diff --git a/aviary/constants.py b/aviary/constants.py index c7770d804..23b694d60 100644 --- a/aviary/constants.py +++ b/aviary/constants.py @@ -7,6 +7,8 @@ GRAV_METRIC_FLOPS = 9.80665 # m/s^2 GRAV_ENGLISH_FLOPS = 32.17399 # ft/s^2 GRAV_ENGLISH_LBM = 1.0 # lbf/lbm +# TODO this does not match what dymos atmosphere comp predicts, which leads to subtle +# problems such as density ratio not being 1 at sea level RHO_SEA_LEVEL_ENGLISH = 0.0023769 # slug/ft^3 RHO_SEA_LEVEL_METRIC = 1.225 # kg/m^3 MU_TAKEOFF = 0.02 # TODO: fill in coefficient of friction for takeoff diff --git a/aviary/mission/gasp_based/ode/landing_eom.py b/aviary/mission/gasp_based/ode/landing_eom.py index d7ddaa3ee..faf6c1794 100644 --- a/aviary/mission/gasp_based/ode/landing_eom.py +++ b/aviary/mission/gasp_based/ode/landing_eom.py @@ -36,7 +36,9 @@ class GlideConditionComponent(om.ExplicitComponent): """ def setup(self): - self.add_input("rho_app", val=0.0, units="slug/ft**3", desc="air density") + self.add_input( + Dynamic.Mission.DENSITY, val=0.0, units="slug/ft**3", desc="air density" + ) add_aviary_input(self, Mission.Landing.MAXIMUM_SINK_RATE, val=900.0) self.add_input(Dynamic.Mission.MASS, val=0.0, units="lbm", desc="aircraft mass at start of landing") @@ -94,19 +96,34 @@ def setup(self): self.declare_partials( Mission.Landing.INITIAL_VELOCITY, - [Dynamic.Mission.MASS, Aircraft.Wing.AREA, "CL_max", "rho_app", - Mission.Landing.GLIDE_TO_STALL_RATIO], + [ + Dynamic.Mission.MASS, + Aircraft.Wing.AREA, + "CL_max", + Dynamic.Mission.DENSITY, + Mission.Landing.GLIDE_TO_STALL_RATIO, + ], ) self.declare_partials( - Mission.Landing.STALL_VELOCITY, [ - Dynamic.Mission.MASS, Aircraft.Wing.AREA, "CL_max", "rho_app"] + Mission.Landing.STALL_VELOCITY, + [ + Dynamic.Mission.MASS, + Aircraft.Wing.AREA, + "CL_max", + Dynamic.Mission.DENSITY, + ], ) self.declare_partials( "TAS_touchdown", - [Mission.Landing.GLIDE_TO_STALL_RATIO, Dynamic.Mission.MASS, - Aircraft.Wing.AREA, "CL_max", "rho_app"], + [ + Mission.Landing.GLIDE_TO_STALL_RATIO, + Dynamic.Mission.MASS, + Aircraft.Wing.AREA, + "CL_max", + Dynamic.Mission.DENSITY, + ], ) - self.declare_partials("density_ratio", ["rho_app"]) + self.declare_partials("density_ratio", [Dynamic.Mission.DENSITY]) self.declare_partials("wing_loading_land", [ Dynamic.Mission.MASS, Aircraft.Wing.AREA]) self.declare_partials( @@ -116,7 +133,7 @@ def setup(self): Dynamic.Mission.MASS, Aircraft.Wing.AREA, "CL_max", - "rho_app", + Dynamic.Mission.DENSITY, Mission.Landing.GLIDE_TO_STALL_RATIO, ], ) @@ -128,7 +145,7 @@ def setup(self): Dynamic.Mission.MASS, Aircraft.Wing.AREA, "CL_max", - "rho_app", + Dynamic.Mission.DENSITY, Mission.Landing.GLIDE_TO_STALL_RATIO, ], ) @@ -140,7 +157,7 @@ def setup(self): Dynamic.Mission.MASS, Aircraft.Wing.AREA, "CL_max", - "rho_app", + Dynamic.Mission.DENSITY, Mission.Landing.GLIDE_TO_STALL_RATIO, Mission.Landing.MAXIMUM_SINK_RATE, ], @@ -152,7 +169,7 @@ def setup(self): Dynamic.Mission.MASS, Aircraft.Wing.AREA, "CL_max", - "rho_app", + Dynamic.Mission.DENSITY, Mission.Landing.BRAKING_DELAY, ], ) @@ -165,7 +182,7 @@ def setup(self): Dynamic.Mission.MASS, Aircraft.Wing.AREA, "CL_max", - "rho_app", + Dynamic.Mission.DENSITY, Mission.Landing.GLIDE_TO_STALL_RATIO, ], ) @@ -274,9 +291,9 @@ def compute_partials(self, inputs, J): J[Mission.Landing.INITIAL_VELOCITY, "CL_max"] = dTasGlide_dClMax = ( dTasStall_dClMax * glide_to_stall_ratio ) - J[Mission.Landing.INITIAL_VELOCITY, "rho_app"] = dTasGlide_dRhoApp = ( - dTasStall_dRhoApp * glide_to_stall_ratio - ) + J[Mission.Landing.INITIAL_VELOCITY, Dynamic.Mission.DENSITY] = ( + dTasGlide_dRhoApp + ) = (dTasStall_dRhoApp * glide_to_stall_ratio) J[Mission.Landing.INITIAL_VELOCITY, Mission.Landing.GLIDE_TO_STALL_RATIO] = TAS_stall @@ -284,7 +301,7 @@ def compute_partials(self, inputs, J): dTasStall_dWeight * GRAV_ENGLISH_LBM J[Mission.Landing.STALL_VELOCITY, Aircraft.Wing.AREA] = dTasStall_dWingArea J[Mission.Landing.STALL_VELOCITY, "CL_max"] = dTasStall_dClMax - J[Mission.Landing.STALL_VELOCITY, "rho_app"] = dTasStall_dRhoApp + J[Mission.Landing.STALL_VELOCITY, Dynamic.Mission.DENSITY] = dTasStall_dRhoApp J["TAS_touchdown", Mission.Landing.GLIDE_TO_STALL_RATIO] = dTasTd_dGlideToStallRatio = ( 0.5 * TAS_stall @@ -296,11 +313,11 @@ def compute_partials(self, inputs, J): J["TAS_touchdown", "CL_max"] = dTasTd_dClMax = ( touchdown_velocity_ratio * dTasStall_dClMax ) - J["TAS_touchdown", "rho_app"] = dTasTd_dRhoApp = ( + J["TAS_touchdown", Dynamic.Mission.DENSITY] = dTasTd_dRhoApp = ( touchdown_velocity_ratio * dTasStall_dRhoApp ) - J["density_ratio", "rho_app"] = 1 / RHO_SEA_LEVEL_ENGLISH + J["density_ratio", Dynamic.Mission.DENSITY] = 1 / RHO_SEA_LEVEL_ENGLISH J["wing_loading_land", Dynamic.Mission.MASS] = GRAV_ENGLISH_LBM / wing_area J["wing_loading_land", Aircraft.Wing.AREA] = -weight / wing_area**2 @@ -323,7 +340,7 @@ def compute_partials(self, inputs, J): * (-rate_of_sink_max / (60.0 * TAS_glide**2)) * dTasGlide_dClMax ) - J["theta", "rho_app"] = dTheta_dRhoApp = ( + J["theta", Dynamic.Mission.DENSITY] = dTheta_dRhoApp = ( (1 - (rate_of_sink_max / (60.0 * TAS_glide)) ** 2) ** (-0.5) * (-rate_of_sink_max / (60.0 * TAS_glide**2)) * dTasGlide_dRhoApp @@ -361,7 +378,7 @@ def compute_partials(self, inputs, J): * (1 / np.cos(theta)) ** 2 * dTheta_dClMax ) - J["glide_distance", "rho_app"] = ( + J["glide_distance", Dynamic.Mission.DENSITY] = ( -approach_alt / (np.tan(theta)) ** 2 * (1 / np.cos(theta)) ** 2 @@ -475,7 +492,7 @@ def compute_partials(self, inputs, J): dInter1_dWingArea * inter2 + inter1 * dInter2_dWingArea ) J["tr_distance", "CL_max"] = dInter1_dClMax * inter2 + inter1 * dInter2_dClMax - J["tr_distance", "rho_app"] = ( + J["tr_distance", Dynamic.Mission.DENSITY] = ( dInter1_dRhoApp * inter2 + inter1 * dInter2_dRhoApp ) J["tr_distance", Mission.Landing.GLIDE_TO_STALL_RATIO] = ( @@ -490,7 +507,7 @@ def compute_partials(self, inputs, J): time_delay * dTasTd_dWeight * GRAV_ENGLISH_LBM J["delay_distance", Aircraft.Wing.AREA] = time_delay * dTasTd_dWingArea J["delay_distance", "CL_max"] = time_delay * dTasTd_dClMax - J["delay_distance", "rho_app"] = time_delay * dTasTd_dRhoApp + J["delay_distance", Dynamic.Mission.DENSITY] = time_delay * dTasTd_dRhoApp J["delay_distance", Mission.Landing.BRAKING_DELAY] = TAS_touchdown flare_alt = ( @@ -553,7 +570,7 @@ def compute_partials(self, inputs, J): * (2 * theta * dTheta_dClMax - 2 * gamma_touchdown * dGammaTd_dClMax) ) ) - J["flare_alt", "rho_app"] = ( + J["flare_alt", Dynamic.Mission.DENSITY] = ( 1 / (2.0 * G * (landing_flare_load_factor - 1.0)) * ( diff --git a/aviary/mission/gasp_based/ode/landing_ode.py b/aviary/mission/gasp_based/ode/landing_ode.py index dab9b9029..acb3627fd 100644 --- a/aviary/mission/gasp_based/ode/landing_ode.py +++ b/aviary/mission/gasp_based/ode/landing_ode.py @@ -41,12 +41,12 @@ def setup(self): (Dynamic.Mission.MACH, Mission.Landing.INITIAL_MACH), ], promotes_outputs=[ - (Dynamic.Mission.DENSITY, "rho_app"), - (Dynamic.Mission.SPEED_OF_SOUND, "sos_app"), - (Dynamic.Mission.TEMPERATURE, "T_app"), - (Dynamic.Mission.STATIC_PRESSURE, "P_app"), - ("viscosity", "viscosity_app"), - (Dynamic.Mission.DYNAMIC_PRESSURE, "q_app"), + Dynamic.Mission.DENSITY, + Dynamic.Mission.SPEED_OF_SOUND, + Dynamic.Mission.TEMPERATURE, + Dynamic.Mission.STATIC_PRESSURE, + "viscosity", + Dynamic.Mission.DYNAMIC_PRESSURE, ], ) @@ -64,12 +64,12 @@ def setup(self): promotes_inputs=[ "*", (Dynamic.Mission.ALTITUDE, Mission.Landing.INITIAL_ALTITUDE), - (Dynamic.Mission.DENSITY, "rho_app"), - (Dynamic.Mission.SPEED_OF_SOUND, "sos_app"), - ("viscosity", "viscosity_app"), + Dynamic.Mission.DENSITY, + Dynamic.Mission.SPEED_OF_SOUND, + "viscosity", ("airport_alt", Mission.Landing.AIRPORT_ALTITUDE), (Dynamic.Mission.MACH, Mission.Landing.INITIAL_MACH), - (Dynamic.Mission.DYNAMIC_PRESSURE, "q_app"), + Dynamic.Mission.DYNAMIC_PRESSURE, ("flap_defl", Aircraft.Wing.FLAP_DEFLECTION_LANDING), ("t_init_flaps", "t_init_flaps_app"), ("t_init_gear", "t_init_gear_app"), @@ -100,7 +100,7 @@ def setup(self): "glide", GlideConditionComponent(), promotes_inputs=[ - "rho_app", + Dynamic.Mission.DENSITY, Mission.Landing.MAXIMUM_SINK_RATE, Dynamic.Mission.MASS, Aircraft.Wing.AREA, diff --git a/aviary/mission/gasp_based/ode/params.py b/aviary/mission/gasp_based/ode/params.py index c18e4e9c3..cd7264eff 100644 --- a/aviary/mission/gasp_based/ode/params.py +++ b/aviary/mission/gasp_based/ode/params.py @@ -141,18 +141,10 @@ def promote_params(sys, trajs=None, phases=None): 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 - ), + 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), } diff --git a/aviary/mission/gasp_based/ode/test/test_landing_eom.py b/aviary/mission/gasp_based/ode/test/test_landing_eom.py index d82fdaab7..15723113f 100644 --- a/aviary/mission/gasp_based/ode/test/test_landing_eom.py +++ b/aviary/mission/gasp_based/ode/test/test_landing_eom.py @@ -8,7 +8,7 @@ from aviary.mission.gasp_based.ode.landing_eom import ( GlideConditionComponent, LandingAltitudeComponent, LandingGroundRollComponent) -from aviary.variable_info.variables import Aircraft, Mission +from aviary.variable_info.variables import Aircraft, Mission, Dynamic class LandingAltTestCase(unittest.TestCase): @@ -55,7 +55,7 @@ def setUp(self): ) self.prob.model.set_input_defaults( - "rho_app", RHO_SEA_LEVEL_ENGLISH, units="slug/ft**3" + Dynamic.Mission.DENSITY, RHO_SEA_LEVEL_ENGLISH, units="slug/ft**3" ) # value from online calculator self.prob.model.set_input_defaults( @@ -137,7 +137,8 @@ def test_case1(self): prob.model.add_subsystem( "group", GlideConditionComponent(), promotes=["*"]) prob.model.set_input_defaults( - "rho_app", RHO_SEA_LEVEL_ENGLISH, units="slug/ft**3") + Dynamic.Mission.DENSITY, RHO_SEA_LEVEL_ENGLISH, units="slug/ft**3" + ) prob.model.set_input_defaults( Mission.Landing.MAXIMUM_SINK_RATE, 900, units="ft/min") prob.model.set_input_defaults("mass", 165279, units="lbm") diff --git a/aviary/models/engines/turboshaft_4465hp.deck b/aviary/models/engines/turboshaft_4465hp.deck index 23f1ddba8..91a42a30a 100644 --- a/aviary/models/engines/turboshaft_4465hp.deck +++ b/aviary/models/engines/turboshaft_4465hp.deck @@ -1,4 +1,4 @@ -# GASP_TS-derived engine deck converted from turboshaft_4465hp.eng +# GASP-derived turboshaft engine deck converted from turboshaft_4465hp.eng # t4max: 50.0 # t4cruise: 45.0 # t4climb: 50.0 @@ -12,2180 +12,1772 @@ # torque_limit: 22976.2 # sls_corrected_airflow: 30.5 - Mach_Number, Altitude (ft), Throttle, Shaft_Power_Corrected (hp), Tailpipe_Thrust (lbf), Fuel_Flow (lb/h) - 0.0, 0.0, 26.0, 794.3999999999999, 618.3999999999999, 1035.8999999999999 - 0.05, 0.0, 26.0, 794.7000000000002, 563.7, 1033.8000000000002 - 0.1, 0.0, 26.0, 794.3, 508.8000000000001, 1027.5000000000007 -0.15000000000000002, 0.0, 26.0, 793.2000000000002, 454.1000000000001, 1016.8 - 0.2, 0.0, 26.0, 791.4, 399.60000000000025, 1001.9999999999999 - 0.25, 0.0, 26.0, 788.1000000000004, 345.4, 983.1000000000009 -0.30000000000000004, 0.0, 26.0, 784.1000000000001, 292.0, 960.5 -0.35000000000000003, 0.0, 26.0, 779.4999999999995, 239.9999999999999, 934.2999999999998 - 0.4, 0.0, 26.0, 773.8999999999988, 189.10000000000008, 904.8000000000008 - 0.45, 0.0, 26.0, 766.7000000000006, 139.39999999999992, 872.3999999999997 - 0.5, 0.0, 26.0, 758.8000000000015, 91.2, 837.2999999999996 - 0.55, 0.0, 26.0, 751.100000000003, 44.80000000000016, 799.6999999999994 - 0.6000000000000001, 0.0, 26.0, 744.5000000000052, 0.5000000000005871, 759.7999999999993 - 0.65, 0.0, 26.0, 739.9000000000082, -41.399999999998585, 717.7999999999993 - 0.7000000000000001, 0.0, 26.0, 738.2000000000118, -80.59999999999746, 673.8999999999996 - 0.75, 0.0, 26.0, 740.3000000000164, -116.79999999999583, 628.3000000000001 - 0.8, 0.0, 26.0, 747.100000000022, -149.69999999999374, 581.200000000001 - 0.0, 0.0, 28.0, 1191.5999999999997, 651.7, 1194.4999999999995 - 0.05, 0.0, 28.0, 1192.0999999999997, 597.0999999999993, 1192.4999999999975 - 0.1, 0.0, 28.0, 1191.5000000000005, 542.3999999999995, 1185.899999999994 -0.15000000000000002, 0.0, 28.0, 1189.7999999999984, 487.79999999999933, 1174.899999999999 - 0.2, 0.0, 28.0, 1186.9999999999964, 433.59999999999894, 1159.5000000000023 - 0.25, 0.0, 28.0, 1182.2000000000012, 379.69999999999965, 1139.7999999999952 -0.30000000000000004, 0.0, 28.0, 1176.0999999999988, 326.6000000000004, 1116.1999999999994 -0.35000000000000003, 0.0, 28.0, 1169.1999999999994, 274.8000000000004, 1088.9000000000017 - 0.4, 0.0, 28.0, 1160.6999999999969, 224.30000000000058, 1058.000000000005 - 0.45, 0.0, 28.0, 1150.100000000001, 174.8999999999994, 1023.900000000005 - 0.5, 0.0, 28.0, 1138.2000000000016, 127.0999999999993, 987.0000000000101 - 0.55, 0.0, 28.0, 1125.8000000000018, 81.39999999999979, 947.7000000000164 - 0.6000000000000001, 0.0, 28.0, 1113.700000000002, 38.30000000000135, 906.4000000000234 - 0.65, 0.0, 28.0, 1102.7000000000025, -1.6999999999956197, 863.5000000000305 - 0.7000000000000001, 0.0, 28.0, 1093.6000000000015, -38.099999999990914, 819.4000000000376 - 0.75, 0.0, 28.0, 1087.2000000000007, -70.39999999998402, 774.5000000000434 - 0.8, 0.0, 28.0, 1084.2999999999981, -98.09999999997468, 729.2000000000479 - 0.0, 0.0, 30.0, 1588.8999999999996, 684.8000000000001, 1353.7999999999993 - 0.05, 0.0, 30.0, 1589.4999999999993, 630.3999999999978, 1351.7999999999934 - 0.1, 0.0, 30.0, 1588.7000000000019, 575.8999999999962, 1345.0999999999865 -0.15000000000000002, 0.0, 30.0, 1586.4999999999966, 521.499999999999, 1333.6999999999996 - 0.2, 0.0, 30.0, 1582.5999999999922, 467.4999999999981, 1317.8000000000077 - 0.25, 0.0, 30.0, 1576.1999999999996, 413.69999999999874, 1297.1999999999828 -0.30000000000000004, 0.0, 30.0, 1568.1999999999978, 360.90000000000094, 1272.6000000000001 -0.35000000000000003, 0.0, 30.0, 1558.9999999999955, 309.4000000000007, 1244.0000000000045 - 0.4, 0.0, 30.0, 1547.699999999982, 259.2000000000002, 1211.8000000000125 - 0.45, 0.0, 30.0, 1533.6000000000042, 210.0999999999986, 1175.9000000000117 - 0.5, 0.0, 30.0, 1517.600000000001, 162.4999999999988, 1136.900000000023 - 0.55, 0.0, 30.0, 1500.5999999999913, 116.80000000000094, 1095.4000000000356 - 0.6000000000000001, 0.0, 30.0, 1483.4999999999702, 73.40000000000593, 1052.0000000000464 - 0.65, 0.0, 30.0, 1467.1999999999348, 32.7000000000148, 1007.3000000000532 - 0.7000000000000001, 0.0, 30.0, 1452.599999999881, -4.8999999999716835, 961.9000000000542 - 0.75, 0.0, 30.0, 1440.5999999998055, -38.999999999952564, 916.400000000046 - 0.8, 0.0, 30.0, 1432.0999999997046, -69.19999999992686, 871.400000000027 - 0.0, 0.0, 32.0, 1986.100000000001, 717.6999999999996, 1513.600000000001 - 0.05, 0.0, 32.0, 1986.9000000000042, 663.4000000000009, 1511.6000000000063 - 0.1, 0.0, 32.0, 1985.9000000000055, 609.1000000000029, 1504.7000000000212 -0.15000000000000002, 0.0, 32.0, 1983.0999999999956, 554.9000000000004, 1492.9999999999945 - 0.2, 0.0, 32.0, 1978.299999999995, 501.10000000000264, 1476.5999999999874 - 0.25, 0.0, 32.0, 1970.200000000027, 447.4999999999964, 1455.2000000000214 -0.30000000000000004, 0.0, 32.0, 1960.1999999999966, 394.9000000000022, 1429.5000000000084 -0.35000000000000003, 0.0, 32.0, 1948.699999999988, 343.7999999999993, 1399.8000000000038 - 0.4, 0.0, 32.0, 1934.599999999947, 293.8999999999996, 1366.1000000000142 - 0.45, 0.0, 32.0, 1916.9000000000524, 245.00000000000563, 1328.4000000000326 - 0.5, 0.0, 32.0, 1897.0000000001098, 198.20000000001303, 1288.8000000000757 - 0.55, 0.0, 32.0, 1876.3000000001823, 154.60000000002424, 1249.4000000001347 - 0.6000000000000001, 0.0, 32.0, 1856.2000000002672, 115.30000000003959, 1212.30000000021 - 0.65, 0.0, 32.0, 1838.1000000003596, 81.40000000005975, 1179.6000000003005 - 0.7000000000000001, 0.0, 32.0, 1823.4000000004567, 54.00000000008495, 1153.4000000004041 - 0.75, 0.0, 32.0, 1813.5000000005543, 34.20000000011595, 1135.8000000005218 - 0.8, 0.0, 32.0, 1809.8000000006484, 23.100000000153102, 1128.9000000006508 - 0.0, 0.0, 34.0, 2383.2999999999993, 750.4000000000004, 1674.2 - 0.05, 0.0, 34.0, 2384.199999999992, 696.2999999999997, 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1.0, 7569.300000000063, 1041.1999999999748, 3625.400000000015 + 0.8, 35000.0, 0.52, 1528.2000000000012, 248.2000000000001, 1218.200000000001 + 0.8, 35000.0, 0.56, 2292.200000000004, 351.900000000004, 1503.1000000000101 + 0.8, 35000.0, 0.6, 3056.300000000028, 455.2000000000091, 1790.8000000000047 + 0.8, 35000.0, 0.64, 3820.0999999998994, 558.400000000001, 2081.7999999999674 + 0.8, 35000.0, 0.68, 4584.1999999998825, 661.6000000000024, 2376.7000000000335 + 0.8, 35000.0, 0.72, 5348.299999999879, 765.2000000000007, 2675.7999999999124 + 0.8, 35000.0, 0.76, 6112.400000000117, 875.899999999998, 2992.099999999943 + 0.8, 35000.0, 0.8, 6876.399999999898, 988.5000000000006, 3317.199999999918 + 0.8, 35000.0, 0.84, 7317.391999999944, 1056.118857142862, 3512.3440000000082 + 0.8, 35000.0, 0.88, 7557.551999999866, 1095.667428571431, 3626.7240000000224 + 0.8, 35000.0, 0.92, 7775.856000000067, 1131.5008000000068, 3731.5071999999577 + 0.8, 35000.0, 0.96, 8037.680000000124, 1173.0856000000133, 3853.91039999994 + 0.8, 35000.0, 1.0, 8294.80000000019, 1215.0000000000227, 3977.199999999917 diff --git a/aviary/models/large_turboprop_freighter/large_turboprop_freighter.csv b/aviary/models/large_turboprop_freighter/large_turboprop_freighter.csv new file mode 100644 index 000000000..a60b2ab4b --- /dev/null +++ b/aviary/models/large_turboprop_freighter/large_turboprop_freighter.csv @@ -0,0 +1,249 @@ +# GASP-derived aircraft input deck converted from large_turboprop_freighter.dat + +# Input Values +aircraft:air_conditioning:mass_coefficient, 2.65, unitless +aircraft:anti_icing:mass, 644, lbm +aircraft:apu:mass, 756, lbm +aircraft:avionics:mass, 936, lbm +aircraft:controls:cockpit_control_mass_scaler, 1, unitless +aircraft:controls:control_mass_increment, 0, lbm +aircraft:controls:stability_augmentation_system_mass, 0, lbm +aircraft:controls:stability_augmentation_system_mass_scaler, 1, unitless +aircraft:crew_and_payload:cargo_mass, 31273, lbm +aircraft:crew_and_payload:catering_items_mass_per_passenger, 0, lbm +aircraft:crew_and_payload:num_passengers, 60, unitless +aircraft:crew_and_payload:passenger_mass_with_bags, 190, lbm +aircraft:crew_and_payload:passenger_service_mass_per_passenger, 0, lbm +aircraft:crew_and_payload:water_mass_per_occupant, 0, lbm +aircraft:design:cg_delta, 0.25, unitless +aircraft:design:cockpit_control_mass_coefficient, 20, unitless +aircraft:design:drag_increment, 0.0015, unitless +aircraft:design:emergency_equipment_mass, 25, lbm +aircraft:design:max_structural_speed, 320, mi/h +aircraft:design:part25_structural_category, 3, unitless +aircraft:design:reserve_fuel_additional, 0.667, lbm +aircraft:design:static_margin, 0.05, unitless +aircraft:design:structural_mass_increment, 0, lbm +aircraft:design:supercritical_drag_shift, 0, unitless +aircraft:engine:additional_mass_fraction, 0.34, unitless +aircraft:engine:mass_scaler, 1, unitless +aircraft:engine:mass_specific, 0.37026, lbm/lbf +aircraft:engine:num_engines, 4, unitless +aircraft:engine:data_file, models/engines/turboshaft_4465hp.deck +aircraft:engine:pod_mass_scaler, 1, unitless +aircraft:engine:pylon_factor, 0.7, unitless +aircraft:engine:reference_diameter, 5.8, ft +aircraft:engine:reference_sls_thrust, 28690, lbf +aircraft:engine:scaled_sls_thrust, 28690, lbf +aircraft:engine:type, 6, unitless +aircraft:engine:wing_locations, [0.385, 0.385], unitless +aircraft:engine:propeller_diameter, 13.5, ft +aircraft:engine:num_propeller_blades, 4, unitless +aircraft:engine:propeller_activity_factor, 167, unitless +aircraft:engine:propeller_tip_speed_max, 