ENH: modifications in the Flight class

Author: kevin-alcaniz

rocketpy/simulation/flight.py

@@ -1740,10 +1740,10 @@ def u_dot_generalized(self, t, u, post_processing=False):  # pylint: disable=too
             e0_dot, e1_dot, e2_dot, e3_dot, alpha1, alpha2, alpha3].
         """
         # Retrieve integration data
-        x, y, z, vx, vy, vz, e0, e1, e2, e3, omega1, omega2, omega3 = u
+        _, _, z, vx, vy, vz, e0, e1, e2, e3, omega1, omega2, omega3 = u
 
         # Create necessary vectors
-        r = Vector([x, y, z])  # CDM position vector
+        # r = Vector([x, y, z])  # CDM position vector
         v = Vector([vx, vy, vz])  # CDM velocity vector
         e = [e0, e1, e2, e3]  # Euler parameters/quaternions
         w = Vector([omega1, omega2, omega3])  # Angular velocity vector
@@ -1896,11 +1896,9 @@ def u_dot_generalized(self, t, u, post_processing=False):  # pylint: disable=too
         # Angular velocity derivative
         w_dot = I_CM.inverse @ (T21 + (T20 ^ r_CM))
 
-        # Velocity vector derivative + Inertial forces
+        # Velocity vector derivative + Coriolis acceleration
         wE = Kt @ Vector(self.env.earth_rotation_vector)
-        v_dot = K @ (T20 / total_mass - (r_CM ^ w_dot)) - (
-            2*(wE ^ v) + wE ^ (wE ^ r)
-        )
+        v_dot = K @ (T20 / total_mass - (r_CM ^ w_dot)) - 2*(wE ^ v)
 
         # Euler parameters derivative
         e_dot = [