Merge pull request OpenMDAO#507 from Kenneth-T-Moore/paramport_refactor2

Paramport Part 2 - removal of most variables from 2DOF (gasp-based) paramport.
xjjiang · Sep 9, 2024 · 4134100 · 4134100
2 parents e543c9d + e8cd8b3
commit 4134100
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Showing 22 changed files with 299 additions and 111 deletions.
diff --git a/aviary/interface/methods_for_level2.py b/aviary/interface/methods_for_level2.py
@@ -1090,8 +1090,15 @@ def add_subsystem_timeseries_outputs(phase, phase_name):
                         phase_name, self._get_phase(phase_name, phase_idx))
                     add_subsystem_timeseries_outputs(phase, phase_name)
 
-                    if phase_name == 'ascent' and self.mission_method is TWO_DEGREES_OF_FREEDOM:
-                        self._add_groundroll_eq_constraint(phase)
+                    if self.mission_method is TWO_DEGREES_OF_FREEDOM:
+
+                        # In GASP, we still use the phase name to infer the phase type.
+                        # We need this information to be available in the builders.
+                        # TODO - Ultimately we should overhaul all of this.
+                        self.phase_info[phase_name]['phase_type'] = phase_name
+
+                        if phase_name == 'ascent':
+                            self._add_groundroll_eq_constraint(phase)
 
             # loop through phase_info and external subsystems
             external_parameters = {}
@@ -1107,9 +1114,8 @@ def add_subsystem_timeseries_outputs(phase, phase_name):
                     for parameter in parameter_dict:
                         external_parameters[phase_name][parameter] = parameter_dict[parameter]
 
-            if self.mission_method in (HEIGHT_ENERGY, SOLVED_2DOF):
-                traj = setup_trajectory_params(
-                    self.model, traj, self.aviary_inputs, phases, meta_data=self.meta_data, external_parameters=external_parameters)
+            traj = setup_trajectory_params(
+                self.model, traj, self.aviary_inputs, phases, meta_data=self.meta_data, external_parameters=external_parameters)
 
         self.traj = traj
 

diff --git a/aviary/mission/gasp_based/ode/climb_ode.py b/aviary/mission/gasp_based/ode/climb_ode.py
@@ -215,3 +215,6 @@ def setup(self):
                                 val=174000 * np.ones(nn), units='lbm')
         self.set_input_defaults(Dynamic.Mission.MACH,
                                 val=0 * np.ones(nn), units="unitless")
+
+        from aviary.variable_info.variables import Aircraft
+        self.set_input_defaults(Aircraft.Wing.AREA, val=1.0, units="ft**2")
diff --git a/aviary/mission/gasp_based/ode/descent_ode.py b/aviary/mission/gasp_based/ode/descent_ode.py
@@ -11,7 +11,7 @@
 from aviary.mission.gasp_based.ode.constraints.speed_constraints import SpeedConstraints
 
 from aviary.variable_info.enums import AnalysisScheme, AlphaModes, SpeedType
-from aviary.variable_info.variables import Mission, Dynamic
+from aviary.variable_info.variables import Aircraft, Mission, Dynamic
 from aviary.subsystems.aerodynamics.aerodynamics_builder import AerodynamicsBuilderBase
 from aviary.subsystems.propulsion.propulsion_builder import PropulsionBuilderBase
 from aviary.mission.gasp_based.ode.time_integration_base_classes import add_SGM_required_inputs
@@ -232,3 +232,5 @@ def setup(self):
                                 val=0 * np.ones(nn), units="unitless")
         self.set_input_defaults(Dynamic.Mission.THROTTLE,
                                 val=0 * np.ones(nn), units="unitless")
+
+        self.set_input_defaults(Aircraft.Wing.AREA, val=1.0, units="ft**2")
diff --git a/aviary/mission/gasp_based/ode/groundroll_ode.py b/aviary/mission/gasp_based/ode/groundroll_ode.py
@@ -136,3 +136,5 @@ def setup(self):
         self.set_input_defaults(Dynamic.Mission.VELOCITY, val=np.zeros(nn), units="kn")
         self.set_input_defaults(Dynamic.Mission.VELOCITY_RATE,
                                 val=np.zeros(nn), units="kn/s")
+
+        self.set_input_defaults(Aircraft.Wing.INCIDENCE, val=1.0, units="deg")
diff --git a/aviary/mission/gasp_based/ode/params.py b/aviary/mission/gasp_based/ode/params.py
@@ -6,75 +6,9 @@
 class ParamPort(om.ExplicitComponent):
 