720, ft/s +# aircraft:engine:gearbox:gear_ratio, 13.53, unitless +aircraft:engine:fixed_rpm, 1019, rpm +aircraft:fuel:density, 6.687, lbm/galUS +aircraft:fuel:fuel_margin, 15, unitless +aircraft:fuel:fuel_system_mass_coefficient, 0.065, unitless +aircraft:fuel:fuel_system_mass_scaler, 1, unitless +aircraft:fuel:unusable_fuel_mass_coefficient, 4.5, unitless +aircraft:fuel:wing_fuel_fraction, 0.324, unitless +aircraft:furnishings:mass, 0, lbm +aircraft:fuselage:aisle_width, 48.8, inch +aircraft:fuselage:delta_diameter, 5, ft +aircraft:fuselage:flat_plate_area_increment, 2, ft**2 +aircraft:fuselage:form_factor, -1, unitless +aircraft:fuselage:mass_coefficient, 145.87, unitless +aircraft:fuselage:nose_fineness, 1, unitless +aircraft:fuselage:num_aisles, 1, unitless +aircraft:fuselage:num_seats_abreast, 6, unitless +aircraft:fuselage:pilot_compartment_length, 10.6, ft +aircraft:fuselage:pressure_differential, 6.55, psi +aircraft:fuselage:seat_pitch, 41.24, inch +aircraft:fuselage:seat_width, 18, inch +aircraft:fuselage:tail_fineness, 2.9, unitless +aircraft:fuselage:wetted_area_factor, 1, unitless +aircraft:horizontal_tail:area, 0, ft**2 +aircraft:horizontal_tail:aspect_ratio, 6.03, unitless +aircraft:horizontal_tail:form_factor, -1, unitless +aircraft:horizontal_tail:mass_coefficient, 0.2285, unitless +aircraft:horizontal_tail:moment_ratio, 0.3061, unitless +aircraft:horizontal_tail:sweep, 0, deg +aircraft:horizontal_tail:taper_ratio, 0.374, unitless +aircraft:horizontal_tail:thickness_to_chord, 0.15, unitless +aircraft:horizontal_tail:vertical_tail_fraction, 0, unitless +aircraft:horizontal_tail:volume_coefficient, 0.8614, unitless +aircraft:hydraulics:flight_control_mass_coefficient, 0.102, unitless +aircraft:hydraulics:gear_mass_coefficient, 0.11, unitless +aircraft:instruments:mass_coefficient, 0.0416, unitless +aircraft:landing_gear:fixed_gear, True, unitless +aircraft:landing_gear:main_gear_location, 0, unitless +aircraft:landing_gear:main_gear_mass_coefficient, 0.916, unitless +aircraft:landing_gear:mass_coefficient, 0.0337, unitless +aircraft:landing_gear:tail_hook_mass_scaler, 1, unitless +aircraft:landing_gear:total_mass_scaler, 1, unitless +aircraft:nacelle:clearance_ratio, 0.2, unitless +aircraft:nacelle:core_diameter_ratio, 1.15, unitless +aircraft:nacelle:fineness, 0.38, unitless +aircraft:nacelle:form_factor, -1, unitless +aircraft:nacelle:mass_specific, 3, lbm/ft**2 +aircraft:strut:area_ratio, 0, unitless +aircraft:strut:attachment_location, 0, ft +aircraft:strut:attachment_location_dimensionless, 0, unitless +aircraft:strut:dimensional_location_specified, False, unitless +aircraft:strut:fuselage_interference_factor, 0, unitless +aircraft:strut:mass_coefficient, 0, unitless +aircraft:vertical_tail:area, 0, ft**2 +aircraft:vertical_tail:aspect_ratio, 1.81, unitless +aircraft:vertical_tail:form_factor, -1, unitless +aircraft:vertical_tail:mass_coefficient, 0.2035, unitless +aircraft:vertical_tail:moment_ratio, 2.809, unitless +aircraft:vertical_tail:sweep, 0, deg +aircraft:vertical_tail:taper_ratio, 0.296, unitless +aircraft:vertical_tail:thickness_to_chord, 0.15, unitless +aircraft:vertical_tail:volume_coefficient, 0.05355, unitless +aircraft:wing:aspect_ratio, 10.078, unitless +aircraft:wing:center_distance, 0.45, unitless +aircraft:wing:choose_fold_location, True, unitless +aircraft:wing:flap_chord_ratio, 0.28, unitless +aircraft:wing:flap_deflection_landing, 15, deg +aircraft:wing:flap_deflection_takeoff, 10, deg +aircraft:wing:flap_drag_increment_optimum, 0.23, unitless +aircraft:wing:flap_lift_increment_optimum, 1.4, unitless +aircraft:wing:flap_span_ratio, 0.6, unitless +aircraft:wing:flap_type, double_slotted, unitless +aircraft:wing:fold_dimensional_location_specified, False, unitless +aircraft:wing:fold_mass_coefficient, 0, unitless +aircraft:wing:folded_span, 0, ft +aircraft:wing:form_factor, -1, unitless +aircraft:wing:fuselage_interference_factor, 1, unitless +aircraft:wing:has_fold, False, unitless +aircraft:wing:has_strut, False, unitless +aircraft:wing:height, 14.5, ft +aircraft:wing:high_lift_mass_coefficient, 1.2, unitless +aircraft:wing:incidence, 2, deg +aircraft:wing:loading, 88.846, lbf/ft**2 +aircraft:wing:mass_coefficient, 131.32, unitless +aircraft:wing:max_lift_ref, 1.5, unitless +aircraft:wing:max_slat_deflection_landing, 0, deg +aircraft:wing:max_slat_deflection_takeoff, 0, deg +aircraft:wing:max_thickness_location, 0.35, unitless +aircraft:wing:min_pressure_location, 0.3, unitless +aircraft:wing:mounting_type, 1, unitless +aircraft:wing:num_flap_segments, 2, unitless +aircraft:wing:optimum_flap_deflection, 55, deg +aircraft:wing:optimum_slat_deflection, 45, deg +aircraft:wing:slat_chord_ratio, 0, unitless +aircraft:wing:slat_lift_increment_optimum, 0.93, unitless +aircraft:wing:slat_span_ratio, 0.9, unitless +aircraft:wing:surface_ctrl_mass_coefficient, 0.588, unitless +aircraft:wing:sweep, 0, deg +aircraft:wing:taper_ratio, 0.52, unitless +aircraft:wing:thickness_to_chord_root, 0.18, unitless +aircraft:wing:thickness_to_chord_tip, 0.12, unitless +aircraft:wing:zero_lift_angle, -1, deg +mission:design:cruise_altitude, 21000, ft +mission:design:gross_mass, 155000, lbm +mission:design:mach, 0.475, unitless +mission:design:range, 0, NM +mission:design:rate_of_climb_at_top_of_climb, 300, ft/min +mission:landing:airport_altitude, 0, ft +mission:landing:braking_delay, 2, s +mission:landing:glide_to_stall_ratio, 1.3, unitless +mission:landing:maximum_flare_load_factor, 1.15, unitless +mission:landing:maximum_sink_rate, 900, ft/min +mission:landing:obstacle_height, 50, ft +mission:landing:touchdown_sink_rate, 5, ft/s +mission:summary:fuel_flow_scaler, 1, unitless +mission:takeoff:decision_speed_increment, 5, kn +mission:takeoff:rotation_speed_increment, 5, kn +mission:taxi:duration, 0.15, h +settings:problem_type, fallout, unitless +settings:equations_of_motion, 2DOF +settings:mass_method, GASP + +mission:constraints:max_mach, 0.5, unitless + +# Initial Guesses +actual_takeoff_mass, 0 +climb_range, 0 +cruise_mass_final, 0 +flight_duration, 0 +fuel_burn_per_passenger_mile, 0.1 +reserves, 0 +rotation_mass, 0.99 +time_to_climb, 0 + +# Unconverted Values +INGASP.ACDCDR, 1, 1, 1, 1, 1.15, 1.392, 1.7855, 3.5714, 5.36 +INGASP.ACLS, 0, 0.4, 0.6, 0.8, 1, 1.2, 1.4, 1.6, 1.8 +INGASP.BENGOB, 0.05 +INGASP.CK10, 1 +INGASP.CK11, 1 +INGASP.CK18, 1 +INGASP.CK7, 1 +INGASP.CK8, 1 +INGASP.CK9, 1 +INGASP.CW, , 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 5, 0 +INGASP.DCDSE, 0 +INGASP.EMCRU, 0.475 +INGASP.HNCRU, 21000 +INGASP.HPORT, 0 +INGASP.HSCREQ, 10000 +INGASP.HTMAX, 400 +INGASP.ICLM, 1 +INGASP.ICRUS, 0 +INGASP.IFERRY, 0 +INGASP.IPART, 1 +INGASP.ISWING, 0 +INGASP.IWLD, 2 +INGASP.JENGSZ, 2 +INGASP.KNAC, 1 +INGASP.KWCD, 9 +INGASP.LCWING, 0 +INGASP.MX, 0 +INGASP.NFAIL, 0 +INGASP.RCCRU, 10 +INGASP.RELP, 0 +INGASP.RELR, 0.4 +INGASP.RF, 3, 100, 10000, 1500, 4, 5, 0, 1 +INGASP.ROSCAB, 500 +INGASP.RWCRTX, 0.985 +INGASP.SKPES, 0.335 +INGASP.TBO, 0 +INGASP.TDELLD, 0 +INGASP.TDELTO, 0 +INGASP.TDELTX, 0 +INGASP.TIDLE, 200 +INGASP.VCLMB, 180 +INGASP.VRAT, 1.15 +INGASP.WLPCT, 0.976 +INGASP.WPLX, 25000 +INGASP.XLFMAX, 1.2 +INGASP.XTORQ, 4500 +INPROP.AF, 167 +INPROP.ANCQHP, 0.03405 +INPROP.BL, 4 +INPROP.BLANG, 0 +INPROP.CLI, 0.5 +INPROP.CTI, 0.2 +INPROP.DIST, 1000 +INPROP.DPROP, 13.5 +INPROP.GR, 0.0738 +INPROP.HNOYS, 1000 +INPROP.HPMSLS, 4465 +INPROP.IDATE, 1980 +INPROP.JSIZE, 1 +INPROP.KNOYS, -1 +INPROP.KODECR, 7 +INPROP.KODETH, 6 +INPROP.NTYP, 5 +INPROP.PCLER, 0.1724 +INPROP.PCNCCL, 1.0228 +INPROP.PCNCCR, 1.05357 +INPROP.PCNCTO, 1 +INPROP.TSPDMX, 720 +INPROP.WKPFAC, 1.1 +INPROP.WPROP1, 4500 +INPROP.XNMAX, 13820 \ No newline at end of file diff --git a/aviary/models/large_turboprop_freighter/phase_info.py b/aviary/models/large_turboprop_freighter/phase_info.py new file mode 100644 index 000000000..660a85f53 --- /dev/null +++ b/aviary/models/large_turboprop_freighter/phase_info.py @@ -0,0 +1,362 @@ +from aviary.variable_info.enums import SpeedType + +# Energy method +# phase_info = { +# "pre_mission": {"include_takeoff": False, "optimize_mass": True}, +# "climb": { +# "subsystem_options": {"core_aerodynamics": {"method": "solved_alpha"}}, +# "user_options": { +# "optimize_mach": False, +# "optimize_altitude": False, +# "num_segments": 5, +# "order": 3, +# "solve_for_distance": False, +# "initial_mach": (0.2, "unitless"), +# "final_mach": (0.475, "unitless"), +# "mach_bounds": ((0.08, 0.478), "unitless"), +# "initial_altitude": (0.0, "ft"), +# "final_altitude": (21_000.0, "ft"), +# "altitude_bounds": ((0.0, 22_000.0), "ft"), +# "throttle_enforcement": "path_constraint", +# "fix_initial": True, +# "constrain_final": False, +# "fix_duration": False, +# "initial_bounds": ((0.0, 0.0), "min"), +# "duration_bounds": ((24.0, 192.0), "min"), +# "add_initial_mass_constraint": False, +# }, +# }, +# "cruise": { +# "subsystem_options": {"core_aerodynamics": {"method": "solved_alpha"}}, +# "user_options": { +# "optimize_mach": False, +# "optimize_altitude": False, +# "num_segments": 5, +# "order": 3, +# "solve_for_distance": False, +# "initial_mach": (0.475, "unitless"), +# "final_mach": (0.475, "unitless"), +# "mach_bounds": ((0.47, 0.48), "unitless"), +# "initial_altitude": (21_000.0, "ft"), +# "final_altitude": (21_000.0, "ft"), +# "altitude_bounds": ((20_000.0, 22_000.0), "ft"), +# "throttle_enforcement": "boundary_constraint", +# "fix_initial": False, +# "constrain_final": False, +# "fix_duration": False, +# "initial_bounds": ((64.0, 192.0), "min"), +# "duration_bounds": ((56.5, 169.5), "min"), +# }, +# }, +# "descent": { +# "subsystem_options": {"core_aerodynamics": {"method": "solved_alpha"}}, +# "user_options": { +# "optimize_mach": False, +# "optimize_altitude": False, +# "num_segments": 5, +# "order": 3, +# "solve_for_distance": False, +# "initial_mach": (0.475, "unitless"), +# "final_mach": (0.1, "unitless"), +# "mach_bounds": ((0.08, 0.48), "unitless"), +# "initial_altitude": (21_000.0, "ft"), +# "final_altitude": (500.0, "ft"), +# "altitude_bounds": ((0.0, 22_000.0), "ft"), +# "throttle_enforcement": "path_constraint", +# "fix_initial": False, +# "constrain_final": True, +# "fix_duration": False, +# "initial_bounds": ((100, 361.5), "min"), +# "duration_bounds": ((29.0, 87.0), "min"), +# }, +# }, +# "post_mission": { +# "include_landing": False, +# "constrain_range": True, +# "target_range": (2_020., "nmi"), +# }, +# } + +# 2DOF +phase_info = { + 'groundroll': { + 'user_options': { + 'num_segments': 1, + 'order': 3, + 'connect_initial_mass': False, + 'fix_initial': True, + 'fix_initial_mass': False, + 'duration_ref': (50.0, 's'), + 'duration_bounds': ((1.0, 100.0), 's'), + 'velocity_lower': (0, 'kn'), + 'velocity_upper': (1000, 'kn'), + 'velocity_ref': (150, 'kn'), + 'mass_lower': (0, 'lbm'), + 'mass_upper': (None, 'lbm'), + 'mass_ref': (150_000, 'lbm'), + 'mass_defect_ref': (150_000, 'lbm'), + 'distance_lower': (0, 'ft'), + 'distance_upper': (10.0e3, 'ft'), + 'distance_ref': (3000, 'ft'), + 'distance_defect_ref': (3000, 'ft'), + }, + 'initial_guesses': { + 'time': ([0.0, 40.0], 's'), + 'velocity': ([0.066, 143.1], 'kn'), + 'distance': ([0.0, 1000.0], 'ft'), + 'throttle': ([0.956, 0.956], 'unitless'), + }, + }, + 'rotation': { + 'user_options': { + 'num_segments': 1, + 'order': 3, + 'fix_initial': False, + 'duration_bounds': ((1, 100), 's'), + 'duration_ref': (50.0, 's'), + 'velocity_lower': (0, 'kn'), + 'velocity_upper': (1000, 'kn'), + 'velocity_ref': (100, 'kn'), + 'velocity_ref0': (0, 'kn'), + 'mass_lower': (0, 'lbm'), + 'mass_upper': (None, 'lbm'), + 'mass_ref': (150_000, 'lbm'), + 'mass_defect_ref': (150_000, 'lbm'), + 'distance_lower': (0, 'ft'), + 'distance_upper': (10_000, 'ft'), + 'distance_ref': (5000, 'ft'), + 'distance_defect_ref': (5000, 'ft'), + 'angle_lower': (0.0, 'rad'), + 'angle_upper': (5.0, 'rad'), + 'angle_ref': (5.0, 'rad'), + 'angle_defect_ref': (5.0, 'rad'), + 'normal_ref': (10000, 'lbf'), + }, + 'initial_guesses': { + 'time': ([40.0, 5.0], 's'), + 'alpha': ([0.0, 2.5], 'deg'), + 'velocity': ([143, 150.0], 'kn'), + 'distance': ([3680.37217765, 4000], 'ft'), + 'throttle': ([0.956, 0.956], 'unitless'), + }, + }, + 'ascent': { + 'user_options': { + 'num_segments': 4, + 'order': 3, + 'fix_initial': False, + 'velocity_lower': (0, 'kn'), + 'velocity_upper': (700, 'kn'), + 'velocity_ref': (200, 'kn'), + 'velocity_ref0': (0, 'kn'), + 'mass_lower': (0, 'lbm'), + 'mass_upper': (None, 'lbm'), + 'mass_ref': (150_000, 'lbm'), + 'mass_defect_ref': (150_000, 'lbm'), + 'distance_lower': (0, 'ft'), + 'distance_upper': (15_000, 'ft'), + 'distance_ref': (1e4, 'ft'), + 'distance_defect_ref': (1e4, 'ft'), + 'alt_lower': (0, 'ft'), + 'alt_upper': (700, 'ft'), + 'alt_ref': (1000, 'ft'), + 'alt_defect_ref': (1000, 'ft'), + 'final_altitude': (500, 'ft'), + 'alt_constraint_ref': (500, 'ft'), + 'angle_lower': (-10, 'rad'), + 'angle_upper': (20, 'rad'), + 'angle_ref': (57.2958, 'deg'), + 'angle_defect_ref': (57.2958, 'deg'), + 'pitch_constraint_lower': (0.0, 'deg'), + 'pitch_constraint_upper': (15.0, 'deg'), + 'pitch_constraint_ref': (1.0, 'deg'), + }, + 'initial_guesses': { + 'time': ([45.0, 25.0], 's'), + 'flight_path_angle': ([0.0, 8.0], 'deg'), + 'alpha': ([2.5, 1.5], 'deg'), + 'velocity': ([150.0, 185.0], 'kn'), + 'distance': ([4.0e3, 10.0e3], 'ft'), + 'altitude': ([0.0, 500.0], 'ft'), + 'tau_gear': (0.2, 'unitless'), + 'tau_flaps': (0.9, 'unitless'), + 'throttle': ([0.956, 0.956], 'unitless'), + }, + }, + 'accel': { + 'user_options': { + 'num_segments': 1, + 'order': 3, + 'fix_initial': False, + 'alt': (500, 'ft'), + 'EAS_constraint_eq': (250, 'kn'), + 'duration_bounds': ((1, 200), 's'), + 'duration_ref': (1000, 's'), + 'velocity_lower': (150, 'kn'), + 'velocity_upper': (270, 'kn'), + 'velocity_ref': (250, 'kn'), + 'velocity_ref0': (150, 'kn'), + 'mass_lower': (0, 'lbm'), + 'mass_upper': (None, 'lbm'), + 'mass_ref': (150_000, 'lbm'), + 'mass_defect_ref': (150_000, 'lbm'), + 'distance_lower': (0, 'NM'), + 'distance_upper': (150, 'NM'), + 'distance_ref': (5, 'NM'), + 'distance_defect_ref': (5, 'NM'), + }, + 'initial_guesses': { + 'time': ([70.0, 13.0], 's'), + 'velocity': ([185.0, 250.0], 'kn'), + 'distance': ([10.0e3, 20.0e3], 'ft'), + 'throttle': ([0.956, 0.956], 'unitless'), + }, + }, + 'climb1': { + 'user_options': { + 'num_segments': 1, + 'order': 3, + 'fix_initial': False, + 'EAS_target': (150, 'kn'), + 'mach_cruise': 0.475, + 'target_mach': False, + 'final_altitude': (10.0e3, 'ft'), + 'duration_bounds': ((30, 300), 's'), + 'duration_ref': (1000, 's'), + 'alt_lower': (400, 'ft'), + 'alt_upper': (11_000, 'ft'), + 'alt_ref': (10.0e3, 'ft'), + 'mass_lower': (0, 'lbm'), + 'mass_upper': (None, 'lbm'), + 'mass_ref': (150_000, 'lbm'), + 'mass_defect_ref': (150_000, 'lbm'), + 'distance_lower': (0, 'NM'), + 'distance_upper': (500, 'NM'), + 'distance_ref': (10, 'NM'), + 'distance_ref0': (0, 'NM'), + }, + 'initial_guesses': { + 'time': ([1.0, 2.0], 'min'), + 'distance': ([20.0e3, 100.0e3], 'ft'), + 'altitude': ([500.0, 10.0e3], 'ft'), + 'throttle': ([0.956, 0.956], 'unitless'), + }, + }, + 'climb2': { + 'user_options': { + 'num_segments': 3, + 'order': 3, + 'fix_initial': False, + 'EAS_target': (160, 'kn'), + 'mach_cruise': 0.475, + 'target_mach': True, + 'final_altitude': (21_000, 'ft'), + 'required_available_climb_rate': (0.1, 'ft/min'), + 'duration_bounds': ((200, 17_000), 's'), + 'duration_ref': (5000, 's'), + 'alt_lower': (9000, 'ft'), + 'alt_upper': (22_000, 'ft'), + 'alt_ref': (20_000, 'ft'), + 'alt_ref0': (0, 'ft'), + 'mass_lower': (0, 'lbm'), + 'mass_upper': (None, 'lbm'), + 'mass_ref': (150_000, 'lbm'), + 'mass_defect_ref': (150_000, 'lbm'), + 'distance_lower': (10, 'NM'), + 'distance_upper': (1000, 'NM'), + 'distance_ref': (500, 'NM'), + 'distance_ref0': (0, 'NM'), + 'distance_defect_ref': (500, 'NM'), + }, + 'initial_guesses': { + 'time': ([216.0, 1300.0], 's'), + 'distance': ([100.0e3, 200.0e3], 'ft'), + 'altitude': ([10_000, 20_000], 'ft'), + 'throttle': ([0.956, 0.956], 'unitless'), + }, + }, + 'cruise': { + 'user_options': { + 'alt_cruise': (21_000, 'ft'), + 'mach_cruise': 0.475, + }, + 'initial_guesses': { + # [Initial mass, delta mass] for special cruise phase. + 'mass': ([150_000.0, -35_000], 'lbm'), + 'initial_distance': (100.0e3, 'ft'), + 'initial_time': (1_000.0, 's'), + 'altitude': (21_000, 'ft'), + 'mach': (0.475, 'unitless'), + }, + }, + 'desc1': { + 'user_options': { + 'num_segments': 3, + 'order': 3, + 'fix_initial': False, + 'input_initial': False, + 'EAS_limit': (160, 'kn'), + 'mach_cruise': 0.475, + 'input_speed_type': SpeedType.MACH, + 'final_altitude': (10_000, 'ft'), + 'duration_bounds': ((300.0, 900.0), 's'), + 'duration_ref': (1000, 's'), + 'alt_lower': (1000, 'ft'), + 'alt_upper': (22_000, 'ft'), + 'alt_ref': (20_000, 'ft'), + 'alt_ref0': (0, 'ft'), + 'alt_constraint_ref': (10000, 'ft'), + 'mass_lower': (0, 'lbm'), + 'mass_upper': (None, 'lbm'), + 'mass_ref': (140_000, 'lbm'), + 'mass_ref0': (0, 'lbm'), + 'mass_defect_ref': (140_000, 'lbm'), + 'distance_lower': (1_000.0, 'NM'), + 'distance_upper': (3_000.0, 'NM'), + 'distance_ref': (2_020, 'NM'), + 'distance_ref0': (0, 'NM'), + 'distance_defect_ref': (100, 'NM'), + }, + 'initial_guesses': { + 'mass': (136000.0, 'lbm'), + 'altitude': ([20_000, 10_000], 'ft'), + 'throttle': ([0.0, 0.0], 'unitless'), + 'distance': ([0.92 * 2_020, 0.96 * 2_020], 'NM'), + 'time': ([28000.0, 500.0], 's'), + }, + }, + 'desc2': { + 'user_options': { + 'num_segments': 1, + 'order': 7, + 'fix_initial': False, + 'input_initial': False, + 'EAS_limit': (250, 'kn'), + 'mach_cruise': 0.80, + 'input_speed_type': SpeedType.EAS, + 'final_altitude': (1000, 'ft'), + 'duration_bounds': ((100.0, 5000), 's'), + 'duration_ref': (500, 's'), + 'alt_lower': (500, 'ft'), + 'alt_upper': (11_000, 'ft'), + 'alt_ref': (10.0e3, 'ft'), + 'alt_ref0': (1000, 'ft'), + 'alt_constraint_ref': (1000, 'ft'), + 'mass_lower': (0, 'lbm'), + 'mass_upper': (None, 'lbm'), + 'mass_ref': (150_000, 'lbm'), + 'mass_defect_ref': (150_000, 'lbm'), + 'distance_lower': (0, 'NM'), + 'distance_upper': (5000, 'NM'), + 'distance_ref': (3500, 'NM'), + 'distance_defect_ref': (100, 'NM'), + }, + 'initial_guesses': { + 'mass': (136000.0, 'lbm'), + 'altitude': ([10.0e3, 1.0e3], 'ft'), + 'throttle': ([0.0, 0.0], 'unitless'), + 'distance': ([0.96 * 2_020, 2_020], 'NM'), + 'time': ([28500.0, 500.0], 's'), + }, + }, +} diff --git a/aviary/models/large_turboprop_freighter/test_bench_large_turboprop_freighter.py b/aviary/models/large_turboprop_freighter/test_bench_large_turboprop_freighter.py new file mode 100644 index 000000000..cfd330d1d --- /dev/null +++ b/aviary/models/large_turboprop_freighter/test_bench_large_turboprop_freighter.py @@ -0,0 +1,59 @@ +import numpy as np +import unittest + +from numpy.testing import assert_almost_equal +from openmdao.utils.testing_utils import use_tempdirs + +from aviary.interface.methods_for_level2 import AviaryProblem +from aviary.subsystems.propulsion.turboprop_model import TurbopropModel +from aviary.utils.process_input_decks import create_vehicle +from aviary.variable_info.variables import Aircraft, Mission, Settings + +from aviary.models.large_turboprop_freighter.phase_info import phase_info + + +@use_tempdirs +@unittest.skip("Skipping until all builders are updated with get_parameters()") +# TODO need to add asserts with "truth" values +class LargeTurbopropFreighterBenchmark(unittest.TestCase): + + def build_and_run_problem(self): + + # Build problem + prob = AviaryProblem() + + # load inputs from .csv to build engine + options, _ = create_vehicle( + "models/large_turboprop_freighter/large_turboprop_freighter.csv" + ) + + turboprop = TurbopropModel('turboprop', options=options) + + # load_inputs needs to be updated to accept an already existing aviary options + prob.load_inputs( + "models/large_turboprop_freighter/large_turboprop_freighter.csv", + phase_info, + engine_builders=[turboprop], + ) + + # FLOPS aero specific stuff? Best guesses for values here + # prob.aviary_inputs.set_val(Mission.Constraints.MAX_MACH, 0.5) + # prob.aviary_inputs.set_val(Aircraft.Fuselage.AVG_DIAMETER, 4.125, 'm') + + prob.check_and_preprocess_inputs() + prob.add_pre_mission_systems() + prob.add_phases() + prob.add_post_mission_systems() + prob.link_phases() + prob.add_driver("SLSQP", max_iter=0, verbosity=0) + prob.add_design_variables() + prob.add_objective() + prob.setup() + prob.set_initial_guesses() + + prob.run_aviary_problem("dymos_solution.db", make_plots=False) + + +if __name__ == '__main__': + test = LargeTurbopropFreighterBenchmark() + test.build_and_run_problem() diff --git a/aviary/sizing_problem.json b/aviary/sizing_problem.json new file mode 100644 index 000000000..419e44243 --- /dev/null +++ b/aviary/sizing_problem.json @@ -0,0 +1,1307 @@ +[ + [ + "aircraft:blended_wing_body_design:num_bays", + 0, + "unitless", + "" + ], + [ + "aircraft:crew_and_payload:mass_per_passenger", + 180, + "lbm", + "" + ], + [ + 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"aircraft:fuel:auxiliary_fuel_capacity", + 0, + "lbm", + "" + ], + [ + "aircraft:fuel:density_ratio", + 1, + "unitless", + "" + ], + [ + "aircraft:fuel:fuel_system_mass_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:fuel:fuselage_fuel_capacity", + 0, + "lbm", + "" + ], + [ + "aircraft:fuel:total_capacity", + 45694, + "lbm", + "" + ], + [ + "aircraft:fuel:unusable_fuel_mass_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:furnishings:mass_scaler", + 1.1, + "unitless", + "" + ], + [ + "aircraft:fuselage:length", + 128, + "ft", + "" + ], + [ + "aircraft:fuselage:mass_scaler", + 1.05, + "unitless", + "" + ], + [ + "aircraft:fuselage:max_height", + 13.17, + "ft", + "" + ], + [ + "aircraft:fuselage:max_width", + 12.33, + "ft", + "" + ], + [ + "aircraft:fuselage:passenger_compartment_length", + 85.5, + "ft", + "" + ], + [ + "aircraft:fuselage:planform_area", + 1578.24, + "ft**2", + "" + ], + [ + "aircraft:fuselage:wetted_area_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:fuselage:wetted_area", + 4158.62, + "ft**2", + "" + ], + [ + "aircraft:horizontal_tail:area", + 355, + "ft**2", + "" + ], + [ + "aircraft:horizontal_tail:aspect_ratio", + 6, + "unitless", + "" + ], + [ + "aircraft:horizontal_tail:mass_scaler", + 1.2, + "unitless", + "" + ], + [ + "aircraft:horizontal_tail:taper_ratio", + 0.22, + "unitless", + "" + ], + [ + "aircraft:horizontal_tail:thickness_to_chord", + 0.125, + "unitless", + "" + ], + [ + "aircraft:horizontal_tail:vertical_tail_fraction", + 0, + "unitless", + "" + ], + [ + "aircraft:horizontal_tail:wetted_area_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:horizontal_tail:wetted_area", + 592.65, + "ft**2", + "" + ], + [ + "aircraft:hydraulics:mass_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:hydraulics:system_pressure", + 3000, + "psi", + "" + ], + [ + "aircraft:instruments:mass_scaler", + 1.25, + "unitless", + "" + ], + [ + "aircraft:landing_gear:main_gear_mass_scaler", + 1.1, + "unitless", + "" + ], + [ + "aircraft:landing_gear:main_gear_oleo_length", + 102, + "inch", + "" + ], + [ + "aircraft:landing_gear:nose_gear_mass_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:landing_gear:nose_gear_oleo_length", + 67, + "inch", + "" + ], + [ + "aircraft:nacelle:avg_diameter", + [ + 7.94 + ], + "ft", + "" + ], + [ + "aircraft:nacelle:avg_length", + [ + 12.3 + ], + "ft", + "" + ], + [ + "aircraft:nacelle:mass_scaler", + [ + 1.0 + ], + "unitless", + "" + ], + [ + "aircraft:nacelle:wetted_area_scaler", + [ + 1.0 + ], + "unitless", + "" + ], + [ + "aircraft:paint:mass_per_unit_area", + 0.037, + "lbm/ft**2", + "" + ], + [ + "aircraft:propulsion:engine_oil_mass_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:propulsion:misc_mass_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:vertical_tail:area", + 284, + "ft**2", + "" + ], + [ + "aircraft:vertical_tail:aspect_ratio", + 1.75, + "unitless", + "" + ], + [ + "aircraft:vertical_tail:mass_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:vertical_tail:taper_ratio", + 0.33, + "unitless", + "" + ], + [ + "aircraft:vertical_tail:thickness_to_chord", + 0.1195, + "unitless", + "" + ], + [ + "aircraft:vertical_tail:wetted_area_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:vertical_tail:wetted_area", + 581.13, + "ft**2", + "" + ], + [ + "aircraft:wing:aeroelastic_tailoring_factor", + 0, + "unitless", + "" + ], + [ + "aircraft:wing:area", + 1370, + "ft**2", + "" + ], + [ + "aircraft:wing:aspect_ratio", + 11.22091, + "unitless", + "" + ], + [ + "aircraft:wing:bending_mass_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:wing:chord_per_semispan", + [ + 0.31, + 0.23, + 0.084 + ], + "unitless", + "" + ], + [ + "aircraft:wing:composite_fraction", + 0.2, + "unitless", + "" + ], + [ + "aircraft:wing:control_surface_area", + 137, + "ft**2", + "" + ], + [ + "aircraft:wing:control_surface_area_ratio", + 0.1, + "unitless", + "" + ], + [ + "aircraft:wing:glove_and_bat", + 134, + "ft**2", + "" + ], + [ + "aircraft:wing:input_station_dist", + [ + 0, + 0.2759, + 0.9367 + ], + "unitless", + "" + ], + [ + "aircraft:wing:load_fraction", + 1, + "unitless", + "" + ], + [ + "aircraft:wing:load_path_sweep_dist", + [ + 0, + 22 + ], + "deg", + "" + ], + [ + "aircraft:wing:mass_scaler", + 1.23, + "unitless", + "" + ], + [ + "aircraft:wing:max_camber_at_70_semispan", + 0, + "unitless", + "" + ], + [ + "aircraft:wing:misc_mass_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:wing:shear_control_mass_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:wing:span", + 117.83, + "ft", + "" + ], + [ + "aircraft:wing:strut_bracing_factor", + 0, + "unitless", + "" + ], + [ + "aircraft:wing:surface_ctrl_mass_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:wing:sweep", + 25, + "deg", + "" + ], + [ + "aircraft:wing:taper_ratio", + 0.278, + "unitless", + "" + ], + [ + "aircraft:wing:thickness_to_chord_dist", + [ + 0.145, + 0.115, + 0.104 + ], + "unitless", + "" + ], + [ + "aircraft:wing:thickness_to_chord", + 0.13, + "unitless", + "" + ], + [ + "aircraft:wing:ultimate_load_factor", + 3.75, + "unitless", + "" + ], + [ + "aircraft:wing:var_sweep_mass_penalty", + 0, + "unitless", + "" + ], + [ + "aircraft:wing:wetted_area_scaler", + 1, + "unitless", + "" + ], + [ + "aircraft:wing:wetted_area", + 2396.56, + "ft**2", + "" + ], + [ + "mission:constraints:max_mach", + 0.785, + "unitless", + "" + ], + [ + "mission:design:gross_mass", + 175864.58080717592, + "lbm", + "" + ], + [ + "mission:design:range", + 3375.0, + "NM", + "" + ], + [ + "mission:design:thrust_takeoff_per_eng", + 28928.1, + "lbf", + "" + ], + [ + "mission:landing:lift_coefficient_max", + 2, + "unitless", + "" + ], + [ + "mission:summary:cruise_mach", + 0.785, + "unitless", + "" + ], + [ + "mission:takeoff:fuel_simple", + 577, + "lbm", + "" + ], + [ + "mission:takeoff:lift_coefficient_max", + 3, + "unitless", + "" + ], + [ + "mission:takeoff:lift_over_drag", + 17.354, + "unitless", + "" + ], + [ + "settings:equations_of_motion", + "[]", + "unitless", + "" + ], + [ + "settings:mass_method", + "[]", + "unitless", + "" + ], + [ + "mission:summary:gross_mass", + 175864.58080717592, + "lbm", + "" + ], + [ + "aircraft:propulsion:total_num_engines", + 2, + "unitless", + "" + ], + [ + "aircraft:propulsion:total_num_fuselage_engines", + 0, + "unitless", + "" + ], + [ + "aircraft:propulsion:total_num_wing_engines", + 2, + "unitless", + "" + ] +] \ No newline at end of file diff --git a/aviary/subsystems/propulsion/gearbox/gearbox_builder.py b/aviary/subsystems/propulsion/gearbox/gearbox_builder.py index f62e88b24..f850f3870 100644 --- a/aviary/subsystems/propulsion/gearbox/gearbox_builder.py +++ b/aviary/subsystems/propulsion/gearbox/gearbox_builder.py @@ -6,15 +6,15 @@ class GearboxBuilder(SubsystemBuilderBase): """ - Define the builder for a single gearbox subsystem that provides methods - to define the gearbox subsystem's states, design variables, fixed values, - initial guesses, and mass names. It also provides methods to build OpenMDAO - systems for the pre-mission and mission computations of the subsystem, + Define the builder for a single gearbox subsystem that provides methods + to define the gearbox subsystem's states, design variables, fixed values, + initial guesses, and mass names. It also provides methods to build OpenMDAO + systems for the pre-mission and mission computations of the subsystem, to get the constraints for the subsystem, and to preprocess the inputs for - the subsystem. + the subsystem. - This is meant to be computations for a single gearbox, so there is no notion - of "num_gearboxs" in this code. + This is meant to be computations for a single gearbox, so there is no notion + of "num_gearboxes" in this code. This is a reduction gearbox, so gear ratio is input_RPM/output_RPM. """ @@ -87,17 +87,17 @@ def get_mass_names(self): def get_outputs(self): return [ - Dynamic.Mission.RPM_GEARBOX, - Dynamic.Mission.SHAFT_POWER_GEARBOX, - Dynamic.Mission.SHAFT_POWER_MAX_GEARBOX, - Dynamic.Mission.TORQUE_GEARBOX, - Mission.Constraints.SHAFT_POWER_RESIDUAL, + Dynamic.Mission.SHAFT_POWER + '_out', + Dynamic.Mission.SHAFT_POWER_MAX + '_out', + Dynamic.Mission.RPM + '_out', + Dynamic.Mission.TORQUE + '_out', + Mission.Constraints.GEARBOX_SHAFT_POWER_RESIDUAL, ] def get_constraints(self): if self.include_constraints: constraints = { - Mission.Constraints.SHAFT_POWER_RESIDUAL: { + Mission.Constraints.GEARBOX_SHAFT_POWER_RESIDUAL: { 'lower': 0.0, 'type': 'path', 'units': 'kW', diff --git a/aviary/subsystems/propulsion/gearbox/model/gearbox_mission.py b/aviary/subsystems/propulsion/gearbox/model/gearbox_mission.py index 87243747e..62a9587b4 100644 --- a/aviary/subsystems/propulsion/gearbox/model/gearbox_mission.py +++ b/aviary/subsystems/propulsion/gearbox/model/gearbox_mission.py @@ -7,7 +7,9 @@ class GearboxMission(om.Group): - """Calculates the mission performance (ODE) of a single gearbox.""" + """ + Calculates the mission performance of a single gearbox. + """ def initialize(self): self.options.declare("num_nodes", types=int) @@ -21,65 +23,103 @@ def initialize(self): def setup(self): n = self.options["num_nodes"] - self.add_subsystem('RPM_comp', - om.ExecComp('RPM_out = RPM_in / gear_ratio', - RPM_out={'val': np.ones(n), 'units': 'rpm'}, - gear_ratio={'val': 1.0, 'units': 'unitless'}, - RPM_in={'val': np.ones(n), 'units': 'rpm'}, - has_diag_partials=True), - promotes_inputs=[('RPM_in', Aircraft.Engine.RPM_DESIGN), - ('gear_ratio', Aircraft.Engine.Gearbox.GEAR_RATIO)], - promotes_outputs=[('RPM_out', Dynamic.Mission.RPM_GEARBOX)]) + self.add_subsystem( + 'rpm_comp', + om.ExecComp( + 'rpm_out = rpm_in / gear_ratio', + rpm_out={'val': np.ones(n), 'units': 'rpm'}, + gear_ratio={'val': 1.0, 'units': 'unitless'}, + rpm_in={'val': np.ones(n), 'units': 'rpm'}, + has_diag_partials=True, + ), + promotes_inputs=[ + ('rpm_in', Dynamic.Mission.RPM + '_in'), + ('gear_ratio', Aircraft.Engine.Gearbox.GEAR_RATIO), + ], + promotes_outputs=[('rpm_out', Dynamic.Mission.RPM + '_out')], + ) - self.add_subsystem('shaft_power_comp', - om.ExecComp('shaft_power_out = shaft_power_in * eff', - shaft_power_in={'val': np.ones(n), 'units': 'kW'}, - shaft_power_out={ - 'val': np.ones(n), 'units': 'kW'}, - eff={'val': 0.98, 'units': 'unitless'}, - has_diag_partials=True), - promotes_inputs=[('shaft_power_in', Dynamic.Mission.SHAFT_POWER), - ('eff', Aircraft.Engine.Gearbox.EFFICIENCY)], - promotes_outputs=[('shaft_power_out', Dynamic.Mission.SHAFT_POWER_GEARBOX)]) + self.add_subsystem( + 'shaft_power_comp', + om.ExecComp( + 'shaft_power_out = shaft_power_in * efficiency', + shaft_power_in={'val': np.ones(n), 'units': 'kW'}, + shaft_power_out={'val': np.ones(n), 'units': 'kW'}, + efficiency={'val': 1.0, 'units': 'unitless'}, + has_diag_partials=True, + ), + promotes_inputs=[ + ('shaft_power_in', Dynamic.Mission.SHAFT_POWER + '_in'), + ('efficiency', Aircraft.Engine.Gearbox.EFFICIENCY), + ], + promotes_outputs=[ + ('shaft_power_out', Dynamic.Mission.SHAFT_POWER + '_out') + ], + ) - self.add_subsystem('torque_comp', - om.ExecComp('torque_out = shaft_power_out / RPM_out', - shaft_power_out={ - 'val': np.ones(n), 'units': 'kW'}, - torque_out={'val': np.ones(n), 'units': 'kN*m'}, - RPM_out={'val': np.ones(n), 'units': 'rad/s'}, - has_diag_partials=True), - promotes_inputs=[('shaft_power_out', Dynamic.Mission.SHAFT_POWER_GEARBOX), - ('RPM_out', Dynamic.Mission.RPM_GEARBOX)], - promotes_outputs=[('torque_out', Dynamic.Mission.TORQUE_GEARBOX)]) + self.add_subsystem( + 'torque_comp', + om.ExecComp( + 'torque_out = shaft_power_out / rpm_out', + shaft_power_out={'val': np.ones(n), 'units': 'kW'}, + torque_out={'val': np.ones(n), 'units': 'kN*m'}, + rpm_out={'val': np.ones(n), 'units': 'rad/s'}, + has_diag_partials=True, + ), + promotes_outputs=[('torque_out', Dynamic.Mission.TORQUE + '_out')], + ) + self.connect( + f'{Dynamic.Mission.SHAFT_POWER}_out', + f'torque_comp.shaft_power_out', + ) + + self.connect( + f'{Dynamic.Mission.RPM}_out', + f'torque_comp.rpm_out', + ) # Determine the maximum power available at this flight condition # this is used for excess power constraints - self.add_subsystem('shaft_power_max_comp', - om.ExecComp('shaft_power_out = shaft_power_in * eff', - shaft_power_in={'val': np.ones(n), 'units': 'kW'}, - shaft_power_out={ - 'val': np.ones(n), 'units': 'kW'}, - eff={'val': 0.98, 'units': 'unitless'}, - has_diag_partials=True), - promotes_inputs=[('shaft_power_in', Dynamic.Mission.SHAFT_POWER_MAX), - ('eff', Aircraft.Engine.Gearbox.EFFICIENCY)], - promotes_outputs=[('shaft_power_out', Dynamic.Mission.SHAFT_POWER_MAX_GEARBOX)]) + self.add_subsystem( + 'shaft_power_max_comp', + om.ExecComp( + 'shaft_power_out = shaft_power_in * efficiency', + shaft_power_in={'val': np.ones(n), 'units': 'kW'}, + shaft_power_out={'val': np.ones(n), 'units': 'kW'}, + efficiency={'val': 1.0, 'units': 'unitless'}, + has_diag_partials=True, + ), + promotes_inputs=[ + ('shaft_power_in', Dynamic.Mission.SHAFT_POWER_MAX + '_in'), + ('efficiency', Aircraft.Engine.Gearbox.EFFICIENCY), + ], + promotes_outputs=[ + ('shaft_power_out', Dynamic.Mission.SHAFT_POWER_MAX + '_out') + ], + ) # We must ensure the design shaft power that was provided to pre-mission is - # larger than the maximum shaft power that could be drawn by the mission. - # Note this is a larger value than the actual maximum shaft power drawn during the mission - # because the aircraft might need to climb to avoid obstacles at anytime during the mission - self.add_subsystem('shaft_power_residual', - om.ExecComp('shaft_power_resid = shaft_power_design - shaft_power_max', - shaft_power_max={ - 'val': np.ones(n), 'units': 'kW'}, - shaft_power_design={'val': 1.0, 'units': 'kW'}, - shaft_power_resid={ - 'val': np.ones(n), 'units': 'kW'}, - has_diag_partials=True), - promotes_inputs=[('shaft_power_max', Dynamic.Mission.SHAFT_POWER_MAX), - ('shaft_power_design', Aircraft.Engine.Gearbox.SHAFT_POWER_DESIGN)], - promotes_outputs=[('shaft_power_resid', Mission.Constraints.SHAFT_POWER_RESIDUAL)]) - - # TODO max thrust from the props will depend on this max shaft power from the gearbox and the new gearbox RPM value + # larger than the maximum shaft power that could be drawn by the mission. + # Note this is a larger value than the actual maximum shaft power drawn during + # the mission because the aircraft might need to climb to avoid obstacles at + # anytime during the mission + self.add_subsystem( + 'shaft_power_residual', + om.ExecComp( + 'shaft_power_residual = shaft_power_design - shaft_power_max', + shaft_power_max={'val': np.ones(n), 'units': 'kW'}, + shaft_power_design={'val': 1.0, 'units': 'kW'}, + shaft_power_residual={'val': np.ones(n), 'units': 'kW'}, + has_diag_partials=True, + ), + promotes_inputs=[ + ('shaft_power_max', Dynamic.Mission.SHAFT_POWER_MAX + '_in'), + ('shaft_power_design', Aircraft.Engine.Gearbox.SHAFT_POWER_DESIGN), + ], + promotes_outputs=[ + ( + 'shaft_power_residual', + Mission.Constraints.GEARBOX_SHAFT_POWER_RESIDUAL, + ) + ], + ) diff --git a/aviary/subsystems/propulsion/gearbox/model/gearbox_premission.py b/aviary/subsystems/propulsion/gearbox/model/gearbox_premission.py index 226fca7cc..d43c08b63 100644 --- a/aviary/subsystems/propulsion/gearbox/model/gearbox_premission.py +++ b/aviary/subsystems/propulsion/gearbox/model/gearbox_premission.py @@ -44,18 +44,25 @@ def setup(self): 'RPM_out'], promotes_outputs=['torque_max']) - # Simple gearbox mass will always produce positive values for mass based on a fixed specific torque - self.add_subsystem('mass_comp', - om.ExecComp('gearbox_mass = torque_max / specific_torque', - gearbox_mass={'val': 0.0, 'units': 'kg'}, - torque_max={'val': 0.0, 'units': 'N*m'}, - specific_torque={'val': 0.0, 'units': 'N*m/kg'}, - has_diag_partials=True), - promotes_inputs=['torque_max', - ('specific_torque', Aircraft.Engine.Gearbox.SPECIFIC_TORQUE)], - promotes_outputs=[('gearbox_mass', Aircraft.Engine.Gearbox.MASS)]) + if self.options["simple_mass"]: + # Simple gearbox mass will always produce positive values for mass based on a fixed specific torque + self.add_subsystem( + 'mass_comp', + om.ExecComp( + 'gearbox_mass = torque_max / specific_torque', + gearbox_mass={'val': 0.0, 'units': 'kg'}, + torque_max={'val': 0.0, 'units': 'N*m'}, + specific_torque={'val': 0.0, 'units': 'N*m/kg'}, + has_diag_partials=True, + ), + promotes_inputs=[ + 'torque_max', + ('specific_torque', Aircraft.Engine.Gearbox.SPECIFIC_TORQUE), + ], + promotes_outputs=[('gearbox_mass', Aircraft.Engine.Gearbox.MASS)], + ) - if self.options["simple_mass"] is False: + else: # This gearbox mass calc can work for large systems but can produce negative weights for some inputs # Gearbox mass from "An N+3 Technolgoy Level Reference Propulsion System" by Scott Jones, William Haller, and Michael Tong # NASA TM 2017-219501 diff --git a/aviary/subsystems/propulsion/gearbox/test/test_gearbox.py b/aviary/subsystems/propulsion/gearbox/test/test_gearbox.py index ebeb6c5a2..816b8ac03 100644 --- a/aviary/subsystems/propulsion/gearbox/test/test_gearbox.py +++ b/aviary/subsystems/propulsion/gearbox/test/test_gearbox.py @@ -53,19 +53,26 @@ def test_gearbox_mission(self): prob.setup(force_alloc_complex=True) - prob.set_val(av.Aircraft.Engine.RPM_DESIGN, [5000, 6195, 6195], units='rpm') - prob.set_val(av.Dynamic.Mission.SHAFT_POWER, [100, 200, 375], units='hp') - prob.set_val(av.Dynamic.Mission.SHAFT_POWER_MAX, [375, 300, 375], units='hp') + prob.set_val(av.Dynamic.Mission.RPM + '_in', [5000, 6195, 6195], units='rpm') + prob.set_val( + av.Dynamic.Mission.SHAFT_POWER + '_in', [100, 200, 375], units='hp' + ) + prob.set_val( + av.Dynamic.Mission.SHAFT_POWER_MAX + '_in', [375, 300, 375], units='hp' + ) prob.set_val(av.Aircraft.Engine.Gearbox.GEAR_RATIO, 12.6, units=None) prob.set_val(av.Aircraft.Engine.Gearbox.EFFICIENCY, 0.98, units=None) prob.run_model() - SHAFT_POWER_GEARBOX = prob.get_val(av.Dynamic.Mission.SHAFT_POWER_GEARBOX, 'hp') - RPM_GEARBOX = prob.get_val(av.Dynamic.Mission.RPM_GEARBOX, 'rpm') - TORQUE_GEARBOX = prob.get_val(av.Dynamic.Mission.TORQUE_GEARBOX, 'ft*lbf') + SHAFT_POWER_GEARBOX = prob.get_val( + av.Dynamic.Mission.SHAFT_POWER + '_out', 'hp' + ) + RPM_GEARBOX = prob.get_val(av.Dynamic.Mission.RPM + '_out', 'rpm') + TORQUE_GEARBOX = prob.get_val(av.Dynamic.Mission.TORQUE + '_out', 'ft*lbf') SHAFT_POWER_MAX_GEARBOX = prob.get_val( - av.Dynamic.Mission.SHAFT_POWER_MAX_GEARBOX, 'hp') + av.Dynamic.Mission.SHAFT_POWER_MAX + '_out', 'hp' + ) SHAFT_POWER_GEARBOX_expected = [98., 196., 367.5] RPM_GEARBOX_expected = [396.82539683, 491.66666667, 491.66666667] diff --git a/aviary/subsystems/propulsion/propeller/hamilton_standard.py b/aviary/subsystems/propulsion/propeller/hamilton_standard.py index 952f37430..6091a10f4 100644 --- a/aviary/subsystems/propulsion/propeller/hamilton_standard.py +++ b/aviary/subsystems/propulsion/propeller/hamilton_standard.py @@ -1,10 +1,13 @@ +import math import warnings + import numpy as np import openmdao.api as om + from aviary.utils.aviary_values import AviaryValues from aviary.variable_info.enums import Verbosity from aviary.variable_info.variables import Aircraft, Dynamic, Settings -from aviary.constants import RHO_SEA_LEVEL_ENGLISH, TSLS_DEGR +from aviary.constants import RHO_SEA_LEVEL_ENGLISH from aviary.utils.functions import add_aviary_input, add_aviary_output @@ -67,12 +70,19 @@ def _unint(xa, ya, x): d2 = x - xa[jx1+1] d3 = x - xa[jx1+2] d4 = x - xa[jx1+3] - c1 = ra/p1*d2/p4*d3 - c2 = -ra/p1*d1/p2*d3 + rb/p2*d3/p5*d4 - c3 = ra/p2*d1/p4*d2 - rb/p2*d2/p3*d4 - c4 = rb/p5*d2/p3*d3 + c1 = ra / p1 * d2 / p4 * d3 + c2 = -ra / p1 * d1 / p2 * d3 + rb / p2 * d3 / p5 * d4 + c3 = ra / p2 * d1 / p4 * d2 - rb / p2 * d2 / p3 * d4 + c4 = rb / p5 * d2 / p3 * d3 y = ya[jx1]*c1 + ya[jx1+1]*c2 + ya[jx1+2]*c3 + ya[jx1+3]*c4 + # we don't want y to be an array + try: + y = y[0] + # floats/ints will give TypeError, numpy versions give IndexError + except (TypeError, IndexError): + pass + return y, Lmt @@ -239,6 +249,9 @@ def _biquad(T, i, xi, yi): return z, lmt +# DO NOT AUTO-FORMAT TABLES +# autopep8: off +# fmt: off CP_Angle_table = np.array([ [ # 2 blades [0.0158, 0.0165, .0188, .0230, .0369, @@ -457,6 +470,8 @@ def _biquad(T, i, xi, yi): .525, .540, .565, .615, .670, .710, .745, .790, .825, .860, .880, .895, # X = 0.20 .225, .260, .320, .375, .430, .495, .550, .610, .660, .710, .740, .775, # X = 0.30 ]) +# autopep8: on +# fmt: on class PreHamiltonStandard(om.ExplicitComponent): @@ -480,21 +495,23 @@ def setup(self): add_aviary_input( self, Dynamic.Mission.DENSITY, val=np.zeros(nn), units='slug/ft**3' ) - add_aviary_input(self, Dynamic.Mission.VELOCITY, val=np.zeros(nn), units='knot') + add_aviary_input(self, Dynamic.Mission.VELOCITY, val=np.zeros(nn), units='ft/s') add_aviary_input( - self, Dynamic.Mission.SPEED_OF_SOUND, val=np.zeros(nn), units='knot' + self, Dynamic.Mission.SPEED_OF_SOUND, val=np.zeros(nn), units='ft/s' ) self.add_output('power_coefficient', val=np.zeros(nn), units='unitless') self.add_output('advance_ratio', val=np.zeros(nn), units='unitless') self.add_output('tip_mach', val=np.zeros(nn), units='unitless') - self.add_output('density_ratio', val=np.zeros(nn), units='unitless') + # TODO this conflicts with 2DOF phases that also output density ratio + # Right now repeating calculation in post-HS component where it is also used + # self.add_output('density_ratio', val=np.zeros(nn), units='unitless') def setup_partials(self): arange = np.arange(self.options['num_nodes']) - self.declare_partials( - 'density_ratio', Dynamic.Mission.DENSITY, rows=arange, cols=arange) + # self.declare_partials( + # 'density_ratio', Dynamic.Mission.DENSITY, rows=arange, cols=arange) self.declare_partials( 'tip_mach', [ @@ -518,13 +535,12 @@ def setup_partials(self): def compute(self, inputs, outputs): diam_prop = inputs[Aircraft.Engine.PROPELLER_DIAMETER] shp = inputs[Dynamic.Mission.SHAFT_POWER] - vktas = inputs[Dynamic.Mission.VELOCITY] + vtas = inputs[Dynamic.Mission.VELOCITY] tipspd = inputs[Dynamic.Mission.PROPELLER_TIP_SPEED] sos = inputs[Dynamic.Mission.SPEED_OF_SOUND] # arbitrarily small number to keep advance ratio nonzero, which allows for static thrust prediction - # NOTE need for a separate static thrust calc method? - vktas[np.where(vktas <= 1e-6)] = 1e-6 + vtas[np.where(vtas <= 1e-6)] = 1e-6 density_ratio = inputs[Dynamic.Mission.DENSITY] / RHO_SEA_LEVEL_ENGLISH if diam_prop <= 0.0: @@ -541,16 +557,21 @@ def compute(self, inputs, outputs): if any(shp) < 0.0: raise om.AnalysisError("Dynamic.Mission.SHAFT_POWER must be non-negative.") - outputs['density_ratio'] = density_ratio - # 1118.21948771 is speed of sound at sea level + # outputs['density_ratio'] = density_ratio # TODO tip mach was already calculated, revisit this outputs['tip_mach'] = tipspd / sos - outputs['advance_ratio'] = 5.309 * vktas / tipspd - outputs['power_coefficient'] = shp * 10.E10 / (2 * 6966.) / density_ratio \ + outputs['advance_ratio'] = math.pi * vtas / tipspd + # TODO back out what is going on with unit conversion factor 10e10/(2*6966) + outputs['power_coefficient'] = ( + shp + * 10.0e10 + / (2 * 6966.0) + / density_ratio / (tipspd**3 * diam_prop**2) + ) def compute_partials(self, inputs, partials): - vktas = inputs[Dynamic.Mission.VELOCITY] + vtas = inputs[Dynamic.Mission.VELOCITY] tipspd = inputs[Dynamic.Mission.PROPELLER_TIP_SPEED] rho = inputs[Dynamic.Mission.DENSITY] diam_prop = inputs[Aircraft.Engine.PROPELLER_DIAMETER] @@ -559,12 +580,13 @@ def compute_partials(self, inputs, partials): unit_conversion_const = 10.E10 / (2 * 6966.) - partials["density_ratio", Dynamic.Mission.DENSITY] = 1 / RHO_SEA_LEVEL_ENGLISH + # partials["density_ratio", Dynamic.Mission.DENSITY] = 1 / RHO_SEA_LEVEL_ENGLISH partials["tip_mach", Dynamic.Mission.PROPELLER_TIP_SPEED] = 1 / sos partials["tip_mach", Dynamic.Mission.SPEED_OF_SOUND] = -tipspd / sos**2 - partials["advance_ratio", Dynamic.Mission.VELOCITY] = 5.309 / tipspd - partials["advance_ratio", Dynamic.Mission.PROPELLER_TIP_SPEED] = - \ - 5.309 * vktas / (tipspd * tipspd) + partials["advance_ratio", Dynamic.Mission.VELOCITY] = math.pi / tipspd + partials["advance_ratio", Dynamic.Mission.PROPELLER_TIP_SPEED] = ( + -math.pi * vtas / (tipspd * tipspd) + ) partials["power_coefficient", Dynamic.Mission.SHAFT_POWER] = unit_conversion_const * \ RHO_SEA_LEVEL_ENGLISH / (rho * tipspd**3*diam_prop**2) partials["power_coefficient", Dynamic.Mission.DENSITY] = -unit_conversion_const * shp * \ @@ -616,8 +638,20 @@ def setup(self): def compute(self, inputs, outputs): verbosity = self.options['aviary_options'].get_val(Settings.VERBOSITY) + act_factor = inputs[Aircraft.Engine.PROPELLER_ACTIVITY_FACTOR][0] + cli = inputs[Aircraft.Engine.PROPELLER_INTEGRATED_LIFT_COEFFICIENT][0] num_blades = self.options['aviary_options'].get_val( - Aircraft.Engine.NUM_PROPELLER_BLADES) + Aircraft.Engine.NUM_PROPELLER_BLADES + ) + # TODO verify this works with multiple engine models (i.e. prop mission is + # properly slicing these inputs) + # ensure num_blades is an int, so it can be used as array index later + try: + len(num_blades) + except TypeError: + num_blades = int(num_blades) + else: + num_blades = int(num_blades[0]) for i_node in range(self.options['num_nodes']): ichck = 0 @@ -635,7 +669,7 @@ def compute(self, inputs, outputs): TXCLI = np.zeros(6) CTTT = np.zeros(4) XXXFT = np.zeros(4) - act_factor = inputs[Aircraft.Engine.PROPELLER_ACTIVITY_FACTOR][0] + for k in range(2): AF_adj_CP[k], run_flag = _unint(Act_Factor_arr, AFCPC[k], act_factor) AF_adj_CT[k], run_flag = _unint(Act_Factor_arr, AFCTC[k], act_factor) @@ -667,7 +701,7 @@ def compute(self, inputs, outputs): # flag that given lift coeff (cli) does not fall on a node point of CL_arr CL_tab_idx_flg = 0 # NCL_flg ifnd = 0 - cli = inputs[Aircraft.Engine.PROPELLER_INTEGRATED_LIFT_COEFFICIENT][0] + power_coefficient = inputs['power_coefficient'][i_node] for ii in range(6): cl_idx = ii @@ -693,7 +727,7 @@ def compute(self, inputs, outputs): lmod = (num_blades % 2) + 1 if (lmod == 1): nbb = 1 - idx_blade = int(num_blades/2.0) + idx_blade = int(num_blades / 2) # even number of blades idx_blade = 1 if 2 blades; # idx_blade = 2 if 4 blades; # idx_blade = 3 if 6 blades; @@ -748,7 +782,10 @@ def compute(self, inputs, outputs): ang_len = ang_arr_len[kdx] BLL[kdx], run_flag = _unint( # blade angle at baseline point for kdx - CP_Angle_table[idx_blade][kdx][:ang_len], Blade_angle_table[kdx], CP_Eff) + CP_Angle_table[idx_blade][kdx][:ang_len], + Blade_angle_table[kdx], + CP_Eff, + ) try: CTT[kdx], run_flag = _unint( # thrust coeff at baseline point for kdx @@ -876,7 +913,7 @@ def setup(self): add_aviary_input( self, Dynamic.Mission.PROPELLER_TIP_SPEED, val=np.zeros(nn), units='ft/s' ) - self.add_input('density_ratio', val=np.zeros(nn), units='unitless') + self.add_input(Dynamic.Mission.DENSITY, val=np.zeros(nn), units='slug/ft**3') self.add_input('advance_ratio', val=np.zeros(nn), units='unitless') self.add_input('power_coefficient', val=np.zeros(nn), units='unitless') @@ -894,13 +931,18 @@ def setup_partials(self): 'thrust_coefficient', 'comp_tip_loss_factor', ], rows=arange, cols=arange) - self.declare_partials(Dynamic.Mission.THRUST, [ - 'thrust_coefficient', - 'comp_tip_loss_factor', - Dynamic.Mission.PROPELLER_TIP_SPEED, - 'density_ratio', - 'install_loss_factor', - ], rows=arange, cols=arange) + self.declare_partials( + Dynamic.Mission.THRUST, + [ + 'thrust_coefficient', + 'comp_tip_loss_factor', + Dynamic.Mission.PROPELLER_TIP_SPEED, + Dynamic.Mission.DENSITY, + 'install_loss_factor', + ], + rows=arange, + cols=arange, + ) self.declare_partials(Dynamic.Mission.THRUST, [ Aircraft.Engine.PROPELLER_DIAMETER, ]) @@ -924,8 +966,17 @@ def compute(self, inputs, outputs): diam_prop = inputs[Aircraft.Engine.PROPELLER_DIAMETER] tipspd = inputs[Dynamic.Mission.PROPELLER_TIP_SPEED] install_loss_factor = inputs['install_loss_factor'] - outputs[Dynamic.Mission.THRUST] = ctx*tipspd**2*diam_prop**2 * \ - inputs['density_ratio']/(1.515E06)*364.76*(1. - install_loss_factor) + density_ratio = inputs[Dynamic.Mission.DENSITY] / RHO_SEA_LEVEL_ENGLISH + + outputs[Dynamic.Mission.THRUST] = ( + ctx + * tipspd**2 + * diam_prop**2 + * density_ratio + / (1.515e06) + * 364.76 + * (1.0 - install_loss_factor) + ) # avoid divide by zero when shaft power is zero calc_idx = np.where(inputs['power_coefficient'] > 1e-6) # index where CP > 1e-5 @@ -943,23 +994,56 @@ def compute_partials(self, inputs, partials): diam_prop = inputs[Aircraft.Engine.PROPELLER_DIAMETER] install_loss_factor = inputs['install_loss_factor'] tipspd = inputs[Dynamic.Mission.PROPELLER_TIP_SPEED] + density_ratio = inputs[Dynamic.Mission.DENSITY] / RHO_SEA_LEVEL_ENGLISH unit_conversion_factor = 364.76 / 1.515E06 partials["thrust_coefficient_comp_loss", 'thrust_coefficient'] = XFT partials["thrust_coefficient_comp_loss", 'comp_tip_loss_factor'] = inputs['thrust_coefficient'] - partials[Dynamic.Mission.THRUST, 'thrust_coefficient'] = XFT*tipspd**2*diam_prop**2 * \ - inputs['density_ratio']*unit_conversion_factor*(1. - install_loss_factor) - partials[Dynamic.Mission.THRUST, 'comp_tip_loss_factor'] = inputs['thrust_coefficient']*tipspd**2*diam_prop**2 * \ - inputs['density_ratio']*unit_conversion_factor*(1. - install_loss_factor) - partials[Dynamic.Mission.THRUST, Dynamic.Mission.PROPELLER_TIP_SPEED] = 2*ctx*tipspd*diam_prop**2 * \ - inputs['density_ratio']*unit_conversion_factor*(1. - install_loss_factor) - partials[Dynamic.Mission.THRUST, Aircraft.Engine.PROPELLER_DIAMETER] = 2*ctx*tipspd**2*diam_prop * \ - inputs['density_ratio']*unit_conversion_factor*(1. - install_loss_factor) - partials[Dynamic.Mission.THRUST, 'density_ratio'] = ctx*tipspd**2 * \ - diam_prop**2*unit_conversion_factor*(1. - install_loss_factor) - partials[Dynamic.Mission.THRUST, 'install_loss_factor'] = -ctx*tipspd**2*diam_prop**2 * \ - inputs['density_ratio']*unit_conversion_factor + partials[Dynamic.Mission.THRUST, 'thrust_coefficient'] = ( + XFT + * tipspd**2 + * diam_prop**2 + * density_ratio + * unit_conversion_factor + * (1.0 - install_loss_factor) + ) + partials[Dynamic.Mission.THRUST, 'comp_tip_loss_factor'] = ( + inputs['thrust_coefficient'] + * tipspd**2 + * diam_prop**2 + * density_ratio + * unit_conversion_factor + * (1.0 - install_loss_factor) + ) + partials[Dynamic.Mission.THRUST, Dynamic.Mission.PROPELLER_TIP_SPEED] = ( + 2 + * ctx + * tipspd + * diam_prop**2 + * density_ratio + * unit_conversion_factor + * (1.0 - install_loss_factor) + ) + partials[Dynamic.Mission.THRUST, Aircraft.Engine.PROPELLER_DIAMETER] = ( + 2 + * ctx + * tipspd**2 + * diam_prop + * density_ratio + * unit_conversion_factor + * (1.0 - install_loss_factor) + ) + partials[Dynamic.Mission.THRUST, Dynamic.Mission.DENSITY] = ( + ctx + * tipspd**2 + * diam_prop**2 + * unit_conversion_factor + * (1.0 - install_loss_factor) / RHO_SEA_LEVEL_ENGLISH + ) + partials[Dynamic.Mission.THRUST, 'install_loss_factor'] = ( + -ctx * tipspd**2 * diam_prop**2 * density_ratio * unit_conversion_factor + ) calc_idx = np.where(inputs['power_coefficient'] > 1e-6) pow_coeff = inputs['power_coefficient'] diff --git a/aviary/subsystems/propulsion/propeller/propeller_performance.py b/aviary/subsystems/propulsion/propeller/propeller_performance.py index 161fa7868..9d952eb60 100644 --- a/aviary/subsystems/propulsion/propeller/propeller_performance.py +++ b/aviary/subsystems/propulsion/propeller/propeller_performance.py @@ -5,7 +5,11 @@ from openmdao.components.ks_comp import KSfunction -from aviary.subsystems.propulsion.propeller.hamilton_standard import HamiltonStandard, PostHamiltonStandard, PreHamiltonStandard +from aviary.subsystems.propulsion.propeller.hamilton_standard import ( + HamiltonStandard, + PostHamiltonStandard, + PreHamiltonStandard, +) from aviary.subsystems.propulsion.propeller.propeller_map import PropellerMap from aviary.utils.aviary_values import AviaryValues from aviary.utils.functions import add_aviary_input, add_aviary_output @@ -47,60 +51,50 @@ def d_smooth_min(x, b, alpha=100.0): return d_sum_log_exp -class TipSpeedLimit(om.ExplicitComponent): +class TipSpeed(om.ExplicitComponent): """ - Computation of propeller tip speed. + Compute current propeller speed and allowable max tip speed + Maximum allowable tip speed is lower of helical tip Mach limited speed and + tip rotational speed limit """ def initialize(self): self.options.declare( - 'num_nodes', types=int, default=1, - desc='Number of nodes to be evaluated in the RHS') + 'num_nodes', + types=int, + default=1, + desc='Number of nodes to be evaluated in the RHS', + ) def setup(self): num_nodes = self.options['num_nodes'] add_aviary_input( - self, - Dynamic.Mission.VELOCITY, - val=np.zeros(num_nodes), - units='ft/s' + self, Dynamic.Mission.VELOCITY, val=np.zeros(num_nodes), units='ft/s' ) add_aviary_input( - self, - Dynamic.Mission.SPEED_OF_SOUND, - val=np.zeros(num_nodes), - units='ft/s' + self, Dynamic.Mission.SPEED_OF_SOUND, val=np.zeros(num_nodes), units='ft/s' ) add_aviary_input( - self, - Aircraft.Engine.PROPELLER_TIP_MACH_MAX, - val=1.0, - units='unitless' + self, Dynamic.Mission.RPM, val=np.zeros(num_nodes), units='rpm' ) add_aviary_input( - self, - Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, - val=0.0, - units='ft/s' + self, Aircraft.Engine.PROPELLER_TIP_MACH_MAX, val=1.0, units='unitless' ) + add_aviary_input( - self, - Aircraft.Engine.PROPELLER_DIAMETER, - val=0.0, - units='ft' + self, Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, val=0.0, units='ft/s' ) + add_aviary_input(self, Aircraft.Engine.PROPELLER_DIAMETER, val=0.0, units='ft') add_aviary_output( self, Dynamic.Mission.PROPELLER_TIP_SPEED, val=np.zeros(num_nodes), - units='ft/s' + units='ft/s', ) self.add_output( - 'rpm', - val=np.zeros(num_nodes), - units='rpm' + 'propeller_tip_speed_limit', val=np.zeros(num_nodes), units='ft/s' ) def setup_partials(self): @@ -110,37 +104,35 @@ def setup_partials(self): r = np.arange(num_nodes) self.declare_partials( - Dynamic.Mission.PROPELLER_TIP_SPEED, + 'propeller_tip_speed_limit', [ Dynamic.Mission.VELOCITY, Dynamic.Mission.SPEED_OF_SOUND, ], - rows=r, cols=r, + rows=r, + cols=r, ) - self.declare_partials( - Dynamic.Mission.PROPELLER_TIP_SPEED, + 'propeller_tip_speed_limit', [ Aircraft.Engine.PROPELLER_TIP_MACH_MAX, - Aircraft.Engine.PROPELLER_TIP_SPEED_MAX + Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, ], ) self.declare_partials( - 'rpm', + Dynamic.Mission.PROPELLER_TIP_SPEED, [ - Dynamic.Mission.VELOCITY, - Dynamic.Mission.SPEED_OF_SOUND, + Dynamic.Mission.RPM, ], - rows=r, cols=r, + rows=r, + cols=r, ) self.declare_partials( - 'rpm', + Dynamic.Mission.PROPELLER_TIP_SPEED, [ - Aircraft.Engine.PROPELLER_TIP_MACH_MAX, - Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, - Aircraft.Engine.PROPELLER_DIAMETER + Aircraft.Engine.PROPELLER_DIAMETER, ], ) @@ -151,33 +143,35 @@ def compute(self, inputs, outputs): sos = inputs[Dynamic.Mission.SPEED_OF_SOUND] tip_mach_max = inputs[Aircraft.Engine.PROPELLER_TIP_MACH_MAX] tip_speed_max = inputs[Aircraft.Engine.PROPELLER_TIP_SPEED_MAX] + rpm = inputs[Dynamic.Mission.RPM] diam = inputs[Aircraft.Engine.PROPELLER_DIAMETER] - tip_speed_mach_limit = ((sos * tip_mach_max)**2 - velocity**2)**0.5 + tip_speed_mach_limit = ((sos * tip_mach_max) ** 2 - velocity**2) ** 0.5 # use KSfunction for smooth derivitive across minimum tip_speed_max_nn = np.tile(tip_speed_max, num_nodes) - prop_tip_speed = -KSfunction.compute( + propeller_tip_speed_limit = -KSfunction.compute( -np.stack((tip_speed_max_nn, tip_speed_mach_limit), axis=1) ).flatten() - rpm = prop_tip_speed / (diam * math.pi / 60) + propeller_tip_speed = rpm * diam * math.pi / 60 - outputs[Dynamic.Mission.PROPELLER_TIP_SPEED] = prop_tip_speed - outputs['rpm'] = rpm + outputs[Dynamic.Mission.PROPELLER_TIP_SPEED] = propeller_tip_speed + outputs['propeller_tip_speed_limit'] = propeller_tip_speed_limit def compute_partials(self, inputs, J): num_nodes = self.options['num_nodes'] velocity = inputs[Dynamic.Mission.VELOCITY] sos = inputs[Dynamic.Mission.SPEED_OF_SOUND] + rpm = inputs[Dynamic.Mission.RPM] tip_mach_max = inputs[Aircraft.Engine.PROPELLER_TIP_MACH_MAX] tip_speed_max = inputs[Aircraft.Engine.PROPELLER_TIP_SPEED_MAX] diam = inputs[Aircraft.Engine.PROPELLER_DIAMETER] tip_speed_max_nn = np.tile(tip_speed_max, num_nodes) - tip_speed_mach_limit = ((sos * tip_mach_max)**2 - velocity**2)**0.5 + tip_speed_mach_limit = ((sos * tip_mach_max) ** 2 - velocity**2) ** 0.5 val = -np.stack((tip_speed_max_nn, tip_speed_mach_limit), axis=1) - prop_tip_speed = -KSfunction.compute(val).flatten() + # prop_tip_speed = -KSfunction.compute(val).flatten() dKS, _ = KSfunction.derivatives(val) @@ -190,32 +184,27 @@ def compute_partials(self, inputs, J): dspeed_dmm = dKS[:, 1] * dtpml_m dspeed_dsm = dKS[:, 0] - J[Dynamic.Mission.PROPELLER_TIP_SPEED, - Dynamic.Mission.VELOCITY] = dspeed_dv - J[Dynamic.Mission.PROPELLER_TIP_SPEED, - Dynamic.Mission.SPEED_OF_SOUND] = dspeed_ds - J[Dynamic.Mission.PROPELLER_TIP_SPEED, - Aircraft.Engine.PROPELLER_TIP_MACH_MAX] = dspeed_dmm - J[Dynamic.Mission.PROPELLER_TIP_SPEED, - Aircraft.Engine.PROPELLER_TIP_SPEED_MAX] = dspeed_dsm - - rpm_fact = (diam * math.pi / 60) + J['propeller_tip_speed_limit', Dynamic.Mission.VELOCITY] = dspeed_dv + J['propeller_tip_speed_limit', Dynamic.Mission.SPEED_OF_SOUND] = dspeed_ds + J['propeller_tip_speed_limit', Aircraft.Engine.PROPELLER_TIP_MACH_MAX] = ( + dspeed_dmm + ) + J['propeller_tip_speed_limit', Aircraft.Engine.PROPELLER_TIP_SPEED_MAX] = ( + dspeed_dsm + ) - J['rpm', - Dynamic.Mission.VELOCITY] = dspeed_dv / rpm_fact - J['rpm', - Dynamic.Mission.SPEED_OF_SOUND] = dspeed_ds / rpm_fact - J['rpm', - Aircraft.Engine.PROPELLER_TIP_MACH_MAX] = dspeed_dmm / rpm_fact - J['rpm', - Aircraft.Engine.PROPELLER_TIP_SPEED_MAX] = dspeed_dsm / rpm_fact + J[Dynamic.Mission.PROPELLER_TIP_SPEED, Dynamic.Mission.RPM] = ( + diam * math.pi / 60 + ) - J['rpm', Aircraft.Engine.PROPELLER_DIAMETER] = - \ - 60 * prop_tip_speed / (math.pi * diam**2) + J[Dynamic.Mission.PROPELLER_TIP_SPEED, Aircraft.Engine.PROPELLER_DIAMETER] = ( + rpm * math.pi / 60 + ) class OutMachs(om.ExplicitComponent): - """This utility sets up relations among helical Mach, free stream Mach and propeller tip Mach. + """ + This utility sets up relations among helical Mach, free stream Mach and propeller tip Mach. helical_mach = sqrt(mach^2 + tip_mach^2). It computes the value of one from the inputs of the other two. """ @@ -253,8 +242,9 @@ def setup(self): units="unitless", desc="helical Mach number", ) - self.declare_partials("helical_mach", [ - "tip_mach", "mach"], rows=arange, cols=arange) + self.declare_partials( + "helical_mach", ["tip_mach", "mach"], rows=arange, cols=arange + ) elif out_type is OutMachType.MACH: self.add_input( "tip_mach", @@ -274,8 +264,9 @@ def setup(self): units="unitless", desc="Mach number", ) - self.declare_partials("mach", [ - "tip_mach", "helical_mach"], rows=arange, cols=arange) + self.declare_partials( + "mach", ["tip_mach", "helical_mach"], rows=arange, cols=arange + ) elif out_type is OutMachType.TIP_MACH: self.add_input( "mach", @@ -295,8 +286,9 @@ def setup(self): units="unitless", desc="tip Mach number of a blade", ) - self.declare_partials("tip_mach", [ - "mach", "helical_mach"], rows=arange, cols=arange) + self.declare_partials( + "tip_mach", ["mach", "helical_mach"], rows=arange, cols=arange + ) def compute(self, inputs, outputs): out_type = self.options["output_mach_type"] @@ -320,23 +312,30 @@ def compute_partials(self, inputs, J): if out_type is OutMachType.HELICAL_MACH: mach = inputs["mach"] tip_mach = inputs["tip_mach"] - J["helical_mach", "mach"] = mach/np.sqrt(mach * mach + tip_mach * tip_mach) - J["helical_mach", "tip_mach"] = tip_mach / \ - np.sqrt(mach * mach + tip_mach * tip_mach) + J["helical_mach", "mach"] = mach / np.sqrt( + mach * mach + tip_mach * tip_mach + ) + J["helical_mach", "tip_mach"] = tip_mach / np.sqrt( + mach * mach + tip_mach * tip_mach + ) elif out_type is OutMachType.MACH: tip_mach = inputs["tip_mach"] helical_mach = inputs["helical_mach"] - J["mach", "helical_mach"] = helical_mach / \ - np.sqrt(helical_mach * helical_mach - tip_mach * tip_mach) - J["mach", "tip_mach"] = -tip_mach / \ - np.sqrt(helical_mach * helical_mach - tip_mach * tip_mach) + J["mach", "helical_mach"] = helical_mach / np.sqrt( + helical_mach * helical_mach - tip_mach * tip_mach + ) + J["mach", "tip_mach"] = -tip_mach / np.sqrt( + helical_mach * helical_mach - tip_mach * tip_mach + ) elif out_type is OutMachType.TIP_MACH: mach = inputs["mach"] helical_mach = inputs["helical_mach"] - J["tip_mach", "helical_mach"] = helical_mach / \ - np.sqrt(helical_mach * helical_mach - mach * mach) - J["tip_mach", "mach"] = -mach / \ - np.sqrt(helical_mach * helical_mach - mach * mach) + J["tip_mach", "helical_mach"] = helical_mach / np.sqrt( + helical_mach * helical_mach - mach * mach + ) + J["tip_mach", "mach"] = -mach / np.sqrt( + helical_mach * helical_mach - mach * mach + ) class AreaSquareRatio(om.ExplicitComponent): @@ -415,13 +414,13 @@ def initialize(self): def setup(self): nn = self.options['num_nodes'] range = np.arange(nn) - self.add_input("vktas", val=np.zeros(nn), units='knot') + self.add_input("vtas", val=np.zeros(nn), units='ft/s') self.add_input("tipspd", val=np.zeros(nn), units='ft/s') self.add_input("sqa_array", val=np.zeros(nn), units='unitless') self.add_output("equiv_adv_ratio", val=np.zeros(nn), units='unitless') self.declare_partials("equiv_adv_ratio", - ["vktas", "tipspd"], + ["vtas", "tipspd"], rows=range, cols=range) self.declare_partials("equiv_adv_ratio", @@ -430,10 +429,10 @@ def setup(self): def compute(self, inputs, outputs): nn = self.options['num_nodes'] - vktas = inputs["vktas"] + vtas = inputs["vtas"] tipspd = inputs["tipspd"] sqa_array = inputs["sqa_array"] - equiv_adv_ratio = (1.0 - 0.254 * sqa_array) * 5.309 * vktas / tipspd + equiv_adv_ratio = (1.0 - 0.254 * sqa_array) * math.pi * vtas / tipspd smooth = self.options["smooth_zje"] if smooth: @@ -445,42 +444,177 @@ def compute(self, inputs, outputs): def compute_partials(self, inputs, partials): nn = self.options['num_nodes'] - vktas = inputs["vktas"] + vtas = inputs["vtas"] tipspd = inputs["tipspd"] sqa_array = inputs["sqa_array"] - jze = (1.0 - 0.254 * sqa_array) * 5.309 * vktas / tipspd + jze = (1.0 - 0.254 * sqa_array) * math.pi * vtas / tipspd - djze_dsqa = -0.254 * 5.309 * vktas / tipspd - djze_dvktas = (1.0 - 0.254 * sqa_array) * 5.309 / tipspd - djze_dtipspd = -(1.0 - 0.254 * sqa_array) * 5.309 * vktas / tipspd**2 + djze_dsqa = -0.254 * math.pi * vtas / tipspd + djze_dvtas = (1.0 - 0.254 * sqa_array) * math.pi / tipspd + djze_dtipspd = -(1.0 - 0.254 * sqa_array) * math.pi * vtas / tipspd**2 smooth = self.options["smooth_zje"] if smooth: alpha = self.options["alpha"] - djze_dsqa = d_smooth_min(jze, np.ones(nn) * 5.0, alpha) * djze_dsqa - djze_dvktas = d_smooth_min(jze, np.ones(nn) * 5.0, alpha) * djze_dvktas - djze_dtipspd = d_smooth_min(jze, np.ones(nn) * 5.0, alpha) * djze_dtipspd + djze_dsqa = d_smooth_min(jze, np.ones(nn) * 5.0, alpha) * djze_dsqa + djze_dvtas = d_smooth_min(jze, np.ones(nn) * 5.0, alpha) * djze_dvtas + djze_dtipspd = d_smooth_min(jze, np.ones(nn) * 5.0, alpha) * djze_dtipspd else: djze_dsqa = np.piecewise(jze, [jze < 5, jze >= 5], [1, 0]) * djze_dsqa - djze_dvktas = np.piecewise(jze, [jze < 5, jze >= 5], [1, 0]) * djze_dvktas + djze_dvtas = np.piecewise(jze, [jze < 5, jze >= 5], [1, 0]) * djze_dvtas djze_dtipspd = np.piecewise(jze, [jze < 5, jze >= 5], [1, 0]) * djze_dtipspd partials["equiv_adv_ratio", "sqa_array"] = djze_dsqa - partials["equiv_adv_ratio", "vktas"] = djze_dvktas + partials["equiv_adv_ratio", "vtas"] = djze_dvtas partials["equiv_adv_ratio", "tipspd"] = djze_dtipspd -class InstallLoss(om.Group): +class AreaSquareRatio(om.ExplicitComponent): """ - Compute installation loss + Compute the area ratio nacelle and propeller with a maximum 0.5. + """ + + def initialize(self): + self.options.declare("num_nodes", types=int) + self.options.declare('smooth_sqa', default=True, types=bool) + self.options.declare('alpha', default=100.0, types=float) + + def setup(self): + nn = self.options["num_nodes"] + arange = np.arange(self.options["num_nodes"]) + self.add_input("DiamNac", val=0.0, units='ft') + self.add_input("DiamProp", val=0.0, units='ft') + + self.add_output('sqa_array', val=np.zeros(nn), units='unitless') + + self.declare_partials("sqa_array", + [ + "DiamNac", + "DiamProp", + ], + rows=arange, cols=np.zeros(nn)) + + def compute(self, inputs, outputs): + nn = self.options["num_nodes"] + diamNac = inputs["DiamNac"] + diamProp = inputs["DiamProp"] + sqa = diamNac**2 / diamProp**2 + + smooth = self.options["smooth_sqa"] + if smooth: + alpha = self.options['alpha'] + sqa = smooth_min(sqa, 0.50, alpha) + else: + sqa = np.minimum(sqa, 0.50) + outputs["sqa_array"] = np.ones(nn) * sqa + + def compute_partials(self, inputs, partials): + diamNac = inputs["DiamNac"] + diamProp = inputs["DiamProp"] + sqa = diamNac**2 / diamProp**2 + + dSQA_dNacDiam = 2 * diamNac / diamProp**2 + dSQA_dPropDiam = -2 * diamNac**2 / diamProp**3 + + smooth = self.options["smooth_sqa"] + if smooth: + alpha = self.options['alpha'] + dSQA_dNacDiam = d_smooth_min(sqa, 0.50, alpha) * dSQA_dNacDiam + dSQA_dPropDiam = d_smooth_min(sqa, 0.50, alpha) * dSQA_dPropDiam + else: + dSQA_dNacDiam = np.piecewise( + sqa, [sqa < 0.5, sqa >= 0.5], [1, 0]) * dSQA_dNacDiam + dSQA_dPropDiam = np.piecewise( + sqa, [sqa < 0.5, sqa >= 0.5], [1, 0]) * dSQA_dPropDiam + partials['sqa_array', "DiamNac"] = dSQA_dNacDiam + partials['sqa_array', "DiamProp"] = dSQA_dPropDiam + + +class AdvanceRatio(om.ExplicitComponent): + """ + Compute the advance ratio jze with a maximum 5.0. """ def initialize(self): self.options.declare( 'num_nodes', types=int, default=1, desc='Number of nodes to be evaluated in the RHS') + self.options.declare('smooth_zje', default=True, types=bool) + self.options.declare('alpha', default=100.0, types=float) + + def setup(self): + nn = self.options['num_nodes'] + range = np.arange(nn) + self.add_input("vtas", val=np.zeros(nn), units='ft/s') + self.add_input("tipspd", val=np.zeros(nn), units='ft/s') + self.add_input("sqa_array", val=np.zeros(nn), units='unitless') + self.add_output("equiv_adv_ratio", val=np.zeros(nn), units='unitless') + + self.declare_partials("equiv_adv_ratio", + ["vtas", "tipspd"], + rows=range, cols=range) + + self.declare_partials("equiv_adv_ratio", + ["sqa_array"], + rows=range, cols=range) + + def compute(self, inputs, outputs): + nn = self.options['num_nodes'] + vtas = inputs["vtas"] + tipspd = inputs["tipspd"] + sqa_array = inputs["sqa_array"] + equiv_adv_ratio = (1.0 - 0.254 * sqa_array) * math.pi * vtas / tipspd + + smooth = self.options["smooth_zje"] + if smooth: + alpha = self.options['alpha'] + jze = smooth_min(equiv_adv_ratio, np.ones(nn) * 5.0, alpha) + else: + jze = np.minimum(equiv_adv_ratio, np.ones(nn) * 5.0) + outputs["equiv_adv_ratio"] = jze + + def compute_partials(self, inputs, partials): + nn = self.options['num_nodes'] + vtas = inputs["vtas"] + tipspd = inputs["tipspd"] + sqa_array = inputs["sqa_array"] + jze = (1.0 - 0.254 * sqa_array) * math.pi * vtas / tipspd + + djze_dsqa = -0.254 * math.pi * vtas / tipspd + djze_dvtas = (1.0 - 0.254 * sqa_array) * math.pi / tipspd + djze_dtipspd = -(1.0 - 0.254 * sqa_array) * math.pi * vtas / tipspd**2 + + smooth = self.options["smooth_zje"] + if smooth: + alpha = self.options["alpha"] + djze_dsqa = d_smooth_min(jze, np.ones(nn) * 5.0, alpha) * djze_dsqa + djze_dvtas = d_smooth_min(jze, np.ones(nn) * 5.0, alpha) * djze_dvtas + djze_dtipspd = d_smooth_min(jze, np.ones(nn) * 5.0, alpha) * djze_dtipspd + else: + djze_dsqa = np.piecewise(jze, [jze < 5, jze >= 5], [1, 0]) * djze_dsqa + djze_dvtas = np.piecewise(jze, [jze < 5, jze >= 5], [1, 0]) * djze_dvtas + djze_dtipspd = np.piecewise(jze, [jze < 5, jze >= 5], [1, 0]) * djze_dtipspd + partials["equiv_adv_ratio", "sqa_array"] = djze_dsqa + partials["equiv_adv_ratio", "vtas"] = djze_dvtas + partials["equiv_adv_ratio", "tipspd"] = djze_dtipspd + + +class InstallLoss(om.Group): + """ + Compute installation loss + """ + + def initialize(self): + self.options.declare( + 'num_nodes', + types=int, + default=1, + desc='Number of nodes to be evaluated in the RHS', + ) self.options.declare( - 'aviary_options', types=AviaryValues, - desc='collection of Aircraft/Mission specific options') + 'aviary_options', + types=AviaryValues, + desc='collection of Aircraft/Mission specific options', + ) def setup(self): nn = self.options['num_nodes'] @@ -495,15 +629,16 @@ def setup(self): self.add_subsystem( name='zje_comp', subsys=AdvanceRatio(num_nodes=nn, smooth_zje=True), - promotes_inputs=["sqa_array", ("vktas", Dynamic.Mission.VELOCITY), + promotes_inputs=["sqa_array", ("vtas", Dynamic.Mission.VELOCITY), ("tipspd", Dynamic.Mission.PROPELLER_TIP_SPEED)], promotes_outputs=["equiv_adv_ratio"], ) self.blockage_factor_interp = self.add_subsystem( "blockage_factor_interp", - om.MetaModelStructuredComp(method="2D-slinear", - extrapolate=True, vec_size=nn), + om.MetaModelStructuredComp( + method="2D-slinear", extrapolate=True, vec_size=nn + ), promotes_inputs=["sqa_array", "equiv_adv_ratio"], promotes_outputs=[ "blockage_factor", @@ -521,7 +656,7 @@ def setup(self): self.blockage_factor_interp.add_input( "equiv_adv_ratio", 0.0, - training_data=[0., 0.5, 1.0, 2.0, 3.0, 4.0, 5.0], + training_data=[0.0, 0.5, 1.0, 2.0, 3.0, 4.0, 5.0], units="unitless", desc="square of DiamNac vs DiamProp", ) @@ -532,16 +667,18 @@ def setup(self): units="unitless", desc="blockage factor", training_data=np.array( - [[1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0], - [0.992, 0.991, 0.988, 0.983, 0.976, 0.970, 0.963], - [0.986, 0.982, 0.977, 0.965, 0.953, 0.940, 0.927], - [0.979, 0.974, 0.967, 0.948, 0.929, 0.908, 0.887], - [0.972, 0.965, 0.955, 0.932, 0.905, 0.872, 0.835], - [0.964, 0.954, 0.943, 0.912, 0.876, 0.834, 0.786], - [0.955, 0.943, 0.928, 0.892, 0.848, 0.801, 0.751], - [0.948, 0.935, 0.917, 0.872, 0.820, 0.763, 0.706], - [0.940, 0.924, 0.902, 0.848, 0.790, 0.726, 0.662], - [0.904, 0.875, 0.835, 0.740, 0.655, 0.560, 0.464]] + [ + [1.0, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0], + [0.992, 0.991, 0.988, 0.983, 0.976, 0.970, 0.963], + [0.986, 0.982, 0.977, 0.965, 0.953, 0.940, 0.927], + [0.979, 0.974, 0.967, 0.948, 0.929, 0.908, 0.887], + [0.972, 0.965, 0.955, 0.932, 0.905, 0.872, 0.835], + [0.964, 0.954, 0.943, 0.912, 0.876, 0.834, 0.786], + [0.955, 0.943, 0.928, 0.892, 0.848, 0.801, 0.751], + [0.948, 0.935, 0.917, 0.872, 0.820, 0.763, 0.706], + [0.940, 0.924, 0.902, 0.848, 0.790, 0.726, 0.662], + [0.904, 0.875, 0.835, 0.740, 0.655, 0.560, 0.464], + ] ), ) @@ -562,28 +699,32 @@ class PropellerPerformance(om.Group): """ Computation of propeller thrust coefficient based on the Hamilton Standard model or a user provided propeller map. Note that a propeller map allows either the helical Mach number or - free stream Mach number as input. This infomation will be detected automatically when the + free stream Mach number as input. This infomation will be detected automatically when the propeller map is loaded into memory. The installation loss factor is either a user input or computed internally. """ def initialize(self): self.options.declare( - 'num_nodes', types=int, default=1, - desc='Number of nodes to be evaluated in the RHS') - self.options.declare( - 'input_rpm', types=bool, default=False, - desc='If True, the input is RPM, otherwise RPM is set by propeller limits') + 'num_nodes', + types=int, + default=1, + desc='Number of nodes to be evaluated in the RHS', + ) - self.options.declare('aviary_options', types=AviaryValues, - desc='collection of Aircraft/Mission specific options') + self.options.declare( + 'aviary_options', + types=AviaryValues, + desc='collection of Aircraft/Mission specific options', + ) def setup(self): options = self.options nn = options['num_nodes'] aviary_options = options['aviary_options'] - # TODO options are lists here when using full Aviary problem - need further investigation + # TODO options are lists here when using full Aviary problem - need + # further investigation compute_installation_loss = aviary_options.get_val( Aircraft.Engine.COMPUTE_PROPELLER_INSTALLATION_LOSS ) @@ -594,32 +735,12 @@ def setup(self): if isinstance(use_propeller_map, (list, np.ndarray)): use_propeller_map = use_propeller_map[0] - if self.options['input_rpm']: - # compute the propeller tip speed based on the input RPM and diameter of the propeller - # NOTE allows for violation of tip speed limits - self.add_subsystem( - 'compute_tip_speed', - om.ExecComp( - 'prop_tip_speed = diameter * rpm * pi / 60.', - prop_tip_speed={'units': "ft/s", 'shape': nn}, - diameter={'val': 0., 'units': "ft"}, - rpm={'units': "rpm", 'shape': nn}, - has_diag_partials=True, - ), - promotes_inputs=[ - 'rpm', # TODO this should be in dynamic - ('diameter', Aircraft.Engine.PROPELLER_DIAMETER), - ], - promotes_outputs=[ - ('prop_tip_speed', Dynamic.Mission.PROPELLER_TIP_SPEED)], - ) - - else: - self.add_subsystem( - 'tip_speed_limit', - subsys=TipSpeedLimit(num_nodes=nn), - promotes=['*'] - ) + # compute the propeller tip speed based on the input RPM and diameter of the propeller + # NOTE allows for violation of tip speed limits + # TODO provide warning to user when max tip speeds are violated + self.add_subsystem( + 'compute_tip_speed', subsys=TipSpeed(num_nodes=nn), promotes=['*'] + ) if compute_installation_loss: self.add_subsystem( @@ -635,7 +756,8 @@ def setup(self): ) else: self.set_input_defaults( - 'install_loss_factor', val=np.ones(nn), units="unitless") + 'install_loss_factor', val=np.ones(nn), units="unitless" + ) self.add_subsystem( name='pre_hamilton_standard', @@ -652,20 +774,20 @@ def setup(self): "power_coefficient", "advance_ratio", "tip_mach", - "density_ratio", + # "density_ratio", ], ) if use_propeller_map: prop_model = PropellerMap('prop', aviary_options) - prop_file_path = aviary_options.get_val( - Aircraft.Engine.PROPELLER_DATA_FILE) + prop_file_path = aviary_options.get_val(Aircraft.Engine.PROPELLER_DATA_FILE) mach_type = prop_model.read_and_set_mach_type(prop_file_path) if mach_type == OutMachType.HELICAL_MACH: self.add_subsystem( name='selectedMach', subsys=OutMachs( - num_nodes=nn, output_mach_type=OutMachType.HELICAL_MACH), + num_nodes=nn, output_mach_type=OutMachType.HELICAL_MACH + ), promotes_inputs=[("mach", Dynamic.Mission.MACH), "tip_mach"], promotes_outputs=[("helical_mach", "selected_mach")], ) @@ -678,7 +800,9 @@ def setup(self): selected_mach={'units': 'unitless', 'shape': nn}, has_diag_partials=True, ), - promotes_inputs=[("mach", Dynamic.Mission.MACH),], + promotes_inputs=[ + ("mach", Dynamic.Mission.MACH), + ], promotes_outputs=["selected_mach"], ) propeller = prop_model.build_propeller_interpolator(nn, aviary_options) @@ -692,11 +816,13 @@ def setup(self): ], promotes_outputs=[ "thrust_coefficient", - ]) + ], + ) # propeller map has taken compresibility into account. - self.set_input_defaults('comp_tip_loss_factor', - np.linspace(1.0, 1.0, nn), units='unitless') + self.set_input_defaults( + 'comp_tip_loss_factor', np.linspace(1.0, 1.0, nn), units='unitless' + ) else: self.add_subsystem( name='hamilton_standard', @@ -712,7 +838,8 @@ def setup(self): promotes_outputs=[ "thrust_coefficient", "comp_tip_loss_factor", - ]) + ], + ) self.add_subsystem( name='post_hamilton_standard', @@ -722,7 +849,7 @@ def setup(self): "comp_tip_loss_factor", Dynamic.Mission.PROPELLER_TIP_SPEED, Aircraft.Engine.PROPELLER_DIAMETER, - "density_ratio", + Dynamic.Mission.DENSITY, 'install_loss_factor', "advance_ratio", "power_coefficient", @@ -732,4 +859,5 @@ def setup(self): Dynamic.Mission.THRUST, "propeller_efficiency", "install_efficiency", - ]) + ], + ) diff --git a/aviary/subsystems/propulsion/test/test_custom_engine_model.py b/aviary/subsystems/propulsion/test/test_custom_engine_model.py index 9577ce5fe..91db9831e 100644 --- a/aviary/subsystems/propulsion/test/test_custom_engine_model.py +++ b/aviary/subsystems/propulsion/test/test_custom_engine_model.py @@ -244,124 +244,6 @@ def test_custom_engine(self): assert_near_equal(float(prob.get_val('traj.cruise.rhs_all.y')), 4.0, tol) -@use_tempdirs -class TurbopropTest(unittest.TestCase): - """ - Test integrating turboprop component with full AviaryProblem - """ - - def test_turboprop(self): - phase_info = { - 'pre_mission': { - 'include_takeoff': False, - 'external_subsystems': [], - 'optimize_mass': True, - }, - 'cruise': { - "subsystem_options": {"core_aerodynamics": {"method": "computed"}}, - "user_options": { - "optimize_mach": False, - "optimize_altitude": False, - "polynomial_control_order": 1, - "num_segments": 2, - "order": 3, - "solve_for_distance": False, - "initial_mach": (0.76, "unitless"), - "final_mach": (0.76, "unitless"), - "mach_bounds": ((0.7, 0.78), "unitless"), - "initial_altitude": (35000.0, "ft"), - "final_altitude": (35000.0, "ft"), - "altitude_bounds": ((23000.0, 38000.0), "ft"), - "throttle_enforcement": "boundary_constraint", - "fix_initial": False, - "constrain_final": False, - "fix_duration": False, - "initial_bounds": ((0.0, 0.0), "min"), - "duration_bounds": ((30.0, 60.0), "min"), - }, - "initial_guesses": {"time": ([0, 30], "min")}, - }, - 'post_mission': { - 'include_landing': False, - 'external_subsystems': [], - }, - } - - engine_filepath = get_path('models/engines/turboshaft_4465hp.deck') - options = get_option_defaults() - options.set_val(Aircraft.Engine.DATA_FILE, engine_filepath) - options.set_val(Aircraft.Engine.NUM_ENGINES, 2) - options.set_val(Aircraft.Engine.PROPELLER_DIAMETER, 10, units='ft') - - options.set_val( - Aircraft.Engine.COMPUTE_PROPELLER_INSTALLATION_LOSS, - val=True, - units='unitless', - ) - options.set_val(Aircraft.Engine.NUM_PROPELLER_BLADES, val=4, units='unitless') - - engine = TurbopropModel(options=options) - - prob = AviaryProblem(reports=True) - - # Load aircraft and options data from user - # Allow for user overrides here - prob.load_inputs( - "models/test_aircraft/aircraft_for_bench_FwFm.csv", - phase_info, - engine_builders=[engine], - ) - - # Preprocess inputs - prob.check_and_preprocess_inputs() - - prob.add_pre_mission_systems() - - prob.add_phases() - - prob.add_post_mission_systems() - - # Link phases and variables - prob.link_phases() - - prob.add_driver("SLSQP", max_iter=20) - - prob.add_design_variables() - - prob.add_objective('fuel_burned') - - prob.setup() - - prob.set_initial_guesses() - - prob.set_val( - f'traj.cruise.rhs_all.