Update inconsistent naming for angle of attack

aviary/mission/flops_based/ode/landing_eom.py

@@ -57,7 +57,7 @@ def setup(self):
             Dynamic.Vehicle.LIFT,
             Dynamic.Vehicle.Propulsion.THRUST_TOTAL,
             Dynamic.Vehicle.DRAG,
-            'angle_of_attack',
+            Dynamic.Vehicle.ANGLE_OF_ATTACK,
             Dynamic.Mission.FLIGHT_PATH_ANGLE,
         ]
 
@@ -113,7 +113,7 @@ def setup(self):
             Dynamic.Vehicle.MASS,
             Dynamic.Vehicle.LIFT,
             Dynamic.Vehicle.DRAG,
-            'angle_of_attack',
+            Dynamic.Vehicle.ANGLE_OF_ATTACK,
             Dynamic.Mission.FLIGHT_PATH_ANGLE,
         ]
 
@@ -165,7 +165,7 @@ def setup(self):
         add_aviary_input(self, Dynamic.Vehicle.LIFT, val=np.ones(nn), units='N')
         add_aviary_input(self, Dynamic.Vehicle.DRAG, val=np.ones(nn), units='N')
 
-        self.add_input('angle_of_attack', val=np.zeros(nn), units='rad')
+        self.add_input(Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
 
         add_aviary_input(
             self, Dynamic.Mission.FLIGHT_PATH_ANGLE, val=np.zeros(nn), units='rad'
@@ -204,7 +204,7 @@ def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
 
         weight = mass * grav_metric
 
-        alpha = inputs['angle_of_attack']
+        alpha = inputs[Dynamic.Vehicle.ANGLE_OF_ATTACK]
         gamma = inputs[Dynamic.Mission.FLIGHT_PATH_ANGLE]
 
         # FLOPS measures glideslope below horizontal
@@ -242,7 +242,7 @@ def compute_partials(self, inputs, J, discrete_inputs=None):
 
         weight = mass * grav_metric
 
-        alpha = inputs['angle_of_attack']
+        alpha = inputs[Dynamic.Vehicle.ANGLE_OF_ATTACK]
         gamma = inputs[Dynamic.Mission.FLIGHT_PATH_ANGLE]
 
         # FLOPS measures glideslope below horizontal
@@ -284,8 +284,8 @@ def compute_partials(self, inputs, J, discrete_inputs=None):
         f_h = t_angle * (drag - weight * s_gamma) / c_angle
         f_v = -(weight * c_gamma - lift) / (s_angle * t_angle)
 
-        J[forces_key, 'angle_of_attack'] = f_h - f_v
-        J[thrust_key, 'angle_of_attack'] = (f_h + f_v) / (2.)
+        J[forces_key, Dynamic.Vehicle.ANGLE_OF_ATTACK] = f_h - f_v
+        J[thrust_key, Dynamic.Vehicle.ANGLE_OF_ATTACK] = (f_h + f_v) / (2.)
 
         f_h = -weight * c_gamma / c_angle
         f_v = -weight * s_gamma / s_angle
@@ -320,7 +320,7 @@ def setup(self):
                          val=np.ones(nn), units='N')
         add_aviary_input(self, Dynamic.Vehicle.DRAG, val=np.ones(nn), units='N')
 
-        self.add_input('angle_of_attack', val=np.zeros(nn), units='rad')
+        self.add_input(Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
 
         add_aviary_input(
             self, Dynamic.Mission.FLIGHT_PATH_ANGLE, val=np.zeros(nn), units='rad'
@@ -351,7 +351,7 @@ def setup_partials(self):
             Dynamic.Vehicle.LIFT,
             Dynamic.Vehicle.Propulsion.THRUST_TOTAL,
             Dynamic.Vehicle.DRAG,
-            'angle_of_attack',
+            Dynamic.Vehicle.ANGLE_OF_ATTACK,
             Dynamic.Mission.FLIGHT_PATH_ANGLE,
         ]
 
@@ -370,7 +370,7 @@ def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
         thrust = inputs[Dynamic.Vehicle.Propulsion.THRUST_TOTAL]
         drag = inputs[Dynamic.Vehicle.DRAG]
 
-        alpha = inputs['angle_of_attack']
+        alpha = inputs[Dynamic.Vehicle.ANGLE_OF_ATTACK]
         gamma = inputs[Dynamic.Mission.FLIGHT_PATH_ANGLE]
 
         # FLOPS measures glideslope below horizontal
@@ -408,7 +408,7 @@ def compute_partials(self, inputs, J, discrete_inputs=None):
         thrust = inputs[Dynamic.Vehicle.Propulsion.THRUST_TOTAL]
         drag = inputs[Dynamic.Vehicle.DRAG]
 