     param_data = {
-        Aircraft.Wing.AREA: dict(units="ft**2", val=1370.3),
         Aircraft.Wing.INCIDENCE: dict(units="deg", val=0),
-        Aircraft.Wing.HEIGHT: dict(units="ft", val=8),
-        Aircraft.Wing.SPAN: dict(units="ft", val=117.8),
-        Mission.Design.GROSS_MASS: dict(units="lbm", val=175400),
-        Mission.Summary.GROSS_MASS: dict(units="lbm", val=175400),
-        Mission.Summary.FUEL_FLOW_SCALER: dict(units="unitless", val=1.0),
-        Mission.Takeoff.AIRPORT_ALTITUDE: dict(units="ft", val=0),
-        Mission.Landing.AIRPORT_ALTITUDE: dict(units="ft", val=0),
         Aircraft.Wing.FLAP_DEFLECTION_TAKEOFF: dict(units="deg", val=10),
         Aircraft.Wing.FLAP_DEFLECTION_LANDING: dict(units="deg", val=40),
-        Aircraft.Wing.AVERAGE_CHORD: dict(units="ft", val=12.615),
-        Aircraft.Fuselage.AVG_DIAMETER: dict(units="inch", val=12 * 13.100),
-        Aircraft.HorizontalTail.AVERAGE_CHORD: dict(units="ft", val=9.577),
-        Aircraft.HorizontalTail.AREA: dict(units="ft**2", val=375.880),
-        Aircraft.HorizontalTail.SPAN: dict(units="ft", val=42.254),
-        Aircraft.VerticalTail.AVERAGE_CHORD: dict(units="ft", val=16.832),
-        Aircraft.VerticalTail.AREA: dict(units="ft**2", val=469.318),
-        Aircraft.VerticalTail.SPAN: dict(units="ft", val=27.996),
-        Aircraft.Fuselage.LENGTH: dict(units="ft", val=129.4),
-        Aircraft.Nacelle.AVG_LENGTH: dict(units="ft", val=14.5),
-        Aircraft.Fuselage.WETTED_AREA: dict(units="ft**2", val=4000),
-        Aircraft.Nacelle.SURFACE_AREA: dict(units="ft**2", val=659.23 / 2),
-        Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED: dict(units="unitless", val=0.1397),
-        Aircraft.Strut.CHORD: dict(
-            units="ft", val=0
-        ),  # only available if Aviary_option Aircraft.Wing.HAS_STRUT
-        Aircraft.Wing.ASPECT_RATIO: dict(units="unitless", val=10.13),
-        Aircraft.Wing.TAPER_RATIO: dict(units="unitless", val=0.33),
-        Aircraft.Wing.THICKNESS_TO_CHORD_ROOT: dict(units="unitless", val=0.15),
-        Aircraft.Wing.THICKNESS_TO_CHORD_TIP: dict(units="unitless", val=0.12),
-        Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION: dict(units="unitless", val=0),
-        Aircraft.Wing.SWEEP: dict(units="deg", val=25),
-        Aircraft.HorizontalTail.SWEEP: dict(units="deg", val=25),
-        Aircraft.HorizontalTail.MOMENT_RATIO: dict(units="unitless", val=0.2307),
-        Aircraft.Wing.MOUNTING_TYPE: dict(units="unitless", val=0),
-        Aircraft.Design.STATIC_MARGIN: dict(units="unitless", val=0.03),
-        Aircraft.Design.CG_DELTA: dict(units="unitless", val=0.25),
-        Aircraft.Wing.FORM_FACTOR: dict(units="unitless", val=1.25),
-        Aircraft.Fuselage.FORM_FACTOR: dict(units="unitless", val=1.25),
-        Aircraft.Nacelle.FORM_FACTOR: dict(units="unitless", val=1.5),
-        Aircraft.VerticalTail.FORM_FACTOR: dict(units="unitless", val=1.25),
-        Aircraft.HorizontalTail.FORM_FACTOR: dict(units="unitless", val=1.25),
-        Aircraft.Wing.FUSELAGE_INTERFERENCE_FACTOR: dict(units="unitless", val=1.1),
-        Aircraft.Strut.FUSELAGE_INTERFERENCE_FACTOR: dict(units="unitless", val=0),
-        Aircraft.Design.DRAG_COEFFICIENT_INCREMENT: dict(units="unitless", val=0.00175),
-        Aircraft.Fuselage.FLAT_PLATE_AREA_INCREMENT: dict(units="ft**2", val=0.25),
-        Aircraft.Wing.CENTER_DISTANCE: dict(units="unitless", val=0.463),
-        Aircraft.Wing.MIN_PRESSURE_LOCATION: dict(units="unitless", val=0.3),
-        Aircraft.Wing.MAX_THICKNESS_LOCATION: dict(units="unitless", val=0.4),
-        Aircraft.Strut.AREA_RATIO: dict(units="unitless", val=0),
-        Aircraft.Wing.ZERO_LIFT_ANGLE: dict(units="deg", val=-1.2),
-        Aircraft.Design.SUPERCRITICAL_DIVERGENCE_SHIFT: dict(units="unitless", val=0.033),
-        Aircraft.Wing.FLAP_CHORD_RATIO: dict(units="unitless", val=0.3),
-        Mission.Design.LIFT_COEFFICIENT_MAX_FLAPS_UP: dict(units="unitless", val=1.2596),
-        Mission.Takeoff.LIFT_COEFFICIENT_MAX: dict(units="unitless", val=2.1886),
-        Mission.Landing.LIFT_COEFFICIENT_MAX: dict(units="unitless", val=2.8155),
-        Mission.Takeoff.LIFT_COEFFICIENT_FLAP_INCREMENT: dict(
-            units="unitless", val=0.4182
-        ),
-        Mission.Landing.LIFT_COEFFICIENT_FLAP_INCREMENT: dict(
-            units="unitless", val=1.0293
-        ),
-        Mission.Takeoff.DRAG_COEFFICIENT_FLAP_INCREMENT: dict(
-            units="unitless", val=0.0085
-        ),
-        Mission.Landing.DRAG_COEFFICIENT_FLAP_INCREMENT: dict(
-            units="unitless", val=0.0406
-        ),
     }
 