{Aircraft.Engine.PROPELLER_TIP_SPEED_MAX}', - 710.0, - units='ft/s', - ) - prob.set_val( - f'traj.cruise.rhs_all.{Aircraft.Engine.PROPELLER_DIAMETER}', 10, units='ft' - ) - prob.set_val( - f'traj.cruise.rhs_all.{Aircraft.Engine.PROPELLER_ACTIVITY_FACTOR}', - 150.0, - units='unitless', - ) - prob.set_val( - ( - 'traj.cruise.rhs_all.' - f'{Aircraft.Engine.PROPELLER_INTEGRATED_LIFT_COEFFICIENT}' - ), - 0.5, - units='unitless', - ) - - prob.set_solver_print(level=0) - - # and run mission - dm.run_problem(prob, run_driver=True, simulate=False, make_plots=True) - - if __name__ == '__main__': unittest.main() # test = TurbopropTest() diff --git a/aviary/subsystems/propulsion/test/test_hamilton_standard.py b/aviary/subsystems/propulsion/test/test_hamilton_standard.py index 5434eea63..515ce449b 100644 --- a/aviary/subsystems/propulsion/test/test_hamilton_standard.py +++ b/aviary/subsystems/propulsion/test/test_hamilton_standard.py @@ -1,5 +1,5 @@ import unittest - +import numpy as np import openmdao.api as om from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal @@ -10,6 +10,7 @@ from aviary.variable_info.variables import Aircraft, Dynamic from aviary.variable_info.options import get_option_defaults from aviary.variable_info.variables import Aircraft, Dynamic +from aviary.constants import RHO_SEA_LEVEL_ENGLISH class PreHamiltonStandardTest(unittest.TestCase): @@ -49,12 +50,14 @@ def test_preHS(self): tol = 5e-4 assert_near_equal(prob.get_val("power_coefficient"), [0.3871, 0.3147, 0.2815], tolerance=tol) - assert_near_equal(prob.get_val("advance_ratio"), - [0.4494, 0.4194, 0.3932], tolerance=tol) - assert_near_equal(prob.get_val("tip_mach"), - [1.05826, 1.1338, 1.3290], tolerance=tol) - assert_near_equal(prob.get_val("density_ratio"), - [1.0001, 1.0001, 0.4482], tolerance=tol) + assert_near_equal( + prob.get_val("advance_ratio"), + [0.44879895, 0.41887902, 0.39269908], + tolerance=tol, + ) + assert_near_equal( + prob.get_val("tip_mach"), [0.6270004, 0.67178614, 0.78743671], tolerance=tol + ) partial_data = prob.check_partials( out_stream=None, @@ -149,7 +152,11 @@ def test_postHS(self): prob.set_val("advance_ratio", [0.4494, 0.4194, 0.3932], units="unitless") prob.set_val(Dynamic.Mission.PROPELLER_TIP_SPEED, [700.0, 750.0, 800.0], units="ft/s") - prob.set_val("density_ratio", [1.0001, 1.0001, 0.4482], units="unitless") + prob.set_val( + Dynamic.Mission.DENSITY, + np.array([1.0001, 1.0001, 0.4482]) * RHO_SEA_LEVEL_ENGLISH, + units="slug/ft**3", + ) prob.set_val(Aircraft.Engine.PROPELLER_DIAMETER, 10.0, units="ft") prob.set_val("thrust_coefficient", [0.2765, 0.2052, 0.1158], units="unitless") prob.set_val("install_loss_factor", [0.0133, 0.0200, 0.0325], units="unitless") @@ -182,3 +189,6 @@ def test_postHS(self): if __name__ == "__main__": unittest.main() + # test = HamiltonStandardTest() + # test.setUp() + # test.test_HS() diff --git a/aviary/subsystems/propulsion/test/test_propeller_performance.py b/aviary/subsystems/propulsion/test/test_propeller_performance.py index 572dde581..ecd6d6c3f 100644 --- a/aviary/subsystems/propulsion/test/test_propeller_performance.py +++ b/aviary/subsystems/propulsion/test/test_propeller_performance.py @@ -7,7 +7,7 @@ from aviary.subsystems.atmosphere.atmosphere import Atmosphere from aviary.subsystems.propulsion.propeller.propeller_performance import ( - OutMachs, PropellerPerformance, TipSpeedLimit, AreaSquareRatio, AdvanceRatio + OutMachs, PropellerPerformance, TipSpeed, AreaSquareRatio, AdvanceRatio ) from aviary.variable_info.enums import OutMachType from aviary.variable_info.variables import Aircraft, Dynamic, Settings @@ -43,7 +43,7 @@ ) XFT = np.array( [1.0, 1.0, 0.9976, 1.0, 1.0, 1.0, 1.0, 1.0, 1.0, - 1.0, 1.0, 1.0, 1.0, 1.0, 0.9976, 1.0, 1.0, 1.0,] + 1.0, 1.0, 1.0, 1.0, 1.0, 0.9976, 1.0, 1.0, 1.0,] ) # CTX = np.array([0.27651, 0.20518, 0.13062, 0.10236, 0.10236, 0.19331, # 0.10189, 0.10189, 0.18123, 0.08523, 0.06463, 0.02800]) @@ -254,6 +254,11 @@ def test_case_0_1_2(self): prob = self.prob prob.set_val(Dynamic.Mission.ALTITUDE, [0.0, 0.0, 25000.0], units="ft") prob.set_val(Dynamic.Mission.VELOCITY, [0.10, 125.0, 300.0], units="knot") + prob.set_val( + Dynamic.Mission.RPM, + [1455.13090827, 1455.13090827, 1455.13090827], + units='rpm', + ) prob.set_val(Dynamic.Mission.SHAFT_POWER, [1850.0, 1850.0, 900.0], units="hp") prob.set_val(Aircraft.Engine.PROPELLER_TIP_MACH_MAX, 1.0, units="unitless") prob.set_val(Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, 800.0, units="ft/s") @@ -294,9 +299,15 @@ def test_case_3_4_5(self): prob.set_val(Dynamic.Mission.ALTITUDE, [10000.0, 10000.0, 0.0], units="ft") prob.set_val(Dynamic.Mission.VELOCITY, [200.0, 200.0, 50.0], units="knot") prob.set_val(Dynamic.Mission.SHAFT_POWER, [1000.0, 1000.0, 1250.0], units="hp") + prob.set_val( + Dynamic.Mission.RPM, + [1225.02, 1225.02, 1225.02], + units='rpm', + ) prob.set_val(Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, 769.70, units="ft/s") prob.run_model() + self.compare_results(case_idx_begin=3, case_idx_end=5) partial_data = prob.check_partials( @@ -336,6 +347,11 @@ def test_case_6_7_8(self): prob.set_val(Dynamic.Mission.ALTITUDE, [10000.0, 10000.0, 0.0], units="ft") prob.set_val(Dynamic.Mission.VELOCITY, [200.0, 200.0, 50.0], units="knot") prob.set_val(Dynamic.Mission.SHAFT_POWER, [1000.0, 1000.0, 1250.0], units="hp") + prob.set_val( + Dynamic.Mission.RPM, + [1193.66207319, 1193.66207319, 1193.66207319], + units='rpm', + ) prob.set_val(Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, 750.0, units="ft/s") prob.run_model() @@ -368,6 +384,12 @@ def test_case_9_10_11(self): prob.set_val(Dynamic.Mission.ALTITUDE, [10000.0, 10000.0, 10000.0], units="ft") prob.set_val(Dynamic.Mission.VELOCITY, [200.0, 200.0, 200.0], units="knot") prob.set_val(Dynamic.Mission.SHAFT_POWER, [900.0, 750.0, 500.0], units="hp") + prob.set_val( + Dynamic.Mission.RPM, + [1193.66207319, 1193.66207319, 1193.66207319], + units='rpm', + ) + prob.set_val(Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, 750.0, units="ft/s") prob.run_model() @@ -400,6 +422,11 @@ def test_case_12_13_14(self): prob.set_val(Dynamic.Mission.ALTITUDE, [0.0, 0.0, 25000.0], units="ft") prob.set_val(Dynamic.Mission.VELOCITY, [0.10, 125.0, 300.0], units="knot") prob.set_val(Dynamic.Mission.SHAFT_POWER, [1850.0, 1850.0, 900.0], units="hp") + prob.set_val( + Dynamic.Mission.RPM, + [1455.1309082687574, 1455.1309082687574, 1156.4081529986502], + units='rpm', + ) prob.set_val(Aircraft.Engine.PROPELLER_TIP_MACH_MAX, 0.8, units="unitless") prob.set_val(Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, 800.0, units="ft/s") @@ -440,6 +467,11 @@ def test_case_15_16_17(self): prob.set_val(Dynamic.Mission.ALTITUDE, [10000.0, 10000.0, 0.0], units="ft") prob.set_val(Dynamic.Mission.VELOCITY, [200.0, 200.0, 50.0], units="knot") prob.set_val(Dynamic.Mission.SHAFT_POWER, [1000.0, 1000.0, 1250.0], units="hp") + prob.set_val( + Dynamic.Mission.RPM, + [1225.0155969783186, 1225.0155969783186, 1225.0155969783186], + units='rpm', + ) prob.set_val(Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, 769.70, units="ft/s") prob.run_model() @@ -477,13 +509,19 @@ def test_helical_mach(self): prob.set_val("tip_mach", val=[0.5, 0.7], units="unitless") prob.run_model() y = prob.get_val("helical_mach") - y_exact = np.sqrt([0.5*0.5 + 0.5*0.5, 0.7*0.7 + 0.7*0.7]) + y_exact = np.sqrt([0.5 * 0.5 + 0.5 * 0.5, 0.7 * 0.7 + 0.7 * 0.7]) assert_near_equal(y, y_exact, tolerance=tol) partial_data = prob.check_partials( - out_stream=None, compact_print=True, show_only_incorrect=True, form='central', method="fd", - minimum_step=1e-12, abs_err_tol=5.0E-4, rel_err_tol=5.0E-5) + out_stream=None, + compact_print=True, + show_only_incorrect=True, + form='central', + method="fd", + minimum_step=1e-12, + abs_err_tol=5.0E-4, + rel_err_tol=5.0E-5) assert_check_partials(partial_data, atol=1e-4, rtol=1e-4) def test_mach(self): @@ -500,13 +538,19 @@ def test_mach(self): prob.set_val("tip_mach", val=[0.5, 0.4], units="unitless") prob.run_model() y = prob.get_val("mach") - y_exact = np.sqrt([0.7*0.7 - 0.5*0.5, 0.8*0.8 - 0.4*0.4]) + y_exact = np.sqrt([0.7 * 0.7 - 0.5 * 0.5, 0.8 * 0.8 - 0.4 * 0.4]) assert_near_equal(y, y_exact, tolerance=tol) partial_data = prob.check_partials( - out_stream=None, compact_print=True, show_only_incorrect=True, form='central', method="fd", - minimum_step=1e-12, abs_err_tol=5.0E-4, rel_err_tol=5.0E-5) + out_stream=None, + compact_print=True, + show_only_incorrect=True, + form='central', + method="fd", + minimum_step=1e-12, + abs_err_tol=5.0E-4, + rel_err_tol=5.0E-5) assert_check_partials(partial_data, atol=1e-4, rtol=1e-4) def test_tip_mach(self): @@ -523,13 +567,19 @@ def test_tip_mach(self): prob.set_val("mach", val=[0.5, 0.4], units="unitless") prob.run_model() y = prob.get_val("tip_mach") - y_exact = np.sqrt([0.7*0.7 - 0.5*0.5, 0.8*0.8 - 0.4*0.4]) + y_exact = np.sqrt([0.7 * 0.7 - 0.5 * 0.5, 0.8 * 0.8 - 0.4 * 0.4]) assert_near_equal(y, y_exact, tolerance=tol) partial_data = prob.check_partials( - out_stream=None, compact_print=True, show_only_incorrect=True, form='central', method="fd", - minimum_step=1e-12, abs_err_tol=5.0E-4, rel_err_tol=5.0E-5) + out_stream=None, + compact_print=True, + show_only_incorrect=True, + form='central', + method="fd", + minimum_step=1e-12, + abs_err_tol=5.0E-4, + rel_err_tol=5.0E-5) assert_check_partials(partial_data, atol=1e-4, rtol=1e-4) @@ -544,7 +594,7 @@ def test_tipspeed(self): prob = om.Problem() prob.model.add_subsystem( "group", - TipSpeedLimit(num_nodes=3), + TipSpeed(num_nodes=3), promotes=["*"], ) prob.setup() @@ -558,10 +608,8 @@ def test_tipspeed(self): prob.run_model() - tip_speed = prob.get_val(Dynamic.Mission.PROPELLER_TIP_SPEED, units='ft/s') - rpm = prob.get_val('rpm', units='rpm') + tip_speed = prob.get_val('propeller_tip_speed_limit', units='ft/s') assert_near_equal(tip_speed, [800, 800, 635.7686], tolerance=tol) - assert_near_equal(rpm, [1455.1309, 1455.1309, 1156.4082], tolerance=tol) partial_data = prob.check_partials( out_stream=None, @@ -653,14 +701,14 @@ def test_zje_1(self): promotes=["*"], ) prob.setup(force_alloc_complex=True) - prob.set_val("vktas", val=[0.1, 125., 300., 1000.], units='knot') + prob.set_val("vtas", val=[0.1, 125., 300., 1000.], units='knot') prob.set_val("tipspd", val=[800., 800., 750., 500.], units='ft/s') prob.set_val("sqa_array", val=[0.0756, 0.0756, 0.0756, 1.0], units='unitless') prob.run_model() equiv_adv_ratio = prob.get_val("equiv_adv_ratio", units='unitless') assert_near_equal(equiv_adv_ratio, [ - 0.000650881807, 0.813602259, 2.08282178, 5], tolerance=1e-5) + 6.50074004e-04, 8.12592505e-01, 2.08023681e+00, 5.0], tolerance=1e-5) partial_data = prob.check_partials(out_stream=None, method="cs") assert_check_partials(partial_data, atol=1e-12, rtol=1e-12) @@ -673,14 +721,17 @@ def test_zje_2(self): promotes=["*"], ) prob.setup(force_alloc_complex=True) - prob.set_val("vktas", val=[0.1, 125., 300., 1000.], units='knot') + prob.set_val("vtas", val=[0.1, 125., 300., 1000.], units='knot') prob.set_val("tipspd", val=[800., 800., 750., 500.], units='ft/s') prob.set_val("sqa_array", val=[0.0756, 0.0756, 0.0756, 1.0], units='unitless') prob.run_model() equiv_adv_ratio = prob.get_val("equiv_adv_ratio", units='unitless') - assert_near_equal(equiv_adv_ratio, [ - 0.000650881807, 0.813602259, 2.08282178, 5], tolerance=1e-5) + assert_near_equal( + equiv_adv_ratio, + [6.50074004e-04, 8.12592505e-01, 2.08023681e+00, 5.0], + tolerance=1e-5 + ) partial_data = prob.check_partials(out_stream=None, method="cs") assert_check_partials(partial_data, atol=1e-12, rtol=1e-12) @@ -688,3 +739,6 @@ def test_zje_2(self): if __name__ == "__main__": unittest.main() + # test = PropellerPerformanceTest() + # test.setUp() + # test.test_case_3_4_5() diff --git a/aviary/subsystems/propulsion/test/test_turboprop_model.py b/aviary/subsystems/propulsion/test/test_turboprop_model.py index eacd6595e..01ddcbdcd 100644 --- a/aviary/subsystems/propulsion/test/test_turboprop_model.py +++ b/aviary/subsystems/propulsion/test/test_turboprop_model.py @@ -5,7 +5,9 @@ from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal from aviary.subsystems.atmosphere.atmosphere import Atmosphere from pathlib import Path +from openmdao.utils.testing_utils import use_tempdirs +from aviary.interface.methods_for_level2 import AviaryProblem from aviary.subsystems.propulsion.turboprop_model import TurbopropModel from aviary.subsystems.propulsion.propeller.propeller_performance import ( PropellerPerformance, @@ -19,6 +21,7 @@ from aviary.subsystems.propulsion.motor.motor_builder import MotorBuilder +@use_tempdirs class TurbopropTest(unittest.TestCase): def setUp(self): self.prob = om.Problem() @@ -50,6 +53,11 @@ def prepare_model( options.set_val(Aircraft.Engine.FLIGHT_IDLE_MIN_FRACTION, 0.08) options.set_val(Aircraft.Engine.GEOPOTENTIAL_ALT, False) options.set_val(Aircraft.Engine.INTERPOLATION_METHOD, 'slinear') + options.set_val( + Aircraft.Engine.FIXED_RPM, + 1455.13090827, + units='rpm', + ) options.set_val( Aircraft.Engine.COMPUTE_PROPELLER_INSTALLATION_LOSS, @@ -126,25 +134,25 @@ def test_case_1(self): ( 223.99923788786057, 37.699999999999996, - 1195.4410168571105, - 1233.1410168571106, - 4983.816421227165, + 1195.4410222483584, + 1233.1410222483585, + 4983.816420783667, -195.79999999999995, ), ( 2239.9923788786077, 136.29999999999967, - 4847.516421227166, - 4983.816421227165, - 4983.816421227165, + 4847.516420783668, + 4983.816420783667, + 4983.816420783667, -643.9999999999998, ), ( 2466.55094358958, 21.30000000000001, - 1833.4755577366554, - 1854.7755577366554, - 1854.7755577366554, + 1834.6578916888234, + 1855.9578916888233, + 1855.9578916888233, -839.7000000000685, ), ] @@ -176,7 +184,9 @@ def test_case_1(self): self.prob.run_model() results = self.get_results() - assert_near_equal(results, truth_vals) + assert_near_equal(results[0], truth_vals[0], tolerance=1.5e-12) + assert_near_equal(results[1], truth_vals[1], tolerance=1.5e-12) + assert_near_equal(results[2], truth_vals[2], tolerance=1.5e-12) # because Hamilton Standard model uses fd method, the following may not be accurate. partial_data = self.prob.check_partials(out_stream=None, form="central") @@ -190,25 +200,25 @@ def test_case_2(self): ( 223.99007751511726, 37.507374999999996, - 1186.6952790705282, - 1224.202654070528, - 4984.168836459296, + 1186.7060713100836, + 1224.2134463100836, + 4984.168016782585, -195.78762499999996, ), ( 2239.9923788786077, 136.29999999999967, - 4847.516421227166, - 4983.816421227165, - 4983.816421227165, + 4847.516420783668, + 4983.816420783667, + 4983.816420783667, -643.9999999999998, ), ( 2466.55094358958, 21.30000000000001, - 1833.4755577366554, - 1854.7755577366554, - 1854.7755577366554, + 1834.6578916888234, + 1855.9578916888233, + 1855.9578916888233, -839.7000000000685, ), ] @@ -230,7 +240,9 @@ def test_case_2(self): self.prob.run_model() results = self.get_results() - assert_near_equal(results, truth_vals) + assert_near_equal(results[0], truth_vals[0], tolerance=1.5e-12) + assert_near_equal(results[1], truth_vals[1], tolerance=1.5e-12) + assert_near_equal(results[2], truth_vals[2], tolerance=1.5e-12) partial_data = self.prob.check_partials(out_stream=None, form="central") assert_check_partials(partial_data, atol=0.15, rtol=0.15) @@ -243,25 +255,25 @@ def test_case_3(self): ( 223.99923788786057, 0.0, - 1195.4410168571105, - 1195.4410168571105, - 4847.516421227166, + 1195.4410222483584, + 1195.4410222483584, + 4847.516420783668, -195.79999999999995, ), ( 2239.9923788786077, 0.0, - 4847.516421227166, - 4847.516421227166, - 4847.516421227166, + 4847.516420783668, + 4847.516420783668, + 4847.516420783668, -643.9999999999998, ), ( 2466.55094358958, 0.0, - 1833.4755577366554, - 1833.4755577366554, - 1833.4755577366554, + 1834.6578916888234, + 1834.6578916888234, + 1834.6578916888234, -839.7000000000685, ), ] @@ -280,7 +292,9 @@ def test_case_3(self): self.prob.run_model() results = self.get_results() - assert_near_equal(results, truth_vals) + assert_near_equal(results[0], truth_vals[0], tolerance=1.5e-12) + assert_near_equal(results[1], truth_vals[1], tolerance=1.5e-12) + assert_near_equal(results[2], truth_vals[2], tolerance=1.5e-12) partial_data = self.prob.check_partials(out_stream=None, form="central") assert_check_partials(partial_data, atol=0.15, rtol=0.15) @@ -309,9 +323,9 @@ def test_electroprop(self): shp_expected = [0.0, 505.55333, 505.55333] prop_thrust_expected = total_thrust_expected = [ - 610.35808, - 2627.26329, - 312.27342, + 610.35808276, + 2627.2632965, + 312.64111293, ] electric_power_expected = [0.0, 408.4409047, 408.4409047] @@ -342,14 +356,17 @@ def build_mission(self, num_nodes, aviary_inputs, **kwargs): PropellerPerformance(aviary_options=aviary_inputs, num_nodes=num_nodes), promotes_inputs=[ Dynamic.Mission.MACH, - Dynamic.Mission.SPEED_OF_SOUND, Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, + Aircraft.Engine.PROPELLER_TIP_MACH_MAX, Dynamic.Mission.DENSITY, Dynamic.Mission.VELOCITY, Aircraft.Engine.PROPELLER_DIAMETER, - Dynamic.Mission.SHAFT_POWER, Aircraft.Engine.PROPELLER_ACTIVITY_FACTOR, Aircraft.Engine.PROPELLER_INTEGRATED_LIFT_COEFFICIENT, + Aircraft.Nacelle.AVG_DIAMETER, + Dynamic.Mission.SPEED_OF_SOUND, + Dynamic.Mission.RPM, + Dynamic.Mission.SHAFT_POWER, ], promotes_outputs=['*'], ) diff --git a/aviary/subsystems/propulsion/turboprop_model.py b/aviary/subsystems/propulsion/turboprop_model.py index 444d9db4a..354830a40 100644 --- a/aviary/subsystems/propulsion/turboprop_model.py +++ b/aviary/subsystems/propulsion/turboprop_model.py @@ -1,13 +1,18 @@ +import warnings + import numpy as np import openmdao.api as om +from aviary.subsystems.subsystem_builder_base import SubsystemBuilderBase from aviary.subsystems.propulsion.engine_model import EngineModel from aviary.subsystems.propulsion.engine_deck import EngineDeck from aviary.subsystems.propulsion.utils import EngineModelVariables from aviary.utils.named_values import NamedValues from aviary.utils.aviary_values import AviaryValues -from aviary.variable_info.variables import Aircraft, Dynamic +from aviary.variable_info.variables import Aircraft, Dynamic, Settings +from aviary.variable_info.enums import Verbosity from aviary.subsystems.propulsion.propeller.propeller_performance import PropellerPerformance +from aviary.subsystems.propulsion.gearbox.gearbox_builder import GearboxBuilder class TurbopropModel(EngineModel): @@ -25,11 +30,14 @@ class TurbopropModel(EngineModel): If using an engine deck, engine performance data (optional). If provided, used instead of tabular data file. shaft_power_model : SubsystemBuilderBase () - Subsystem builder for the shaft power generating component. If None, an + Subsystem builder for the shaft power generating component. If None, an EngineDeck built using provided options is used. propeller_model : SubsystemBuilderBase () - Subsystem builder for the propeller. If None, the Hamilton Standard methodology + Subsystem builder for the propeller. If None, the Hamilton Standard methodology is used to model the propeller. + gearbox_model : SubsystemBuilderBase () + Subsystem builder used for the gearbox. If None, the simple gearbox model is + used. Methods ------- @@ -41,14 +49,22 @@ class TurbopropModel(EngineModel): update """ - def __init__(self, name='turboprop_model', options: AviaryValues = None, - data: NamedValues = None, shaft_power_model=None, propeller_model=None): + def __init__( + self, + name='turboprop_model', + options: AviaryValues = None, + data: NamedValues = None, + shaft_power_model: SubsystemBuilderBase = None, + propeller_model: SubsystemBuilderBase = None, + gearbox_model: SubsystemBuilderBase = None, + ): # also calls _preprocess_inputs() as part of EngineModel __init__ super().