Added test for N+3 HSA example

examples/HybridTwin_active_thermal.py

@@ -24,7 +24,7 @@
 from openconcept.utilities.visualization import plot_trajectory
 
 """
-WARNING: This example has known convergence issues because of the chiller in the
+WARNING: This example has known convergence problems because of the chiller in the
          propulsion layout (TwinSeriesHybridElectricPropulsionRefrigerated)
 
 Eytan Adler, 27/10/2021

examples/tests/test_example_aircraft.py

@@ -12,6 +12,7 @@
 from examples.Caravan import run_caravan_analysis
 from examples.KingAirC90GT import run_kingair_analysis
 from examples.ElectricSinglewithThermal import run_electricsingle_analysis
+from examples.N3_HybridSingleAisle_Refrig import run_hybrid_sa_analysis
 
 
 class TBMAnalysisTestCase(unittest.TestCase):
@@ -130,29 +131,14 @@ def test_values_B738(self):
         assert_near_equal(prob.get_val('loiter.fuel_used_final', units='lbm'), 34424.68533072, tolerance=3e-4)
         # changelog: 9/2020 - previously 34555.313, updated CFM surrogate model to reject spurious high Mach, low altitude points
 
+class N3HSATestCase(unittest.TestCase):
+    def setUp(self):
+        self.prob = run_hybrid_sa_analysis(plots=False)
+
+    def test_values_N3HSA(self):
+        prob = self.prob
+        # block fuel (no reserve, since the N+3 HSA uses the basic 3-phase mission)
+        assert_near_equal(prob.get_val('descent.fuel_used_final', units='lbm'), 9006.52397811, tolerance=1e-5)
+
 if __name__=="__main__":
-    # unittest.main()
-
-    prob = run_hybrid_twin_active_thermal_analysis()
-
-    climb_duct_area = np.array([ 0.80614565,  3.25480096,  7.11240858, 12.075577  , 17.55488029,
-                                23.40694116, 29.15510781, 34.44182758, 39.05343787, 43.00420553, 46.43866073])
-    cruise_duct_area = np.array([17.17611522, 15.22748148, 14.66271227, 14.38669164, 14.2745505 ,
-                                    14.20434496, 14.15713767, 14.11684779, 14.08034799, 14.04524349, 14.01099713])
-    prob.set_val('climb.propmodel.duct.area_nozzle', climb_duct_area, units='inch**2')
-    prob.set_val('cruise.propmodel.duct.area_nozzle', cruise_duct_area, units='inch**2')
-    prob.run_model()
-
-    assert_near_equal(prob.get_val('climb.OEW', units='lb'), 6673.001027260613, tolerance=1e-5)
-    # assert_near_equal(prob.get_val('descent.fuel_used_final', units='lb'), 871.66394047, tolerance=1e-5)
-    # assert_near_equal(prob.get_val('descent.propmodel.batt1.SOC_final', units=None), 0.00484123, tolerance=1e-5)
-
-    assert_near_equal(prob.get_val('climb.propmodel.duct.area_nozzle', units='inch**2'), climb_duct_area, tolerance=1e-5)
-    assert_near_equal(prob.get_val('cruise.propmodel.duct.area_nozzle', units='inch**2'), cruise_duct_area, tolerance=1e-5)
-    Wdot = np.array([ 6618.15094465, 17863.48477045, 25558.10458551, 30652.72996714, 33805.46342847, 35538.5460011,
-                        36221.44062722, 36149.9707508, 35539.35428109, 34562.89222503, 33346.05141285])
-    assert_near_equal(prob.get_val('climb.propmodel.refrig.elec_load', units='W'), Wdot, tolerance=1e-5)
-    assert_near_equal(prob.get_val('cruise.propmodel.refrig.elec_load', units='W'), np.zeros(11), tolerance=1e-5)
-    assert_near_equal(prob.get_val('climb.propmodel.motorheatsink.T', units='degC')[-1], 76.48202028574951, tolerance=1e-5)
-    assert_near_equal(prob.get_val('climb.propmodel.batteryheatsink.T', units='degC')[-1], 6.9112870295027165, tolerance=1e-5)
-    assert_near_equal(prob.get_val('cruise.propmodel.duct.drag', units='lbf')[-1], 1.5888992670493287, tolerance=1e-5)
+    unittest.main()