     def setup(self):
@@ -149,3 +83,98 @@ def promote_params(sys, trajs=None, phases=None):
                         static_target=True,
                     )
                 sys.promotes(phasename, inputs=proms)
+
+
+params_for_unit_tests = {
+    Aircraft.Wing.AREA: dict(units="ft**2", val=1370.3),
+    Aircraft.Wing.HEIGHT: dict(units="ft", val=8),
+    Aircraft.Wing.SPAN: dict(units="ft", val=117.8),
+    Mission.Design.GROSS_MASS: dict(units="lbm", val=175400),
+    Mission.Summary.GROSS_MASS: dict(units="lbm", val=175400),
+    Mission.Summary.FUEL_FLOW_SCALER: dict(units="unitless", val=1.0),
+    Mission.Takeoff.AIRPORT_ALTITUDE: dict(units="ft", val=0),
+    Mission.Landing.AIRPORT_ALTITUDE: dict(units="ft", val=0),
+    Aircraft.Wing.AVERAGE_CHORD: dict(units="ft", val=12.615),
+    Aircraft.Fuselage.AVG_DIAMETER: dict(units="inch", val=12 * 13.100),
+    Aircraft.HorizontalTail.AVERAGE_CHORD: dict(units="ft", val=9.577),
+    Aircraft.HorizontalTail.AREA: dict(units="ft**2", val=375.880),
+    Aircraft.HorizontalTail.SPAN: dict(units="ft", val=42.254),
+    Aircraft.VerticalTail.AVERAGE_CHORD: dict(units="ft", val=16.832),
+    Aircraft.VerticalTail.AREA: dict(units="ft**2", val=469.318),
+    Aircraft.VerticalTail.SPAN: dict(units="ft", val=27.996),
+    Aircraft.Fuselage.LENGTH: dict(units="ft", val=129.4),
+    Aircraft.Nacelle.AVG_LENGTH: dict(units="ft", val=14.5),
+    Aircraft.Fuselage.WETTED_AREA: dict(units="ft**2", val=4000),
+    Aircraft.Nacelle.SURFACE_AREA: dict(units="ft**2", val=659.23 / 2),
+    Aircraft.Wing.THICKNESS_TO_CHORD_UNWEIGHTED: dict(units="unitless", val=0.1397),
+    Aircraft.Strut.CHORD: dict(
+        units="ft", val=0
+    ),  # only available if Aviary_option Aircraft.Wing.HAS_STRUT
+    Aircraft.Wing.ASPECT_RATIO: dict(units="unitless", val=10.13),
+    Aircraft.Wing.TAPER_RATIO: dict(units="unitless", val=0.33),
+    Aircraft.Wing.THICKNESS_TO_CHORD_ROOT: dict(units="unitless", val=0.15),
+    Aircraft.Wing.THICKNESS_TO_CHORD_TIP: dict(units="unitless", val=0.12),
+    Aircraft.HorizontalTail.VERTICAL_TAIL_FRACTION: dict(units="unitless", val=0),
+    Aircraft.Wing.SWEEP: dict(units="deg", val=25),
+    Aircraft.HorizontalTail.SWEEP: dict(units="deg", val=25),
+    Aircraft.HorizontalTail.MOMENT_RATIO: dict(units="unitless", val=0.2307),
+    Aircraft.Wing.MOUNTING_TYPE: dict(units="unitless", val=0),
+    Aircraft.Design.STATIC_MARGIN: dict(units="unitless", val=0.03),
+    Aircraft.Design.CG_DELTA: dict(units="unitless", val=0.25),
+    Aircraft.Wing.FORM_FACTOR: dict(units="unitless", val=1.25),