__init__(name, options) self.shaft_power_model = shaft_power_model self.propeller_model = propeller_model + self.gearbox_model = gearbox_model # Initialize turboshaft engine deck. New required variable set w/o thrust if shaft_power_model is None: @@ -63,11 +79,23 @@ def __init__(self, name='turboprop_model', options: AviaryValues = None, }, ) + # TODO No reason gearbox model needs to be required. All connections can + # be handled in configure - need to figure out when user wants gearbox without + # directly passing builder + if gearbox_model is None: + # TODO where can we bring in include_constraints? kwargs in init is an option, + # but that still requires the L2 interface + self.gearbox_model = GearboxBuilder( + name=name + '_gearbox', include_constraints=True + ) + # BUG if using both custom subsystems that happen to share a kwarg but need different values, this breaks def build_pre_mission(self, aviary_inputs, **kwargs) -> om.Group: shp_model = self.shaft_power_model propeller_model = self.propeller_model + gearbox_model = self.gearbox_model turboprop_group = om.Group() + # TODO engine scaling for turboshafts requires EngineSizing to be refactored to # accept target scaling variable as an option, skipping for now if type(shp_model) is not EngineDeck: @@ -79,6 +107,16 @@ def build_pre_mission(self, aviary_inputs, **kwargs) -> om.Group: promotes=['*'] ) + gearbox_model_pre_mission = gearbox_model.build_pre_mission( + aviary_inputs, **kwargs + ) + if gearbox_model_pre_mission is not None: + turboprop_group.add_subsystem( + gearbox_model_pre_mission.name, + subsys=gearbox_model_pre_mission, + promotes=['*'], + ) + if propeller_model is not None: propeller_model_pre_mission = propeller_model.build_pre_mission( aviary_inputs, **kwargs @@ -97,6 +135,7 @@ def build_mission(self, num_nodes, aviary_inputs, **kwargs): num_nodes=num_nodes, shaft_power_model=self.shaft_power_model, propeller_model=self.propeller_model, + gearbox_model=self.gearbox_model, aviary_inputs=aviary_inputs, kwargs=kwargs, ) @@ -105,34 +144,39 @@ def build_mission(self, num_nodes, aviary_inputs, **kwargs): def build_post_mission(self, aviary_inputs, **kwargs): shp_model = self.shaft_power_model + gearbox_model = self.gearbox_model propeller_model = self.propeller_model turboprop_group = om.Group() - if type(shp_model) is not EngineDeck: - shp_model_post_mission = shp_model.build_post_mission( - aviary_inputs, **kwargs + + shp_model_post_mission = shp_model.build_post_mission(aviary_inputs, **kwargs) + if shp_model_post_mission is not None: + turboprop_group.add_subsystem( + shp_model.name, + subsys=shp_model_post_mission, + aviary_options=aviary_inputs, ) - if shp_model_post_mission is not None: - turboprop_group.add_subsystem( - shp_model_post_mission.name, - subsys=shp_model_post_mission, - aviary_options=aviary_inputs, - ) - if self.propeller_model is not None: + gearbox_model_post_mission = gearbox_model.build_post_mission( + aviary_inputs, **kwargs + ) + if gearbox_model_post_mission is not None: + turboprop_group.add_subsystem( + gearbox_model.name, + subsys=gearbox_model_post_mission, + aviary_options=aviary_inputs, + ) + + if propeller_model is not None: propeller_model_post_mission = propeller_model.build_post_mission( aviary_inputs, **kwargs ) if propeller_model_post_mission is not None: turboprop_group.add_subsystem( - propeller_model_post_mission.name, + propeller_model.name, subsys=propeller_model_post_mission, aviary_options=aviary_inputs, ) - # turboprop_group.set_input_default( - # Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, val=0.0, units='ft/s' - # ) - return turboprop_group @@ -143,20 +187,26 @@ def initialize(self): ) self.options.declare('shaft_power_model', desc='shaft power generation model') self.options.declare('propeller_model', desc='propeller model') - self.options.declare('kwargs', desc='kwargs for turboprop mission models') + self.options.declare('gearbox_model', desc='gearbox model') + self.options.declare('kwargs', desc='kwargs for turboprop mission model') self.options.declare( - 'aviary_inputs', desc='aviary inputs for turboprop mission' + 'aviary_inputs', desc='aviary inputs for turboprop mission model' ) def setup(self): - num_nodes = self.options['num_nodes'] + # All promotions for configurable components in this group are handled during + # configure() + + # save num_nodes for use in configure() + self.num_nodes = num_nodes = self.options['num_nodes'] shp_model = self.options['shaft_power_model'] propeller_model = self.options['propeller_model'] + gearbox_model = self.options['gearbox_model'] kwargs = self.options['kwargs'] - aviary_inputs = self.options['aviary_inputs'] - - max_thrust_group = om.Group() + # save aviary_inputs for use in configure() + self.aviary_inputs = aviary_inputs = self.options['aviary_inputs'] + # Shaft Power Model try: shp_kwargs = kwargs[shp_model.name] except (AttributeError, KeyError): @@ -164,59 +214,66 @@ def setup(self): shp_model_mission = shp_model.build_mission( num_nodes, aviary_inputs, **shp_kwargs) if shp_model_mission is not None: - self.add_subsystem( - shp_model.name, - subsys=shp_model_mission, - promotes_inputs=['*'], - ) + self.add_subsystem(shp_model.name, subsys=shp_model_mission) - # Gearbox can go here + # NOTE: this subsystem is a empty component that has fixed RPM added as an output + # in configure() if provided in aviary_inputs + self.add_subsystem('fixed_rpm_source', subsys=om.IndepVarComp()) + + # Gearbox Model + try: + gearbox_kwargs = kwargs[gearbox_model.name] + except (AttributeError, KeyError): + gearbox_kwargs = {} + if gearbox_model is not None: + gearbox_model_mission = gearbox_model.build_mission( + num_nodes, aviary_inputs, **gearbox_kwargs + ) + if gearbox_model_mission is not None: + self.add_subsystem(gearbox_model.name, subsys=gearbox_model_mission) + # Propeller Model try: propeller_kwargs = kwargs[propeller_model.name] except (AttributeError, KeyError): propeller_kwargs = {} if propeller_model is not None: - + propeller_group = om.Group() propeller_model_mission = propeller_model.build_mission( num_nodes, aviary_inputs, **propeller_kwargs ) if propeller_model_mission is not None: - self.add_subsystem( - propeller_model.name, + propeller_group.add_subsystem( + propeller_model.name + '_base', subsys=propeller_model_mission, - promotes_inputs=[ - '*', - (Dynamic.Mission.SHAFT_POWER, 'propeller_shaft_power'), - ], - promotes_outputs=[ - '*', - (Dynamic.Mission.THRUST, 'propeller_thrust'), - ], + promotes_inputs=['*'], + promotes_outputs=[Dynamic.Mission.THRUST], ) - self.connect(Dynamic.Mission.SHAFT_POWER, 'propeller_shaft_power') - propeller_model_mission_max = propeller_model.build_mission( num_nodes, aviary_inputs, **propeller_kwargs ) - max_thrust_group.add_subsystem( + propeller_group.add_subsystem( propeller_model.name + '_max', subsys=propeller_model_mission_max, - promotes_inputs=['*', - (Dynamic.Mission.SHAFT_POWER, 'propeller_shaft_power_max')], - promotes_outputs=[(Dynamic.Mission.THRUST, 'propeller_thrust_max')] + promotes_inputs=[ + '*', + (Dynamic.Mission.SHAFT_POWER, Dynamic.Mission.SHAFT_POWER_MAX), + ], + promotes_outputs=[ + (Dynamic.Mission.THRUST, Dynamic.Mission.THRUST_MAX) + ], ) - self.connect( - Dynamic.Mission.SHAFT_POWER_MAX, 'propeller_shaft_power_max' - ) + self.add_subsystem(propeller_model.name, propeller_group) - else: # use the Hamilton Standard model + else: + # use the Hamilton Standard model # only promote top-level inputs to avoid conflicts with max group prop_inputs = [ Dynamic.Mission.MACH, Aircraft.Engine.PROPELLER_TIP_SPEED_MAX, + Aircraft.Engine.PROPELLER_TIP_MACH_MAX, Dynamic.Mission.DENSITY, Dynamic.Mission.VELOCITY, Aircraft.Engine.PROPELLER_DIAMETER, @@ -224,32 +281,26 @@ def setup(self): Aircraft.Engine.PROPELLER_INTEGRATED_LIFT_COEFFICIENT, Aircraft.Nacelle.AVG_DIAMETER, Dynamic.Mission.SPEED_OF_SOUND, + Dynamic.Mission.RPM, ] try: propeller_kwargs = kwargs['hamilton_standard'] except KeyError: propeller_kwargs = {} - self.add_subsystem( - 'propeller_model', + propeller_group = om.Group() + + propeller_group.add_subsystem( + 'propeller_model_base', PropellerPerformance( aviary_options=aviary_inputs, num_nodes=num_nodes, **propeller_kwargs, ), - promotes_inputs=[ - *prop_inputs, - (Dynamic.Mission.SHAFT_POWER, 'propeller_shaft_power'), - ], - promotes_outputs=[ - '*', - (Dynamic.Mission.THRUST, 'propeller_thrust'), - ], + promotes=['*'], ) - self.connect(Dynamic.Mission.SHAFT_POWER, 'propeller_shaft_power') - - max_thrust_group.add_subsystem( + propeller_group.add_subsystem( 'propeller_model_max', PropellerPerformance( aviary_options=aviary_inputs, @@ -258,12 +309,12 @@ def setup(self): ), promotes_inputs=[ *prop_inputs, - (Dynamic.Mission.SHAFT_POWER, 'propeller_shaft_power_max'), + (Dynamic.Mission.SHAFT_POWER, Dynamic.Mission.SHAFT_POWER_MAX), ], - promotes_outputs=[(Dynamic.Mission.THRUST, 'propeller_thrust_max')], + promotes_outputs=[(Dynamic.Mission.THRUST, Dynamic.Mission.THRUST_MAX)], ) - self.connect(Dynamic.Mission.SHAFT_POWER_MAX, 'propeller_shaft_power_max') + self.add_subsystem('propeller_model', propeller_group) thrust_adder = om.ExecComp( 'turboprop_thrust=turboshaft_thrust+propeller_thrust', @@ -288,37 +339,256 @@ def setup(self): promotes_outputs=[('turboprop_thrust', Dynamic.Mission.THRUST)], ) - max_thrust_group.add_subsystem( + self.add_subsystem( 'max_thrust_adder', subsys=max_thrust_adder, promotes_inputs=['*'], - promotes_outputs=[('turboprop_thrust_max', Dynamic.Mission.THRUST_MAX)] - ) - - self.add_subsystem( - 'turboprop_max_group', - max_thrust_group, - promotes_inputs=['*'], - promotes_outputs=[Dynamic.Mission.THRUST_MAX], + promotes_outputs=[('turboprop_thrust_max', Dynamic.Mission.THRUST_MAX)], ) def configure(self): - # configure step to alias thrust output from shaft power model if present + """ + Correctly connect variables between shaft power model, gearbox, and propeller, + aliasing names if they are present in both sets of connections. + + If a gearbox is present, inputs to the gearbox are usually done via connection, + while outputs from the gearbox are promoted. This prevents intermediate values + from "leaking" out of the model and getting incorrectly connected to outside + components. It is assumed only the gearbox has variables like this. + + Set up fixed RPM value if requested by user, which overrides any RPM defined by + shaft power model + """ + has_gearbox = self.options['gearbox_model'] is not None + + # TODO this list shouldn't be hardcoded - it should mirror propulsion_mission list + # Don't promote inputs that are in this list - shaft power should be an output + # of this system, also having it as an input causes feedback loop problem at + # the propulsion level + skipped_inputs = [ + Dynamic.Mission.ELECTRIC_POWER_IN, + Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE, + Dynamic.Mission.NOX_RATE, + Dynamic.Mission.SHAFT_POWER, + Dynamic.Mission.SHAFT_POWER_MAX, + Dynamic.Mission.TEMPERATURE_T4, + Dynamic.Mission.THRUST, + Dynamic.Mission.THRUST_MAX, + ] + + # Build lists of inputs/outputs for each component as needed: + # "_input_list" or "_output_list" are all variables that still need to be + # connected or promoted. This list is pared down as each variable is handled. + # "_inputs" or "_outputs" is a list that tracks all the pomotions needed for a + # given component, which is done at the end as a bulk promote. + shp_model = self._get_subsystem(self.options['shaft_power_model'].name) - output_dict = shp_model.list_outputs( + shp_output_dict = shp_model.list_outputs( return_format='dict', units=True, out_stream=None, all_procs=True ) + shp_output_list = list( + set( + shp_output_dict[key]['prom_name'] + for key in shp_output_dict + if '.' not in shp_output_dict[key]['prom_name'] + ) + ) + # always promote all shaft power model inputs w/o aliasing + shp_inputs = ['*'] + shp_outputs = [] + + if has_gearbox: + gearbox_model = self._get_subsystem(self.options['gearbox_model'].name) + gearbox_input_dict = gearbox_model.list_inputs( + return_format='dict', units=True, out_stream=None, all_procs=True + ) + # Assumption is made that variables with '_out' should never be promoted or + # connected as top-level input to gearbox. This is necessary because + # Aviary gearbox uses things like shp_out internally, like when computing + # torque output, so "shp_out" is an input to that internal component + gearbox_input_list = list( + set( + gearbox_input_dict[key]['prom_name'] + for key in gearbox_input_dict + if '.' not in gearbox_input_dict[key]['prom_name'] + and '_out' not in gearbox_input_dict[key]['prom_name'] + ) + ) + gearbox_inputs = [] + gearbox_output_dict = gearbox_model.list_outputs( + return_format='dict', units=True, out_stream=None, all_procs=True + ) + gearbox_output_list = list( + set( + gearbox_output_dict[key]['prom_name'] + for key in gearbox_output_dict + if '.' not in gearbox_output_dict[key]['prom_name'] + ) + ) + gearbox_outputs = [] + + if self.options['propeller_model'] is None: + propeller_model_name = 'propeller_model' + else: + propeller_model_name = self.options['propeller_model'].name + propeller_model = self._get_subsystem(propeller_model_name) + propeller_input_dict = propeller_model.list_inputs( + return_format='dict', units=True, out_stream=None, all_procs=True + ) + propeller_input_list = list( + set( + propeller_input_dict[key]['prom_name'] + for key in propeller_input_dict + if '.' not in propeller_input_dict[key]['prom_name'] + ) + ) + propeller_inputs = [] + # always promote all propeller model outputs w/o aliasing except thrust + propeller_outputs = [ + '*', + (Dynamic.Mission.THRUST, 'propeller_thrust'), + (Dynamic.Mission.THRUST_MAX, 'propeller_thrust_max'), + ] + + ######################### + # SHP MODEL CONNECTIONS # + ######################### + # Everything not explicitly handled here gets promoted later on + # Thrust outputs are directly promoted with alias (this is a special case) + if Dynamic.Mission.THRUST in shp_output_list: + shp_outputs.append((Dynamic.Mission.THRUST, 'turboshaft_thrust')) + shp_output_list.remove(Dynamic.Mission.THRUST) + + if Dynamic.Mission.THRUST_MAX in shp_output_list: + shp_outputs.append((Dynamic.Mission.THRUST_MAX, 'turboshaft_thrust_max')) + shp_output_list.remove(Dynamic.Mission.THRUST_MAX) + + # Gearbox connections + if has_gearbox: + for var in shp_output_list.copy(): + # Check for case: var is output from shp_model, connects to gearbox, then + # gets updated by gearbox + # RPM has special handling, so skip it here + if var + '_in' in gearbox_input_list and var != Dynamic.Mission.RPM: + # if var is in gearbox input and output, connect on shp -> gearbox side + if ( + var in gearbox_output_list + or var + '_out' in gearbox_output_list + ): + shp_outputs.append((var, var + '_gearbox')) + shp_output_list.remove(var) + gearbox_inputs.append((var + '_in', var + '_gearbox')) + gearbox_input_list.remove(var + '_in') + # otherwise it gets promoted, which will get done later + + # If fixed RPM is requested by the user, use that value. Override RPM output + # from shaft power model if present, warning user + rpm_ivc = self._get_subsystem('fixed_rpm_source') + + if Aircraft.Engine.FIXED_RPM in self.aviary_inputs: + fixed_rpm = self.aviary_inputs.get_val( + Aircraft.Engine.FIXED_RPM, units='rpm' + ) - outputs = ['*'] - - if Dynamic.Mission.THRUST in [ - output_dict[key]['prom_name'] for key in output_dict - ]: - outputs.append((Dynamic.Mission.THRUST, 'turboshaft_thrust')) + if Dynamic.Mission.RPM in shp_output_list: + if self.aviary_inputs.get_val(Settings.VERBOSITY) >= Verbosity.BRIEF: + warnings.warn( + 'Overriding RPM value outputted by EngineModel' + f'{shp_model.name} with fixed RPM of {fixed_rpm}' + ) - if Dynamic.Mission.THRUST_MAX in [ - output_dict[key]['prom_name'] for key in output_dict - ]: - outputs.append((Dynamic.Mission.THRUST_MAX, 'turboshaft_thrust_max')) + shp_outputs.append( + (Dynamic.Mission.RPM, 'AUTO_OVERRIDE:' + Dynamic.Mission.RPM) + ) + shp_output_list.remove(Dynamic.Mission.RPM) + + fixed_rpm_nn = np.ones(self.num_nodes) * fixed_rpm + + rpm_ivc.add_output(Dynamic.Mission.RPM, fixed_rpm_nn, units='rpm') + if has_gearbox: + self.promotes('fixed_rpm_source', [(Dynamic.Mission.RPM, 'fixed_rpm')]) + gearbox_inputs.append((Dynamic.Mission.RPM + '_in', 'fixed_rpm')) + gearbox_input_list.remove(Dynamic.Mission.RPM + '_in') + else: + self.promotes('fixed_rpm_source', ['*']) + else: + rpm_ivc.add_output('AUTO_OVERRIDE:' + Dynamic.Mission.RPM, 1.0, units='rpm') + if has_gearbox: + if Dynamic.Mission.RPM in shp_output_list: + shp_outputs.append( + (Dynamic.Mission.RPM, Dynamic.Mission.RPM + '_gearbox') + ) + shp_output_list.remove(Dynamic.Mission.RPM) + gearbox_inputs.append( + (Dynamic.Mission.RPM + '_in', Dynamic.Mission.RPM + '_gearbox') + ) + gearbox_input_list.remove(Dynamic.Mission.RPM + '_in') + + # All other shp model outputs that don't interact with gearbox will be promoted + for var in shp_output_list: + shp_outputs.append(var) + + ############################# + # GEARBOX MODEL CONNECTIONS # + ############################# + if has_gearbox: + # Promote all inputs which don't come from shp model (those got connected), + # don't promote ones in skip list + for var in gearbox_input_list.copy(): + if var not in skipped_inputs: + gearbox_inputs.append(var) + # DO NOT promote inputs in skip list - always skip + gearbox_input_list.remove(var) + + # gearbox outputs can always get promoted + for var in propeller_input_list.copy(): + if var in gearbox_output_list and var in propeller_input_list: + gearbox_outputs.append((var, var)) + gearbox_output_list.remove(var) + # connect variables in skip list to propeller + if var in skipped_inputs: + self.connect( + var, + propeller_model.name + '.' + var, + ) + + # alias outputs with 'out' to match with propeller + if var + '_out' in gearbox_output_list and var in propeller_input_list: + gearbox_outputs.append((var + '_out', var)) + gearbox_output_list.remove(var + '_out') + # connect variables in skip list to propeller + if var in skipped_inputs: + self.connect( + var, + propeller_model.name + '.' + var, + ) + + # inputs/outputs that didn't need special handling will get promoted + for var in gearbox_input_list: + gearbox_inputs.append(var) + for var in gearbox_output_list: + gearbox_outputs.append(var) + + ############################### + # PROPELLER MODEL CONNECTIONS # + ############################### + # we will promote all inputs not in skip list + for var in propeller_input_list.copy(): + if