mass_without_motor_to_CDM,
+           motor_center_of_dry_mass_to_CDM,
 
 # Good variable names regexes, separated by a comma. If names match any regex,
 # they will always be accepted

rocketpy/rocket/aero_surface.py

@@ -901,7 +901,7 @@ def lift_source(mach):
         # Lift coefficient derivative for n fins corrected with Fin-Body interference
         self.clalpha_multiple_fins = (
             self.lift_interference_factor
-            * self.__fin_num_correction(self.n)
+            * self.fin_num_correction(self.n)
             * self.clalpha_single_fin
         )  # Function of mach number
         self.clalpha_multiple_fins.set_inputs("Mach")
@@ -957,7 +957,7 @@ def evaluate_roll_parameters(self):
         return self.roll_parameters
 
     @staticmethod
-    def __fin_num_correction(n):
+    def fin_num_correction(n):
         """Calculates a correction factor for the lift coefficient of multiple
         fins.
         The specifics  values are documented at:
@@ -975,7 +975,7 @@ def __fin_num_correction(n):
             Factor that accounts for the number of fins.
         """
         corrector_factor = [2.37, 2.74, 2.99, 3.24]
-        if n >= 5 and n <= 8:  # pylint: disable=chained-comparison
+        if 5 <= n <= 8:
             return corrector_factor[n - 5]
         else:
             return n / 2

rocketpy/rocket/rocket.py

@@ -644,25 +644,25 @@ def evaluate_dry_inertias(self):
         motor_dry_mass = self.motor.dry_mass
         mass = self.mass
 
-        # Compute axes distances
-        noMCM_to_CDM = (  # pylint: disable=invalid-name
+        # Compute axes distances (CDM: Center of Dry Mass)
+        center_of_mass_without_motor_to_CDM = (
             self.center_of_mass_without_motor - self.center_of_dry_mass_position
         )
-        motorCDM_to_CDM = (  # pylint: disable=invalid-name
+        motor_center_of_dry_mass_to_CDM = (
             self.motor_center_of_dry_mass_position - self.center_of_dry_mass_position
         )
 
         # Compute dry inertias
         self.dry_I_11 = parallel_axis_theorem_from_com(
-            self.I_11_without_motor, mass, noMCM_to_CDM
+            self.I_11_without_motor, mass, center_of_mass_without_motor_to_CDM
         ) + parallel_axis_theorem_from_com(
-            self.motor.dry_I_11, motor_dry_mass, motorCDM_to_CDM
+            self.motor.dry_I_11, motor_dry_mass, motor_center_of_dry_mass_to_CDM
         )
 
         self.dry_I_22 = parallel_axis_theorem_from_com(
-            self.I_22_without_motor, mass, noMCM_to_CDM
+            self.I_22_without_motor, mass, center_of_mass_without_motor_to_CDM
         ) + parallel_axis_theorem_from_com(
-            self.motor.dry_I_22, motor_dry_mass, motorCDM_to_CDM
+            self.motor.dry_I_22, motor_dry_mass, motor_center_of_dry_mass_to_CDM
         )
 
         self.dry_I_33 = self.I_33_without_motor + self.motor.dry_I_33

rocketpy/simulation/flight.py

@@ -1716,7 +1716,7 @@ def u_dot_generalized(
                 else:
                     R3 += air_brakes_force
         # Get rocket velocity in body frame
-        velocity_vector_in_body_frame = Kt @ v
+        velocity_in_body_frame = Kt @ v
         # Calculate lift and moment for each component of the rocket
         for aero_surface, position in self.rocket.aerodynamic_surfaces:
             comp_cpz = (
@@ -1726,7 +1726,7 @@ def u_dot_generalized(
             surface_radius = aero_surface.rocket_radius
             reference_area = np.pi * surface_radius**2
             # Component absolute velocity in body frame
-            comp_vb = velocity_vector_in_body_frame + (w ^ comp_cp)
+            comp_vb = velocity_in_body_frame + (w ^ comp_cp)
             # Wind velocity at component altitude
             comp_z = z + (K @ comp_cp).z
             comp_wind_vx = self.env.wind_velocity_x.get_value_opt(comp_z)
@@ -1797,7 +1797,7 @@ def u_dot_generalized(
         )
         M3 += self.rocket.cp_eccentricity_x * R2 - self.rocket.cp_eccentricity_y * R1
 
-        weight_vector_in_body_frame = Kt @ Vector(
+        weight_in_body_frame = Kt @ Vector(
             [0, 0, -total_mass * self.env.gravity.get_value_opt(z)]
         )
 
@@ -1815,14 +1815,14 @@ def u_dot_generalized(
             ((w ^ T00) ^ w)
             + (w ^ T03)
             + T04
-            + weight_vector_in_body_frame
+            + weight_in_body_frame
             + Vector([R1, R2, R3])
         )
 
         T21 = (
             ((I @ w) ^ w)
             + T05 @ w
-            - (weight_vector_in_body_frame ^ r_CM)
+            - (weight_in_body_frame ^ r_CM)
             + Vector([M1, M2, M3])
         )
 
@@ -3434,8 +3434,6 @@ class TimeNodes:
         TimeNodes object are instances of the TimeNode class.
         """
 
-        # pylint: disable=missing-function-docstring
-
         def __init__(self, init_list=None):
             if not init_list:
                 init_list = []

rocketpy/tools.py

@@ -820,7 +820,6 @@ def check_requirement_version(module_name, version):
 
 
 def exponential_backoff(max_attempts, base_delay=1, max_delay=60):
-    # pylint: disable=missing-function-docstring
     def decorator(func):
         @functools.wraps(func)
         def wrapper(*args, **kwargs):