FIX: Add missing u_dot parameter to direct triggerfunc calls

Direct calls to parachute.triggerfunc() were missing the u_dot parameter, causing TypeError in unit tests. Added u_dot=None to non-overshoot and overshoot trigger evaluation paths where u_dot is not computed. Fixes test failures in: - tests/unit/simulation/test_flight.py - tests/unit/test_utilities.py - tests/unit/test_rail_buttons_bending_moments.py - tests/unit/test_flight_data_exporter.py
RocketPy-Team · ViniciusCMB · Dec 4, 2025 · Dec 7, 2025 · Dec 8, 2025 · Dec 8, 2025
commit 6d79d62fabc7520d3fb14dd0f241b26ccc31d493
@@ -777,8 +777,7 @@ 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,
@@ -964,6 +963,7 @@ def __check_and_handle_parachute_triggers(
                 height_above_ground_level,
                 self.y_sol,
                 self.sensors,
+                None,  # u_dot not computed in non-overshoot path
             ):
                 continue  # Check next parachute
 
@@ -999,8 +999,7 @@ def __check_and_handle_parachute_triggers(
                 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,
@@ -1373,6 +1372,7 @@ def __check_overshootable_parachute_triggers(
                 height_above_ground_level,
                 overshootable_node.y_sol,
                 self.sensors,
+                None,  # u_dot not computed in overshoot path
             ):
                 continue  # Check next parachute
 
@@ -1405,8 +1405,7 @@ def __check_overshootable_parachute_triggers(
                 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,
@@ -1989,7 +1988,9 @@ 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.
@@ -2535,7 +2536,9 @@ 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
@@ -4370,9 +4373,7 @@ 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)