STY: Apply ruff format to flight.py

Author: ViniciusCMB

rocketpy/simulation/flight.py

@@ -818,7 +818,8 @@ def __simulate(self, verbose):
                             lambda self, parachute_porosity=parachute.porosity: setattr(
                                 self, "parachute_porosity", parachute_porosity
                             ),
-                            lambda self, added_mass_coefficient=parachute.added_mass_coefficient: setattr(
+                            lambda self,
+                            added_mass_coefficient=parachute.added_mass_coefficient: setattr(
                                 self,
                                 "parachute_added_mass_coefficient",
                                 added_mass_coefficient,
@@ -1068,25 +1069,30 @@ def __simulate(self, verbose):
                                             i += 1
                                         # Create flight phase for time after inflation
                                         callbacks = [
-                                            lambda self, parachute_cd_s=parachute.cd_s: setattr(
+                                            lambda self,
+                                            parachute_cd_s=parachute.cd_s: setattr(
                                                 self, "parachute_cd_s", parachute_cd_s
                                             ),
-                                            lambda self, parachute_radius=parachute.radius: setattr(
+                                            lambda self,
+                                            parachute_radius=parachute.radius: setattr(
                                                 self,
                                                 "parachute_radius",
                                                 parachute_radius,
                                             ),
-                                            lambda self, parachute_height=parachute.height: setattr(
+                                            lambda self,
+                                            parachute_height=parachute.height: setattr(
                                                 self,
                                                 "parachute_height",
                                                 parachute_height,
                                             ),
-                                            lambda self, parachute_porosity=parachute.porosity: setattr(
+                                            lambda self,
+                                            parachute_porosity=parachute.porosity: setattr(
                                                 self,
                                                 "parachute_porosity",
                                                 parachute_porosity,
                                             ),
-                                            lambda self, added_mass_coefficient=parachute.added_mass_coefficient: setattr(
+                                            lambda self,
+                                            added_mass_coefficient=parachute.added_mass_coefficient: setattr(
                                                 self,
                                                 "parachute_added_mass_coefficient",
                                                 added_mass_coefficient,
@@ -1690,9 +1696,7 @@ def udot_rail2(self, t, u, post_processing=False):  # pragma: no cover
         # Hey! We will finish this function later, now we just can use u_dot
         return self.u_dot_generalized(t, u, post_processing=post_processing)
 
-    def u_dot(
-        self, t, u, post_processing=False
-    ):  # pylint: disable=too-many-locals,too-many-statements
+    def u_dot(self, t, u, post_processing=False):  # pylint: disable=too-many-locals,too-many-statements
         """Calculates derivative of u state vector with respect to time
         when rocket is flying in 6 DOF motion during ascent out of rail
         and descent without parachute.
@@ -2238,9 +2242,7 @@ def u_dot_generalized_3dof(self, t, u, post_processing=False):
 
         return u_dot
 
-    def u_dot_generalized(
-        self, t, u, post_processing=False
-    ):  # pylint: disable=too-many-locals,too-many-statements
+    def u_dot_generalized(self, t, u, post_processing=False):  # pylint: disable=too-many-locals,too-many-statements
         """Calculates derivative of u state vector with respect to time when the
         rocket is flying in 6 DOF motion in space and significant mass variation
         effects exist. Typical flight phases include powered ascent after launch
@@ -4075,7 +4077,9 @@ def add(self, flight_phase, index=None):  # TODO: quite complex method
             new_index = (
                 index - 1
                 if flight_phase.t < previous_phase.t
-                else index + 1 if flight_phase.t > next_phase.t else index
+                else index + 1
+                if flight_phase.t > next_phase.t
+                else index
             )
             flight_phase.t += adjust
             self.add(flight_phase, new_index)