+    Aircraft.Fuselage.FORM_FACTOR: dict(units="unitless", val=1.25),
+    Aircraft.Nacelle.FORM_FACTOR: dict(units="unitless", val=1.5),
+    Aircraft.VerticalTail.FORM_FACTOR: dict(units="unitless", val=1.25),
+    Aircraft.HorizontalTail.FORM_FACTOR: dict(units="unitless", val=1.25),
+    Aircraft.Wing.FUSELAGE_INTERFERENCE_FACTOR: dict(units="unitless", val=1.1),
+    Aircraft.Strut.FUSELAGE_INTERFERENCE_FACTOR: dict(units="unitless", val=0),
+    Aircraft.Design.DRAG_COEFFICIENT_INCREMENT: dict(units="unitless", val=0.00175),
+    Aircraft.Fuselage.FLAT_PLATE_AREA_INCREMENT: dict(units="ft**2", val=0.25),
+    Aircraft.Wing.CENTER_DISTANCE: dict(units="unitless", val=0.463),
+    Aircraft.Wing.MIN_PRESSURE_LOCATION: dict(units="unitless", val=0.3),
+    Aircraft.Wing.MAX_THICKNESS_LOCATION: dict(units="unitless", val=0.4),
+    Aircraft.Strut.AREA_RATIO: dict(units="unitless", val=0),
+    Aircraft.Wing.ZERO_LIFT_ANGLE: dict(units="deg", val=-1.2),
+    Aircraft.Design.SUPERCRITICAL_DIVERGENCE_SHIFT: dict(units="unitless", val=0.033),
+    Aircraft.Wing.FLAP_CHORD_RATIO: dict(units="unitless", val=0.3),
+    Mission.Design.LIFT_COEFFICIENT_MAX_FLAPS_UP: dict(units="unitless", val=1.2596),
+    Mission.Takeoff.LIFT_COEFFICIENT_MAX: dict(units="unitless", val=2.1886),
+    Mission.Landing.LIFT_COEFFICIENT_MAX: dict(units="unitless", val=2.8155),
+    Mission.Takeoff.LIFT_COEFFICIENT_FLAP_INCREMENT: dict(
+        units="unitless", val=0.4182
+    ),
+    Mission.Landing.LIFT_COEFFICIENT_FLAP_INCREMENT: dict(
+        units="unitless", val=1.0293
+    ),
+    Mission.Takeoff.DRAG_COEFFICIENT_FLAP_INCREMENT: dict(
+        units="unitless", val=0.0085
+    ),
+    Mission.Landing.DRAG_COEFFICIENT_FLAP_INCREMENT: dict(
+        units="unitless", val=0.0406
+    ),
+}
+
+
+def set_params_for_unit_tests(prob):
+    """
+    Helper function to set parameters for several ode tests with the 2DOF method.
+
+    This is needed because the Paramport used to contain default values for some
+    variables.
+
+    Parameters
+    ----------
+    prob : Problem
+        OpenMDAO problem that has been setup.
+
+    Returns
+    -------
+    Problem
+    """
+    for key, val in params_for_unit_tests.items():
+        try:
+            prob.set_val(key, val['val'], units=val['units'])
+        except:
+            pass
+
+    return prob
diff --git a/aviary/mission/gasp_based/ode/test/test_accel_ode.py b/aviary/mission/gasp_based/ode/test/test_accel_ode.py
@@ -4,11 +4,12 @@
 from openmdao.utils.assert_utils import assert_check_partials
 