-        alpha = inputs['angle_of_attack']
+        alpha = inputs[Dynamic.Vehicle.ANGLE_OF_ATTACK]
         gamma = inputs[Dynamic.Mission.FLIGHT_PATH_ANGLE]
 
         # FLOPS measures glideslope below horizontal
@@ -434,8 +434,8 @@ def compute_partials(self, inputs, J, discrete_inputs=None):
         J[f_h_key, Dynamic.Vehicle.DRAG] = c_gamma
         J[f_v_key, Dynamic.Vehicle.DRAG] = s_gamma
 
-        J[f_h_key, 'angle_of_attack'] = thrust * s_angle
-        J[f_v_key, 'angle_of_attack'] = thrust * c_angle
+        J[f_h_key, Dynamic.Vehicle.ANGLE_OF_ATTACK] = thrust * s_angle
+        J[f_v_key, Dynamic.Vehicle.ANGLE_OF_ATTACK] = thrust * c_angle
 
         f_h = -drag * s_gamma - lift * c_gamma - thrust * s_angle
         J[f_h_key, Dynamic.Mission.FLIGHT_PATH_ANGLE] = -f_h

aviary/mission/flops_based/ode/landing_ode.py

@@ -174,7 +174,7 @@ def setup(self):
                 Dynamic.Vehicle.LIFT,
                 Dynamic.Vehicle.Propulsion.THRUST_TOTAL,
                 Dynamic.Vehicle.DRAG,
-                'angle_of_attack',
+                Dynamic.Vehicle.ANGLE_OF_ATTACK,
                 'angle_of_attack_rate',
                 Mission.Landing.FLARE_RATE,
             ],

aviary/mission/flops_based/ode/takeoff_eom.py

@@ -547,7 +547,7 @@ def setup(self):
                          val=np.ones(nn), units='N')
         add_aviary_input(self, Dynamic.Vehicle.DRAG, val=np.ones(nn), units='N')
 
-        self.add_input('angle_of_attack', val=np.zeros(nn), units='rad')
+        self.add_input(Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
 
         add_aviary_input(
             self, Dynamic.Mission.FLIGHT_PATH_ANGLE, val=np.zeros(nn), units='rad'
@@ -586,7 +586,7 @@ def setup_partials(self):
                 Dynamic.Vehicle.Propulsion.THRUST_TOTAL,
                 Dynamic.Vehicle.LIFT,
                 Dynamic.Vehicle.DRAG,
-                'angle_of_attack',
+                Dynamic.Vehicle.ANGLE_OF_ATTACK,
                 Dynamic.Mission.FLIGHT_PATH_ANGLE,
             ]
 
@@ -635,7 +635,7 @@ def setup_partials(self):
 
             self.declare_partials(
                 'forces_horizontal',
-                ['angle_of_attack', Dynamic.Mission.FLIGHT_PATH_ANGLE],
+                [Dynamic.Vehicle.ANGLE_OF_ATTACK, Dynamic.Mission.FLIGHT_PATH_ANGLE],
                 dependent=False,
             )
 
@@ -664,7 +664,7 @@ def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
             alpha0 = \
                 aviary_options.get_val(Mission.Takeoff.ANGLE_OF_ATTACK_RUNWAY, 'rad')
 
-            alpha = inputs['angle_of_attack']
+            alpha = inputs[Dynamic.Vehicle.ANGLE_OF_ATTACK]
             gamma = inputs[Dynamic.Mission.FLIGHT_PATH_ANGLE]
 
             angle = alpha - alpha0 + t_inc + gamma
@@ -713,7 +713,7 @@ def compute_partials(self, inputs, J, discrete_inputs=None):
         thrust = inputs[Dynamic.Vehicle.Propulsion.THRUST_TOTAL]
         drag = inputs[Dynamic.Vehicle.DRAG]
 
-        alpha = inputs['angle_of_attack']
+        alpha = inputs[Dynamic.Vehicle.ANGLE_OF_ATTACK]
         gamma = inputs[Dynamic.Mission.FLIGHT_PATH_ANGLE]
 
         angle = alpha - alpha0 + t_inc + gamma
@@ -733,8 +733,8 @@ def compute_partials(self, inputs, J, discrete_inputs=None):
         J['forces_horizontal', Dynamic.Vehicle.DRAG] = -c_gamma
         J['forces_vertical', Dynamic.Vehicle.DRAG] = -s_gamma
 