var not in skipped_inputs: + propeller_inputs.append(var) + propeller_input_list.remove(var) + + ############## + # PROMOTIONS # + ############## + # bulk promote desired inputs and outputs for each subsystem we have been tracking + self.promotes(shp_model.name, inputs=shp_inputs, outputs=shp_outputs) + + if has_gearbox: + self.promotes( + gearbox_model.name, inputs=gearbox_inputs, outputs=gearbox_outputs + ) - self.promotes(shp_model.name, outputs=outputs) + self.promotes( + propeller_model_name, inputs=propeller_inputs, outputs=propeller_outputs + ) diff --git a/aviary/utils/engine_deck_conversion.py b/aviary/utils/engine_deck_conversion.py index 16025095f..b6476f733 100644 --- a/aviary/utils/engine_deck_conversion.py +++ b/aviary/utils/engine_deck_conversion.py @@ -256,26 +256,26 @@ def EngineDeckConverter(input_file, output_file, data_format: EngineDeckType): # TODO flight condition dependent throttle range? # NOTE this often leaves max throttles less than 1 in the deck - this caues # problems when finding reference SLS thrust, as there is often no max - # power data at that point in the engine deck. It is reccomended GASP + # power data at that point in the engine deck. It is recommended GASP # engine decks override Aircraft.Engine.REFERENCE_THRUST in EngineDecks data[THROTTLE] = normalize(data[TEMPERATURE], minimum=0.0, maximum=t4max) - # remove all points above T4max - # TODO save these points as commented out? - valid_idx = np.where(data[THROTTLE] <= 1.0) - data[MACH] = data[MACH][valid_idx] - data[ALTITUDE] = data[ALTITUDE][valid_idx] - data[THROTTLE] = data[THROTTLE][valid_idx] - data[FUEL_FLOW] = data[FUEL_FLOW][valid_idx] + else: + data[THROTTLE] = normalize(T4T2, minimum=0.0, maximum=t4max) + + # TODO save these points as commented out? + valid_idx = np.where(data[THROTTLE] <= 1.0) + data[MACH] = data[MACH][valid_idx] + data[ALTITUDE] = data[ALTITUDE][valid_idx] + data[THROTTLE] = data[THROTTLE][valid_idx] + data[FUEL_FLOW] = data[FUEL_FLOW][valid_idx] + if compute_T4: data[TEMPERATURE] = data[TEMPERATURE][valid_idx] - if is_turbo_prop: - data[SHAFT_POWER_CORRECTED] = data[SHAFT_POWER_CORRECTED][valid_idx] - data[TAILPIPE_THRUST] = data[TAILPIPE_THRUST][valid_idx] - else: - data[THRUST] = data[THRUST][valid_idx] - + if is_turbo_prop: + data[SHAFT_POWER_CORRECTED] = data[SHAFT_POWER_CORRECTED][valid_idx] + data[TAILPIPE_THRUST] = data[TAILPIPE_THRUST][valid_idx] else: - data[THROTTLE] = T4T2 + data[THRUST] = data[THRUST][valid_idx] # data needs to be string so column length can be easily found later for var in data: diff --git a/aviary/variable_info/variable_meta_data.py b/aviary/variable_info/variable_meta_data.py index ac028334e..9f6e7f532 100644 --- a/aviary/variable_info/variable_meta_data.py +++ b/aviary/variable_info/variable_meta_data.py @@ -920,7 +920,8 @@ add_meta_data( Aircraft.CrewPayload.PASSENGER_PAYLOAD_MASS, meta_data=_MetaData, - # note: this GASP variable does not include cargo, but it does include passenger baggage + # note: this GASP variable does not include cargo, but it does include + # passenger baggage historical_name={"GASP": 'INGASP.WPL', "FLOPS": None, "LEAPS1": None @@ -1225,16 +1226,11 @@ ) add_meta_data( - Aircraft.Design.IJEFF, - meta_data=_MetaData, - historical_name={"GASP": 'INGASP.IJEFF', - "FLOPS": None, - "LEAPS1": None - }, + Aircraft.Design.IJEFF, meta_data=_MetaData, + historical_name={"GASP": 'INGASP.IJEFF', "FLOPS": None, "LEAPS1": None}, desc="A flag used by Jeff V. Bowles to debug GASP code during his 53 years supporting the development of GASP. " - "This flag is planted here to thank him for his hard work and dedication, Aviary wouldn't be what it is today " - "without his help.", -) + "This flag is planted here to thank him for his hard work and dedication, Aviary wouldn't be what it is today " + "without his help.",) add_meta_data( Aircraft.Design.LAMINAR_FLOW_LOWER, @@ -1375,21 +1371,15 @@ ) add_meta_data( - Aircraft.Design.RESERVE_FUEL_FRACTION, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None - }, - option=True, - units="unitless", + Aircraft.Design.RESERVE_FUEL_FRACTION, meta_data=_MetaData, + historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, + option=True, units="unitless", desc='required fuel reserves: given as a proportion of mission fuel. This value must be nonnegative. ' - 'Mission fuel only includes normal phases and excludes reserve phases. ' - 'If it is 0.5, the reserve fuel is half of the mission fuel (one third of the total fuel). Note ' - 'it can be greater than 1. If it is 2, there would be twice as much reserve fuel as mission fuel ' - '(the total fuel carried would be 1/3 for the mission and 2/3 for the reserve)', - default_value=0, -) + 'Mission fuel only includes normal phases and excludes reserve phases. ' + 'If it is 0.5, the reserve fuel is half of the mission fuel (one third of the total fuel). Note ' + 'it can be greater than 1. If it is 2, there would be twice as much reserve fuel as mission fuel ' + '(the total fuel carried would be 1/3 for the mission and 2/3 for the reserve)', + default_value=0,) add_meta_data( Aircraft.Design.SMOOTH_MASS_DISCONTINUITIES, @@ -1741,15 +1731,16 @@ add_meta_data( Aircraft.Engine.CONSTANT_FUEL_CONSUMPTION, meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": 'MISSIN.FLEAK', - "LEAPS1": ['iengine.fuel_leak', 'aircraft.inputs.L0_engine.fuel_leak'] - }, + historical_name={ + "GASP": None, + "FLOPS": 'MISSIN.FLEAK', + "LEAPS1": [ + 'iengine.fuel_leak', + 'aircraft.inputs.L0_engine.fuel_leak']}, option=True, units='lbm/h', desc='Additional constant fuel flow. This value is not scaled with the engine', - default_value=0.0 -) + default_value=0.0) add_meta_data( Aircraft.Engine.CONTROLS_MASS, @@ -1778,6 +1769,17 @@ desc='filepath to data file containing engine performance tables' ) +add_meta_data( + Aircraft.Engine.FIXED_RPM, + meta_data=_MetaData, + historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, + units='rpm', + default_value=1.0, + desc='RPM the engine is set to be running at. Overrides RPM provided by ' + 'engine model or chosen by optimizer. Typically used when pairing a motor or ' + 'turboshaft using a fixed operating RPM with a propeller.', +) + add_meta_data( Aircraft.Engine.FLIGHT_IDLE_MAX_FRACTION, meta_data=_MetaData, @@ -1886,19 +1888,11 @@ # TODO dependency on NTYE? Does this var need preprocessing? Can this mention be removed? add_meta_data( - Aircraft.Engine.HAS_PROPELLERS, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None - }, - option=True, - units="unitless", - default_value=False, - types=bool, + Aircraft.Engine.HAS_PROPELLERS, meta_data=_MetaData, + historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, + option=True, units="unitless", default_value=False, types=bool, desc='if True, the aircraft has propellers, otherwise aircraft is assumed to have no ' - 'propellers. In GASP this depended on NTYE', -) + 'propellers. In GASP this depended on NTYE',) add_meta_data( Aircraft.Engine.IGNORE_NEGATIVE_THRUST, @@ -1916,19 +1910,11 @@ ) add_meta_data( - Aircraft.Engine.INTERPOLATION_METHOD, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None - }, - units="unitless", - option=True, - default_value='slinear', - types=str, + Aircraft.Engine.INTERPOLATION_METHOD, meta_data=_MetaData, + historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, + units="unitless", option=True, default_value='slinear', types=str, desc="method used for interpolation on an engine deck's data file, allowable values are " - 'table methods from openmdao.components.interp_util.interp', -) + 'table methods from openmdao.components.interp_util.interp',) add_meta_data( Aircraft.Engine.MASS, @@ -2114,10 +2100,11 @@ add_meta_data( Aircraft.Engine.PROPELLER_TIP_MACH_MAX, meta_data=_MetaData, - historical_name={"GASP": None, # TODO this needs verification - "FLOPS": None, - "LEAPS1": None - }, + historical_name={ + "GASP": None, # TODO this needs verification + "FLOPS": None, + "LEAPS1": None, + }, units='unitless', desc='maximum allowable Mach number at propeller tip (based on helical speed)', default_value=1.0, @@ -2132,7 +2119,7 @@ "LEAPS1": None, }, units='ft/s', - desc='maximum allowable propeller linear tip speed', + desc='maximum allowable linear propeller tip speed due to rotation', default_value=800.0, ) @@ -2400,11 +2387,8 @@ add_meta_data( Aircraft.Engine.Gearbox.MASS, meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None - }, - units='kg', + historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, + units='lbm', desc='The mass of the gearbox.', default_value=0, ) @@ -2412,24 +2396,22 @@ add_meta_data( Aircraft.Engine.Gearbox.SHAFT_POWER_DESIGN, meta_data=_MetaData, - historical_name={"GASP": 'INPROP.HPMSLS', # max sea level static horsepower, hp - "FLOPS": None, - "LEAPS1": None, - }, - units='kW', - desc='A guess for the maximum power that will be transmitted through the gearbox during the mission.', + historical_name={ + "GASP": 'INPROP.HPMSLS', # max sea level static horsepower, hp + "FLOPS": None, + "LEAPS1": None, + }, + units='hp', + desc='A guess for the maximum power that will be transmitted through the gearbox during the mission (max shp input).', default_value=1.0, - option=True + option=True, ) add_meta_data( Aircraft.Engine.Gearbox.SPECIFIC_TORQUE, meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None - }, - units='N*m/kg', + historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, + units='lbf*ft/lbm', desc='The specific torque of the gearbox, used to calculate gearbox mass. ', default_value=100, ) @@ -2444,7 +2426,7 @@ Aircraft.Engine.Motor.MASS, meta_data=_MetaData, historical_name={"GASP": 'WMOTOR', "FLOPS": None, "LEAPS1": None}, - units='kg', + units='lbm', desc='Total motor mass (considers number of motors)', default_value=0.0, ) @@ -2452,13 +2434,10 @@ add_meta_data( Aircraft.Engine.Motor.TORQUE_MAX, meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None - }, - units='N*m', + historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, + units='lbf*ft', desc='Max torque value that can be output from a single motor. Used to determine ' - 'motor mass in pre-mission', + 'motor mass in pre-mission', ) # ______ _ @@ -3830,19 +3809,11 @@ desc='landing gear drag coefficient') add_meta_data( - Aircraft.LandingGear.FIXED_GEAR, - meta_data=_MetaData, - historical_name={"GASP": 'INGASP.IGEAR', - "FLOPS": None, - "LEAPS1": None - }, - option=True, - default_value=True, - types=bool, - units="unitless", + Aircraft.LandingGear.FIXED_GEAR, meta_data=_MetaData, + historical_name={"GASP": 'INGASP.IGEAR', "FLOPS": None, "LEAPS1": None}, + option=True, default_value=True, types=bool, units="unitless", desc='Type of landing gear. In GASP, 0 is retractable and 1 is deployed (fixed). Here, ' - 'false is retractable and true is deployed (fixed).', -) + 'false is retractable and true is deployed (fixed).',) add_meta_data( Aircraft.LandingGear.MAIN_GEAR_LOCATION, @@ -5321,19 +5292,11 @@ ) add_meta_data( - Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None - }, - units="unitless", - default_value=False, - types=bool, - option=True, + Aircraft.Wing.FOLD_DIMENSIONAL_LOCATION_SPECIFIED, meta_data=_MetaData, + historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, + units="unitless", default_value=False, types=bool, option=True, desc='if true, fold location from the chosen input is an actual fold span, ' - 'if false it is normalized to the half span. In GASP this depended on STRUT or YWFOLD' -) + 'if false it is normalized to the half span. In GASP this depended on STRUT or YWFOLD') add_meta_data( Aircraft.Wing.FOLD_MASS, @@ -6413,16 +6376,11 @@ ) add_meta_data( - Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None - }, + Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE, meta_data=_MetaData, + historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, units='lbm/h', desc='Current rate of fuel consumption of the vehicle, per single instance of each ' - 'engine model. Consumption (i.e. mass reduction) of fuel is defined as negative.' -) + 'engine model. Consumption (i.e. mass reduction) of fuel is defined as negative.') add_meta_data( Dynamic.Mission.FUEL_FLOW_RATE_NEGATIVE_TOTAL, @@ -6549,18 +6507,6 @@ desc='Current total rate of nitrous oxide (NOx) production by the vehicle' ) -# add_meta_data( -# Dynamic.Mission.PERCENT_ROTOR_RPM_CORRECTED, -# meta_data=_MetaData, -# historical_name={"GASP": None, -# "FLOPS": None, -# "LEAPS1": None -# }, -# units='unitless', -# desc='percent of the corrected rotor speed', -# default_value=0.9, -# ) - add_meta_data( Dynamic.Mission.PROPELLER_TIP_SPEED, meta_data=_MetaData, @@ -6581,16 +6527,6 @@ desc='Rotational rate of shaft, per engine.', ) -add_meta_data( - Dynamic.Mission.RPM_GEARBOX, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None}, - units='rpm', - desc='Rotational rate of shaft coming out of the gearbox and into the prop.', -) - add_meta_data( Dynamic.Mission.SPECIFIC_ENERGY, meta_data=_MetaData, @@ -6623,14 +6559,6 @@ desc='current shaft power, per engine', ) -add_meta_data( - Dynamic.Mission.SHAFT_POWER_GEARBOX, - meta_data=_MetaData, - historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, - units='kW', - desc='current shaft power coming out of the gearbox, per gearbox', -) - add_meta_data( Dynamic.Mission.SHAFT_POWER_MAX, meta_data=_MetaData, @@ -6642,17 +6570,6 @@ desc='The maximum possible shaft power currently producible, per engine' ) -add_meta_data( - Dynamic.Mission.SHAFT_POWER_MAX_GEARBOX, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None - }, - units='hp', - desc='The maximum possible shaft power the gearbox can currently produce, per gearbox' -) - add_meta_data( Dynamic.Mission.SPECIFIC_ENERGY_RATE_EXCESS, meta_data=_MetaData, @@ -6785,14 +6702,6 @@ 'condition, per engine', ) -add_meta_data( - Dynamic.Mission.TORQUE_GEARBOX, - meta_data=_MetaData, - historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, - units='N*m', - desc='Current torque being produced, per gearbox', -) - add_meta_data( Dynamic.Mission.VELOCITY, meta_data=_MetaData, @@ -6837,6 +6746,13 @@ # | |____ | (_) | | | | | \__ \ | |_ | | | (_| | | | | | | | | |_ \__ \ # \_____| \___/ |_| |_| |___/ \__| |_| \__,_| |_| |_| |_| \__| |___/ # =========================================================================== +add_meta_data( + Mission.Constraints.GEARBOX_SHAFT_POWER_RESIDUAL, + meta_data=_MetaData, + historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, + units='kW', + desc='Must be zero or positive to ensure that the gearbox is sized large enough to handle the maximum shaft power the engine could output during any part of the mission', +) add_meta_data( Mission.Constraints.MASS_RESIDUAL, @@ -6898,14 +6814,6 @@ 'tolerance)', ) -add_meta_data( - Mission.Constraints.SHAFT_POWER_RESIDUAL, - meta_data=_MetaData, - historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, - units='kW', - desc='Must be zero or positive to ensure that the gearbox is sized large enough to handle the maximum shaft power the engine could output during any part of the mission', -) - # _____ _ # | __ \ (_) # | | | | ___ ___ _ __ _ _ __ @@ -7142,7 +7050,7 @@ # 'FLOPS': ['&DEFTOL.TOLIN.BRAKMU', 'BALFLD.BRAKMU'], # 'GASP': None, # 'LEAPS1': 'aircraft.inputs.L0_takeoff_and_landing.braking_mu'}, - historical_name={'FLOPS': None, 'GASP': None, 'LEAPS1': None}, default_value=0.3, + historical_name={'FLOPS': None, 'GASP': None, 'LEAPS1': None}, default_value=0.3, units='unitless', desc='landing coefficient of friction, with brakes on') @@ -7962,21 +7870,19 @@ ) add_meta_data( - Settings.VERBOSITY, - meta_data=_MetaData, - historical_name={"GASP": None, - "FLOPS": None, - "LEAPS1": None - }, + Settings.VERBOSITY, meta_data=_MetaData, + historical_name={"GASP": None, "FLOPS": None, "LEAPS1": None}, desc='Sets how much information Aviary outputs when run. Options include:' - '0. QUIET: All output except errors are suppressed' - '1. BRIEF: Only important information is output, in human-readable format' - '2. VERBOSE: All user-relevant information is output, in human-readable format' - '3. DEBUG: Any information can be outtputed, including warnings, intermediate calculations, etc., with no formatting requirement', - option=True, - types=Verbosity, - default_value=Verbosity.BRIEF -) - -# here we create a copy of the Aviary-core metadata. The reason for this copy is that if we simply imported the Aviary _MetaData in all the external subsystem extensions, we would be modifying the original and the original _MetaData in the core of Aviary could get altered in undesirable ways. By importing this copy to the API the user modifies a new MetaData designed just for their purposes. + '0. QUIET: All output except errors are suppressed' + '1. BRIEF: Only important information is output, in human-readable format' + '2. VERBOSE: All user-relevant information is output, in human-readable format' + '3. DEBUG: Any information can be outtputed, including warnings, intermediate calculations, etc., with no formatting requirement', + option=True, types=Verbosity, default_value=Verbosity.BRIEF) + +# here we create a copy of the Aviary-core metadata. The reason for this +# copy is that if we simply imported the Aviary _MetaData in all the +# external subsystem extensions, we would be modifying the original and +# the original _MetaData in the core of Aviary could get altered in +# undesirable ways. By importing this copy to the API the user modifies a +# new MetaData designed just for their purposes. CoreMetaData = deepcopy(_MetaData) diff --git a/aviary/variable_info/variables.py b/aviary/variable_info/variables.py index 9e576cd1a..93c547b67 100644 --- a/aviary/variable_info/variables.py +++ b/aviary/variable_info/variables.py @@ -210,6 +210,7 @@ class Engine: CONSTANT_FUEL_CONSUMPTION = 'aircraft:engine:constant_fuel_consumption' CONTROLS_MASS = 'aircraft:engine:controls_mass' DATA_FILE = 'aircraft:engine:data_file' + FIXED_RPM = 'aircraft:engine:fixed_rpm' FLIGHT_IDLE_MAX_FRACTION = 'aircraft:engine:flight_idle_max_fraction' FLIGHT_IDLE_MIN_FRACTION = 'aircraft:engine:flight_idle_min_fraction' FLIGHT_IDLE_THRUST_FRACTION = 'aircraft:engine:flight_idle_thrust_fraction' @@ -636,14 +637,10 @@ class Mission: MASS_RATE = 'mass_rate' NOX_RATE = 'nox_rate' NOX_RATE_TOTAL = 'nox_rate_total' - # PERCENT_ROTOR_RPM_CORRECTED = 'percent_rotor_rpm_corrected' PROPELLER_TIP_SPEED = 'propeller_tip_speed' RPM = 'rotations_per_minute' - RPM_GEARBOX = 'rotations_per_minute_gearbox' SHAFT_POWER = 'shaft_power' - SHAFT_POWER_GEARBOX = 'shaft_power_gearbox' SHAFT_POWER_MAX = 'shaft_power_max' - SHAFT_POWER_MAX_GEARBOX = 'shaft_power_max_gearbox' SPECIFIC_ENERGY = 'specific_energy' SPECIFIC_ENERGY_RATE = 'specific_energy_rate' SPECIFIC_ENERGY_RATE_EXCESS = 'specific_energy_rate_excess' @@ -657,7 +654,6 @@ class Mission: THRUST_MAX_TOTAL = 'thrust_net_max_total' THRUST_TOTAL = 'thrust_net_total' TORQUE = 'torque' - TORQUE_GEARBOX = 'torque_gearbox' TORQUE_MAX = 'torque_max' VELOCITY = 'velocity' VELOCITY_RATE = 'velocity_rate' @@ -669,11 +665,13 @@ class Mission: class Constraints: # these can be residuals (for equality constraints), # upper bounds, or lower bounds + GEARBOX_SHAFT_POWER_RESIDUAL = ( + 'mission:constraints:gearbox_shaft_power_residual' + ) MASS_RESIDUAL = 'mission:constraints:mass_residual' MAX_MACH = 'mission:constraints:max_mach' RANGE_RESIDUAL = 'mission:constraints:range_residual' RANGE_RESIDUAL_RESERVE = 'mission:constraints:range_residual_reserve' - SHAFT_POWER_RESIDUAL = 'shaft_power_residual' class Design: # These values MAY change in design mission, but in off-design