 from aviary.mission.gasp_based.ode.accel_ode import AccelODE
-from aviary.variable_info.options import get_option_defaults
-from aviary.utils.test_utils.IO_test_util import check_prob_outputs
-from aviary.variable_info.variables import Dynamic
+from aviary.mission.gasp_based.ode.params import set_params_for_unit_tests
 from aviary.subsystems.propulsion.utils import build_engine_deck
 from aviary.utils.test_utils.default_subsystems import get_default_mission_subsystems
+from aviary.utils.test_utils.IO_test_util import check_prob_outputs
+from aviary.variable_info.options import get_option_defaults
+from aviary.variable_info.variables import Dynamic
 
 
 class AccelerationODETestCase(unittest.TestCase):
@@ -35,6 +36,8 @@ def test_accel(self):
         self.prob.set_val(Dynamic.Mission.VELOCITY, [185, 252], units="kn")
         self.prob.set_val(Dynamic.Mission.MASS, [174974, 174878], units="lbm")
 
+        set_params_for_unit_tests(self.prob)
+
         self.prob.run_model()
         testvals = {
             Dynamic.Mission.LIFT: [174974, 174878],

diff --git a/aviary/mission/gasp_based/ode/test/test_ascent_ode.py b/aviary/mission/gasp_based/ode/test/test_ascent_ode.py
@@ -5,6 +5,7 @@
 from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal
 
 from aviary.mission.gasp_based.ode.ascent_ode import AscentODE
+from aviary.mission.gasp_based.ode.params import set_params_for_unit_tests
 from aviary.subsystems.propulsion.utils import build_engine_deck
 from aviary.utils.test_utils.default_subsystems import get_default_mission_subsystems
 from aviary.variable_info.options import get_option_defaults
@@ -30,6 +31,8 @@ def test_ascent_partials(self):
         self.prob.set_val(Dynamic.Mission.VELOCITY, [100, 100], units="kn")
         self.prob.set_val("t_curr", [1, 2], units="s")
 
+        set_params_for_unit_tests(self.prob)
+
         self.prob.run_model()
 
         tol = tol = 1e-6

diff --git a/aviary/mission/gasp_based/ode/test/test_breguet_cruise_ode.py b/aviary/mission/gasp_based/ode/test/test_breguet_cruise_ode.py
@@ -5,6 +5,7 @@
 from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal
 
 from aviary.mission.gasp_based.ode.breguet_cruise_ode import BreguetCruiseODESolution
+from aviary.mission.gasp_based.ode.params import set_params_for_unit_tests
 from aviary.subsystems.propulsion.utils import build_engine_deck
 from aviary.utils.test_utils.default_subsystems import get_default_mission_subsystems
 from aviary.variable_info.options import get_option_defaults
@@ -34,6 +35,8 @@ def test_cruise(self):
 
         self.prob.set_val(Dynamic.Mission.MACH, [0.7, 0.7], units="unitless")
 
+        set_params_for_unit_tests(self.prob)
+
         self.prob.run_model()
 
         tol = tol = 1e-6

diff --git a/aviary/mission/gasp_based/ode/test/test_climb_ode.py b/aviary/mission/gasp_based/ode/test/test_climb_ode.py
@@ -5,11 +5,12 @@
 from openmdao.utils.assert_utils import assert_check_partials
 
 from aviary.mission.gasp_based.ode.climb_ode import ClimbODE
+from aviary.mission.gasp_based.ode.params import set_params_for_unit_tests
+from aviary.subsystems.propulsion.utils import build_engine_deck
 from aviary.utils.test_utils.IO_test_util import check_prob_outputs
+from aviary.utils.test_utils.default_subsystems import get_default_mission_subsystems
 from aviary.variable_info.options import get_option_defaults
 from aviary.variable_info.variables import Aircraft, Dynamic
-from aviary.subsystems.propulsion.utils import build_engine_deck
-from aviary.utils.test_utils.default_subsystems import get_default_mission_subsystems
 
 
 class ClimbODETestCase(unittest.TestCase):
@@ -43,6 +44,8 @@ def test_start_of_climb(self):
         # slightly greater than zero to help check partials
         self.prob.set_val(Aircraft.Wing.INCIDENCE, 0.0000001, units="deg")
 