-        J['forces_horizontal', 'angle_of_attack'] = -thrust * s_angle
-        J['forces_vertical', 'angle_of_attack'] = thrust * c_angle
+        J['forces_horizontal', Dynamic.Vehicle.ANGLE_OF_ATTACK] = -thrust * s_angle
+        J['forces_vertical', Dynamic.Vehicle.ANGLE_OF_ATTACK] = thrust * c_angle
 
         J['forces_horizontal', Dynamic.Mission.FLIGHT_PATH_ANGLE] = (
             -thrust * s_angle + drag * s_gamma - lift * c_gamma
@@ -772,7 +772,7 @@ def setup(self):
         )
         add_aviary_input(self, Dynamic.Vehicle.DRAG, val=np.ones(nn), units='N')
 
-        self.add_input('angle_of_attack', val=np.zeros(nn), units='rad')
+        self.add_input(Dynamic.Vehicle.ANGLE_OF_ATTACK, val=np.zeros(nn), units='rad')
 
         add_aviary_input(
             self, Dynamic.Mission.FLIGHT_PATH_ANGLE, val=np.zeros(nn), units='rad'
@@ -800,7 +800,7 @@ def setup_partials(self):
             [
                 Dynamic.Vehicle.MASS,
                 Dynamic.Vehicle.Propulsion.THRUST_TOTAL,
-                'angle_of_attack',
+                Dynamic.Vehicle.ANGLE_OF_ATTACK,
                 Dynamic.Mission.FLIGHT_PATH_ANGLE,
             ],
             rows=rows_cols,
@@ -846,7 +846,7 @@ def compute(self, inputs, outputs, discrete_inputs=None, discrete_outputs=None):
 
         weight = mass * grav_metric
 
-        alpha = inputs['angle_of_attack']
+        alpha = inputs[Dynamic.Vehicle.ANGLE_OF_ATTACK]
         gamma = inputs[Dynamic.Mission.FLIGHT_PATH_ANGLE]
 
         angle = alpha - alpha0 + t_inc
@@ -880,7 +880,7 @@ def compute_partials(self, inputs, J, discrete_inputs=None):
 
         weight = mass * grav_metric
 
-        alpha = inputs['angle_of_attack']
+        alpha = inputs[Dynamic.Vehicle.ANGLE_OF_ATTACK]
         gamma = inputs[Dynamic.Mission.FLIGHT_PATH_ANGLE]
 
         angle = alpha - alpha0 + t_inc
@@ -900,8 +900,8 @@ def compute_partials(self, inputs, J, discrete_inputs=None):
         J[f_h_key, Dynamic.Vehicle.Propulsion.THRUST_TOTAL] = c_angle
         J[f_v_key, Dynamic.Vehicle.Propulsion.THRUST_TOTAL] = s_angle
 
-        J[f_h_key, 'angle_of_attack'] = -thrust * s_angle
-        J[f_v_key, 'angle_of_attack'] = thrust * c_angle
+        J[f_h_key, Dynamic.Vehicle.ANGLE_OF_ATTACK] = -thrust * s_angle
+        J[f_v_key, Dynamic.Vehicle.ANGLE_OF_ATTACK] = thrust * c_angle
 
         J[f_h_key, Dynamic.Mission.FLIGHT_PATH_ANGLE] = -weight * c_gamma
         J[f_v_key, Dynamic.Mission.FLIGHT_PATH_ANGLE] = weight * s_gamma

aviary/mission/flops_based/ode/takeoff_ode.py

@@ -180,7 +180,7 @@ def setup(self):
                 Dynamic.Vehicle.LIFT,
                 Dynamic.Vehicle.Propulsion.THRUST_TOTAL,
                 Dynamic.Vehicle.DRAG,
-                'angle_of_attack',
+                Dynamic.Vehicle.ANGLE_OF_ATTACK,
             ],
             promotes_outputs=[
                 Dynamic.Mission.DISTANCE_RATE,

