Fix level2 detailed takeoff example

aviary/examples/run_level2_with_detailed_landing.py

@@ -167,6 +167,9 @@
 
 prob.setup()
 
+# set the start-of-landing mass to mission:summary:gross_mass
+prob.set_val('mission:summary:gross_mass', 120000, units='lbm')
+
 prob.run_aviary_problem()
 
 try:

aviary/examples/run_level2_with_detailed_takeoff.py

@@ -27,13 +27,14 @@
 
 mach_optimize = True
 altitude_optimize = True
-optimizer = 'SLSQP'
+optimizer = 'IPOPT'
+num_segments = 2
 
 phase_info = {
     'pre_mission': {'include_takeoff': False, 'optimize_mass': False},
     'AB': {
         'user_options': {
-            'num_segments': 5,
+            'num_segments': num_segments,
             'order': 3,
             'ground_roll': True,
             'time_duration_ref': (100.0, 'kn'),
@@ -50,7 +51,7 @@
     },
     'rotate': {
         'user_options': {
-            'num_segments': 5,
+            'num_segments': num_segments,
             'order': 3,
             'ground_roll': True,
             'clean': False,
@@ -88,7 +89,7 @@
     },
     'BC': {
         'user_options': {
-            'num_segments': 5,
+            'num_segments': num_segments,
             'order': 3,
             'clean': False,
             'time_initial_ref': (1.0e3, 'ft'),
@@ -115,7 +116,7 @@
     },
     'CD_to_P2': {
         'user_options': {
-            'num_segments': 4,
+            'num_segments': num_segments,
             'order': 3,
             'clean': False,
             'time_initial_ref': (1.0e3, 'ft'),
@@ -150,7 +151,7 @@
     },
     'P2_to_DE': {
         'user_options': {
-            'num_segments': 4,
+            'num_segments': num_segments,
             'order': 3,
             'clean': False,
             'time_initial_ref': (1.0e3, 'ft'),
@@ -185,7 +186,7 @@
     },
     'DE': {
         'user_options': {
-            'num_segments': 3,
+            'num_segments': num_segments,
             'order': 3,
             'clean': False,
             'time_initial_ref': (1.0e3, 'ft'),
@@ -219,7 +220,7 @@
     },
     'EF_to_P1': {
         'user_options': {
-            'num_segments': 3,
+            'num_segments': num_segments,
             'order': 3,
             'clean': False,
             'time_initial_ref': (1.0e3, 'ft'),
@@ -260,7 +261,7 @@
     },
     'EF_past_P1': {
         'user_options': {
-            'num_segments': 5,
+            'num_segments': num_segments,
             'order': 3,
             'clean': False,
             'time_initial_ref': (1.0e3, 'ft'),
@@ -317,16 +318,23 @@
 
     prob.build_model()
 
-    prob.add_driver(optimizer, max_iter=25)
+    prob.add_driver(optimizer, max_iter=200, verbosity=2)
+    # custom optimizer seettings
+    prob.driver.opt_settings['mu_init'] = 1.0
+    prob.driver.opt_settings['nlp_scaling_method'] = 'none'
+    prob.driver.opt_settings['limited_memory_max_history'] = 50
 
     prob.add_design_variables()
 
     # Load optimization problem formulation
     # Detail which variables the optimizer can control
-    prob.add_objective('mass')
+    prob.add_objective('mass')  # maximize final mass (i.e. minimize fuel burn)
 
     prob.setup()
 
+    # set takeoff (initial) mass
+    prob.set_val('mission:summary:gross_mass', 175000, units='lbm')
+
     prob.run_aviary_problem(suppress_solver_print=True)
 
     try:

aviary/mission/solved_two_dof_problem_configurator.py

@@ -1,3 +1,5 @@
+import openmdao.api as om
+
 from aviary.mission.flops_based.phases.groundroll_phase import (
     GroundrollPhase as GroundrollPhaseVelocityIntegrated,
 )
@@ -246,7 +248,7 @@ def check_trajectory(self, aviary_group):
         """
         pass
 
-    def add_post_mission_systems(self, model):
+    def add_post_mission_systems(self, aviary_group):
         """
         Add any post mission systems.
 
@@ -259,7 +261,29 @@ def add_post_mission_systems(self, model):
         aviary_group : AviaryGroup
             Aviary model that owns this configurator.
         """
-        pass
+        # Add a mass equality constraint to set mission:summary:gross_mass = initial mass state
+        first_flight_phase_name = list(aviary_group.phase_info.keys())[0]
+        first_flight_phase = aviary_group.traj._phases[first_flight_phase_name]
+        first_flight_phase.set_state_options(
+            Dynamic.Vehicle.MASS, fix_initial=False, input_initial=False
+        )
+
+        # connect summary mass to the initial guess of mass in the first phase
+        eq = aviary_group.add_subsystem(
+            f'link_{first_flight_phase_name}_mass',
+            om.EQConstraintComp(),
+            promotes_inputs=[('rhs:mass', Mission.Summary.GROSS_MASS)],
+        )
+
+        # TODO: replace hard_coded ref for this constraint.
+        eq.add_eq_output('mass', eq_units='lbm', normalize=False, ref=100000.0, add_constraint=True)
+
+        aviary_group.connect(
+            f'traj.{first_flight_phase_name}.states:mass',
+            f'link_{first_flight_phase_name}_mass.lhs:mass',
+            src_indices=[0],
+            flat_src_indices=True,
+        )
 
     def set_phase_initial_guesses(
         self, aviary_group, phase_name, phase, guesses, target_prob, parent_prefix