+        set_params_for_unit_tests(self.prob)
+
         self.prob.run_model()
 
         testvals = {
@@ -79,6 +82,8 @@ def test_end_of_climb(self):
         self.prob.set_val(Dynamic.Mission.MASS, np.array([174149, 171592]), units="lbm")
         self.prob.set_val("EAS", np.array([270, 270]), units="kn")
 
+        set_params_for_unit_tests(self.prob)
+
         self.prob.run_model()
 
         testvals = {

diff --git a/aviary/mission/gasp_based/ode/test/test_descent_ode.py b/aviary/mission/gasp_based/ode/test/test_descent_ode.py
@@ -7,12 +7,13 @@
 from packaging import version
 
 from aviary.mission.gasp_based.ode.descent_ode import DescentODE
-from aviary.variable_info.options import get_option_defaults
+from aviary.mission.gasp_based.ode.params import set_params_for_unit_tests
+from aviary.subsystems.propulsion.utils import build_engine_deck
+from aviary.utils.test_utils.default_subsystems import get_default_mission_subsystems
 from aviary.utils.test_utils.IO_test_util import check_prob_outputs
 from aviary.variable_info.enums import SpeedType
+from aviary.variable_info.options import get_option_defaults
 from aviary.variable_info.variables import Dynamic
-from aviary.subsystems.propulsion.utils import build_engine_deck
-from aviary.utils.test_utils.default_subsystems import get_default_mission_subsystems
 
 
 class DescentODETestCase(unittest.TestCase):
@@ -43,6 +44,8 @@ def test_high_alt(self):
         self.prob.set_val(Dynamic.Mission.ALTITUDE, np.array([36500, 14500]), units="ft")
         self.prob.set_val(Dynamic.Mission.MASS, np.array([147661, 147572]), units="lbm")
 
+        set_params_for_unit_tests(self.prob)
+
         self.prob.run_model()
 
         testvals = {
@@ -79,6 +82,8 @@ def test_low_alt(self):
         self.prob.set_val(Dynamic.Mission.MASS, 147410, units="lbm")
         self.prob.set_val("EAS", 250, units="kn")
 
+        set_params_for_unit_tests(self.prob)
+
         self.prob.run_model()
 
         testvals = {

diff --git a/aviary/mission/gasp_based/ode/test/test_flight_path_ode.py b/aviary/mission/gasp_based/ode/test/test_flight_path_ode.py
@@ -5,6 +5,7 @@
 from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal
 
 from aviary.mission.gasp_based.ode.flight_path_ode import FlightPathODE
+from aviary.mission.gasp_based.ode.params import set_params_for_unit_tests
 from aviary.variable_info.options import get_option_defaults
 from aviary.subsystems.propulsion.utils import build_engine_deck
 from aviary.utils.test_utils.default_subsystems import get_default_mission_subsystems
@@ -30,6 +31,8 @@ def test_case1(self):
         """
         self.prob.setup(check=False, force_alloc_complex=True)
 
+        set_params_for_unit_tests(self.prob)
+
         self.prob.set_val(Dynamic.Mission.VELOCITY, [100, 100], units="kn")
         self.prob.set_val(Dynamic.Mission.MASS, [100000, 100000], units="lbm")
         self.prob.set_val(Dynamic.Mission.ALTITUDE, [500, 500], units="ft")
@@ -66,6 +69,8 @@ def test_case2(self):
         self.fp.options["ground_roll"] = True
         self.prob.setup(check=False, force_alloc_complex=True)
 
+        set_params_for_unit_tests(self.prob)
+
         self.prob.set_val(Dynamic.Mission.VELOCITY, [100, 100], units="kn")
         self.prob.set_val(Dynamic.Mission.MASS, [100000, 100000], units="lbm")
         self.prob.set_val(Dynamic.Mission.ALTITUDE, [500, 500], units="ft")