aviary/mission/flops_based/ode/test/test_landing_eom.py

@@ -46,7 +46,7 @@ def test_case(self):
             input_validation_data=detailed_landing_flare,
             output_validation_data=detailed_landing_flare,
             input_keys=[
-                'angle_of_attack',
+                Dynamic.Vehicle.ANGLE_OF_ATTACK,
                 Dynamic.Mission.FLIGHT_PATH_ANGLE,
                 Dynamic.Mission.VELOCITY,
                 Dynamic.Vehicle.MASS,
@@ -107,7 +107,7 @@ def test_GlideSlopeForces(self):
             units="N",
         )
         prob.model.set_input_defaults(
-            "angle_of_attack", np.array([5.086, 6.834]), units="deg"
+            Dynamic.Vehicle.ANGLE_OF_ATTACK, np.array([5.086, 6.834]), units="deg"
         )
         prob.model.set_input_defaults(
             Dynamic.Mission.FLIGHT_PATH_ANGLE, np.array([-3.0, -2.47]), units="deg"
@@ -153,7 +153,7 @@ def test_FlareSumForces(self):
             Dynamic.Vehicle.Propulsion.THRUST_TOTAL, np.array([4980.3, 4102]), units="N"
         )
         prob.model.set_input_defaults(
-            "angle_of_attack", np.array([5.086, 6.834]), units="deg"
+            Dynamic.Vehicle.ANGLE_OF_ATTACK, np.array([5.086, 6.834]), units="deg"
         )
         prob.model.set_input_defaults(
             Dynamic.Mission.FLIGHT_PATH_ANGLE, np.array([-3.0, -2.47]), units="deg"

aviary/mission/flops_based/ode/test/test_landing_ode.py

@@ -54,7 +54,7 @@ def test_case(self):
             input_validation_data=detailed_landing_flare,
             output_validation_data=detailed_landing_flare,
             input_keys=[
-                'angle_of_attack',
+                Dynamic.Vehicle.ANGLE_OF_ATTACK,
                 Dynamic.Mission.FLIGHT_PATH_ANGLE,
                 Dynamic.Mission.VELOCITY,
                 Dynamic.Vehicle.MASS,

aviary/mission/flops_based/ode/test/test_takeoff_eom.py

@@ -29,7 +29,7 @@ def test_case_ground(self):
             input_validation_data=detailed_takeoff_ground,
             output_validation_data=detailed_takeoff_ground,
             input_keys=[
-                'angle_of_attack',
+                Dynamic.Vehicle.ANGLE_OF_ATTACK,
                 Dynamic.Mission.FLIGHT_PATH_ANGLE,
                 Dynamic.Mission.VELOCITY,
                 Dynamic.Vehicle.MASS,
@@ -54,7 +54,7 @@ def test_case_climbing(self):
             input_validation_data=detailed_takeoff_climbing,
             output_validation_data=detailed_takeoff_climbing,
             input_keys=[
-                'angle_of_attack',
+                Dynamic.Vehicle.ANGLE_OF_ATTACK,
                 Dynamic.Mission.FLIGHT_PATH_ANGLE,
                 Dynamic.Mission.VELOCITY,
                 Dynamic.Vehicle.MASS,
@@ -395,7 +395,7 @@ def test_ClimbGradientForces(self):
             Dynamic.Mission.FLIGHT_PATH_ANGLE, np.array([0.612, 4.096]), units="rad"
         )
         prob.model.set_input_defaults(
-            "angle_of_attack", np.array([5.086, 6.834]), units="rad"
+            Dynamic.Vehicle.ANGLE_OF_ATTACK, np.array([5.086, 6.834]), units="rad"
         )
 
         prob.setup(check=False, force_alloc_complex=True)

aviary/mission/flops_based/ode/test/test_takeoff_ode.py

@@ -30,7 +30,7 @@ def test_case_ground(self):
             input_validation_data=detailed_takeoff_ground,
             output_validation_data=detailed_takeoff_ground,
             input_keys=[
-                'angle_of_attack',
+                Dynamic.Vehicle.ANGLE_OF_ATTACK,
                 Dynamic.Mission.FLIGHT_PATH_ANGLE,
                 Dynamic.Mission.ALTITUDE,
                 Dynamic.Mission.VELOCITY,
@@ -60,7 +60,7 @@ def test_case_climbing(self):
             input_validation_data=detailed_takeoff_climbing,
             output_validation_data=detailed_takeoff_climbing,
             input_keys=[
-                'angle_of_attack',
+                Dynamic.Vehicle.ANGLE_OF_ATTACK,
                 Dynamic.Mission.FLIGHT_PATH_ANGLE,
                 Dynamic.Mission.ALTITUDE,
                 Dynamic.Mission.VELOCITY,

aviary/mission/flops_based/phases/detailed_landing_phases.py

@@ -205,7 +205,7 @@ def build_phase(self, aviary_options: AviaryValues = None):
         angle_of_attack_ref = user_options.get_val('angle_of_attack_ref', units)
 
         phase.add_control(
-            'angle_of_attack', opt=True, units=units,
+            Dynamic.Vehicle.ANGLE_OF_ATTACK, opt=True, units=units,
             upper=upper_angle_of_attack, lower=lower_angle_of_attack,
             ref=angle_of_attack_ref
         )
@@ -275,7 +275,7 @@ def _extra_ode_init_kwargs(self):
 LandingApproachToMicP3._add_meta_data('initial_height', val=1., units='ft')
 
 LandingApproachToMicP3._add_initial_guess_meta_data(
-    InitialGuessControl('angle_of_attack'))
+    InitialGuessControl(Dynamic.Vehicle.ANGLE_OF_ATTACK))
 
 LandingApproachToMicP3._add_initial_guess_meta_data(InitialGuessState('altitude'))
 
@@ -530,7 +530,7 @@ def build_phase(self, aviary_options: AviaryValues = None):
             opt=False
         )
 
-        phase.add_control('angle_of_attack', opt=False, units='deg')
+        phase.add_control(Dynamic.Vehicle.ANGLE_OF_ATTACK, opt=False, units='deg')
 
         phase.add_timeseries_output(
             Dynamic.Vehicle.DRAG, output_name=Dynamic.Vehicle.DRAG, units='lbf'
@@ -590,7 +590,7 @@ def _extra_ode_init_kwargs(self):
 LandingObstacleToFlare._add_meta_data('altitude_ref', val=1., units='ft')
 
 LandingObstacleToFlare._add_initial_guess_meta_data(
-    InitialGuessControl('angle_of_attack'))
+    InitialGuessControl(Dynamic.Vehicle.ANGLE_OF_ATTACK))
 
 LandingObstacleToFlare._add_initial_guess_meta_data(InitialGuessState('altitude'))
 
@@ -763,7 +763,7 @@ def build_phase(self, aviary_options: AviaryValues = None):
         angle_of_attack_ref = user_options.get_val('angle_of_attack_ref', units)
 
         phase.add_polynomial_control(
-            'angle_of_attack', opt=True, units=units, order=1,
+            Dynamic.Vehicle.ANGLE_OF_ATTACK, opt=True, units=units, order=1,
             lower=lower_angle_of_attack, upper=upper_angle_of_attack,
             ref=angle_of_attack_ref,
             rate_targets="angle_of_attack_rate"
@@ -829,7 +829,7 @@ def _extra_ode_init_kwargs(self):
 LandingFlareToTouchdown._add_meta_data('angle_of_attack_ref', val=10., units='deg')
 
 LandingFlareToTouchdown._add_initial_guess_meta_data(
-    InitialGuessPolynomialControl('angle_of_attack'))
+    InitialGuessPolynomialControl(Dynamic.Vehicle.ANGLE_OF_ATTACK))
 
 LandingFlareToTouchdown._add_initial_guess_meta_data(InitialGuessState('altitude'))
 
@@ -974,7 +974,7 @@ def build_phase(self, aviary_options=None):
         max_angle_of_attack = user_options.get_val('max_angle_of_attack', units)
 
         phase.add_polynomial_control(
-            'angle_of_attack', opt=True, units=units, order=1,
+            Dynamic.Vehicle.ANGLE_OF_ATTACK, opt=True, units=units, order=1,
             lower=0, upper=max_angle_of_attack, fix_final=True,
             fix_initial=False, ref=max_angle_of_attack)
 
@@ -1019,7 +1019,7 @@ def _extra_ode_init_kwargs(self):
 LandingTouchdownToNoseDown._add_meta_data('max_angle_of_attack', val=10.0, units='deg')
 
 LandingTouchdownToNoseDown._add_initial_guess_meta_data(
-    InitialGuessPolynomialControl('angle_of_attack'))
+    InitialGuessPolynomialControl(Dynamic.Vehicle.ANGLE_OF_ATTACK))
 
 
 @_init_initial_guess_meta_data
@@ -1155,7 +1155,7 @@ def build_phase(self, aviary_options=None):
             opt=False
         )
 
-        phase.add_parameter('angle_of_attack', val=0.0, opt=False, units='deg')
+        phase.add_parameter(Dynamic.Vehicle.ANGLE_OF_ATTACK, val=0.0, opt=False, units='deg')
 
         phase.add_timeseries_output(
             Dynamic.Vehicle.Propulsion.THRUST_TOTAL,
@@ -1196,7 +1196,7 @@ def _extra_ode_init_kwargs(self):
 LandingNoseDownToStop._add_meta_data('max_velocity', val=100.0, units='ft/s')
 
 LandingNoseDownToStop._add_initial_guess_meta_data(
-    InitialGuessParameter('angle_of_attack'))
+    InitialGuessParameter(Dynamic.Vehicle.ANGLE_OF_ATTACK))
 
 
 class LandingTrajectory: