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212 lines (172 loc) · 8.08 KB
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"""
Test file to test the outputs, derivatives, and IO of each sample component/group.
The name of this file needs to start with 'test' so that the testflo command will
find and run the file.
"""
import unittest
import openmdao.api as om
from openmdao.utils.assert_utils import assert_check_partials, assert_near_equal
from openmdao.utils.testing_utils import use_tempdirs
from aviary.mission.energy_state.phases.simplified_takeoff import (
FinalTakeoffConditions,
StallSpeed,
TakeoffGroup,
)
from aviary.variable_info.variables import Aircraft, Dynamic, Mission
@use_tempdirs
class StallSpeedTest(unittest.TestCase):
"""Test computation in StallSpeed class."""
def setUp(self):
self.prob = om.Problem()
self.prob.model.add_subsystem(
'comp',
StallSpeed(),
promotes=['*'],
)
self.prob.model.set_input_defaults('mass', val=181200.0, units='lbm') # check
self.prob.model.set_input_defaults(
Dynamic.Atmosphere.DENSITY, val=1.225, units='kg/m**3'
) # check
self.prob.model.set_input_defaults(
'planform_area', val=1370.0, units='ft**2'
) # check (this is the reference wing area)
self.prob.model.set_input_defaults('Cl_max', val=2.0000, units='unitless') # check
self.prob.setup(check=False, force_alloc_complex=True)
def test_case1(self):
self.prob.run_model()
tol = 1e-5
assert_near_equal(self.prob['v_stall'], 71.90002053, tol) # not actual value
partial_data = self.prob.check_partials(out_stream=None, method='cs')
assert_check_partials(partial_data, atol=1e-12, rtol=1e-12) # check the partial derivatives
@use_tempdirs
class FinalConditionsTest(unittest.TestCase):
"""Test final conditions computation in FinalTakeoffConditions class."""
def setUp(self):
self.prob = om.Problem()
opts = {
Mission.SEA_LEVEL_DENSITY: (0.0023769, 'slug/ft**3'),
}
self.prob.model.add_subsystem(
'comp',
FinalTakeoffConditions(**opts),
promotes=['*'],
)
self.prob.model.set_input_defaults('v_stall', val=100, units='m/s') # not actual value
self.prob.model.set_input_defaults('mass', val=181200.0, units='lbm') # check
self.prob.model.set_input_defaults(Mission.Takeoff.FUEL_MASS, val=577, units='lbm') # check
self.prob.model.set_input_defaults(
Dynamic.Atmosphere.DENSITY,
val=0.0023769,
units='slug/ft**3',
) # check
self.prob.model.set_input_defaults(Aircraft.Wing.AREA, val=1370.0, units='ft**2') # check
self.prob.model.set_input_defaults(
Mission.Takeoff.LIFT_COEFFICIENT_MAX, val=2.0000, units='unitless'
) # check
self.prob.model.set_input_defaults(
Aircraft.Propulsion.TOTAL_SCALED_SLS_THRUST, val=28928.0 * 2, units='lbf'
) # check
self.prob.model.set_input_defaults(
Mission.Takeoff.CLIMBOUT_THRUST_FRACTION, val=1, units='unitless'
)
self.prob.model.set_input_defaults(
Mission.Takeoff.LIFT_OVER_DRAG, val=17.354, units='unitless'
) # check
self.prob.setup(check=False, force_alloc_complex=True)
def test_case1(self):
self.prob.run_model()
tol = 1e-5
assert_near_equal(
self.prob[Mission.Takeoff.GROUND_DISTANCE], 6637.65417226, tol
) # ft (not actual value)
# m/s (not actual value)
assert_near_equal(self.prob[Mission.Takeoff.FINAL_VELOCITY], 123.09, tol)
assert_near_equal(
self.prob[Mission.Takeoff.FINAL_MASS], 180623.0, tol
) # lbm (not actual value)
assert_near_equal(self.prob[Mission.Takeoff.FINAL_ALTITUDE], 35, tol) # ft
partial_data = self.prob.check_partials(out_stream=None, method='cs')
assert_check_partials(partial_data, atol=1e-12, rtol=1e-12)
class FinalConditionsTest2(unittest.TestCase):
"""Test mass-weight conversion."""
def setUp(self):
import aviary.mission.energy_state.phases.simplified_takeoff as takeoff
takeoff.GRAV_ENGLISH_LBM = 1.1
def tearDown(self):
import aviary.mission.energy_state.phases.simplified_takeoff as takeoff
takeoff.GRAV_ENGLISH_LBM = 1.0
def test_case1(self):
prob = om.Problem()
prob.model.add_subsystem('comp', FinalTakeoffConditions(), promotes=['*'])
# default value v_stall = 0.1 will worsen the output
prob.model.set_input_defaults('v_stall', val=100, units='m/s')
# default value GROSS_MASS = 150000 will worsen the output
prob.model.set_input_defaults('mass', val=181200.0, units='lbm')
prob.model.set_input_defaults(Mission.Takeoff.FUEL_MASS, val=577, units='lbm') # check
prob.model.set_input_defaults(
Dynamic.Atmosphere.DENSITY,
val=0.0023769,
units='slug/ft**3',
) # check
prob.model.set_input_defaults(Aircraft.Wing.AREA, val=1370.0, units='ft**2') # check
prob.model.set_input_defaults(
Mission.Takeoff.LIFT_COEFFICIENT_MAX, val=2.0000, units='unitless'
) # check
prob.model.set_input_defaults(
Aircraft.Propulsion.TOTAL_SCALED_SLS_THRUST, val=28928.0 * 2, units='lbf'
) # check
prob.model.set_input_defaults(
Mission.Takeoff.CLIMBOUT_THRUST_FRACTION, val=1, units='unitless'
)
prob.model.set_input_defaults(
Mission.Takeoff.LIFT_OVER_DRAG, val=17.354, units='unitless'
) # check
prob.setup(check=False, force_alloc_complex=True)
partial_data = prob.check_partials(out_stream=None, method='cs')
assert_check_partials(partial_data, atol=1e-12, rtol=1e-12)
@use_tempdirs
class TakeoffGroupTest(unittest.TestCase):
"""Test computation in TakeoffGroup."""
def setUp(self):
self.prob = om.Problem()
self.prob.model.add_subsystem('group_example', TakeoffGroup(), promotes=['*'])
self.prob.model.set_input_defaults(Mission.GROSS_MASS, val=181300.0, units='lbm') # check
self.prob.model.set_input_defaults(Mission.Taxi.FUEL_MASS_TAXI_OUT, val=101, units='lbm')
self.prob.model.set_input_defaults(Mission.Takeoff.FUEL_MASS, val=577, units='lbm') # check
self.prob.model.set_input_defaults(Aircraft.Wing.AREA, val=1370.0, units='ft**2') # check
self.prob.model.set_input_defaults(
Mission.Takeoff.LIFT_COEFFICIENT_MAX, val=2.0000, units='unitless'
) # check
self.prob.model.set_input_defaults(
Aircraft.Propulsion.TOTAL_SCALED_SLS_THRUST, val=28928.0 * 2, units='lbf'
) # check
self.prob.model.set_input_defaults(
Mission.Takeoff.CLIMBOUT_THRUST_FRACTION, val=1, units='unitless'
)
self.prob.model.set_input_defaults(
Mission.Takeoff.LIFT_OVER_DRAG, val=17.354, units='unitless'
)
self.prob.model.set_input_defaults(Dynamic.Mission.ALTITUDE, val=0, units='ft') # check
self.prob.setup(check=False, force_alloc_complex=True)
def test_case1(self):
self.prob.run_model()
tol = 1e-5
assert_near_equal(self.prob['end_of_taxi_mass'], 181199, tol)
assert_near_equal(self.prob['v_stall'], 71.90002053, tol)
assert_near_equal(
self.prob[Mission.Takeoff.GROUND_DISTANCE], 6637.65645404, tol
) # ft (not actual value)
assert_near_equal(
self.prob[Mission.Takeoff.FINAL_VELOCITY], 88.50175527, tol
) # m/s (not actual value)
assert_near_equal(
self.prob[Mission.Takeoff.FINAL_MASS], 180623.0, tol
) # lbm (not actual value)
assert_near_equal(self.prob[Mission.Takeoff.FINAL_ALTITUDE], 35, tol) # ft
assert_near_equal(self.prob[Mission.Takeoff.FINAL_MACH], 0.26009873, tol)
partial_data = self.prob.check_partials(
out_stream=None, excludes=['*.standard_atmosphere'], method='cs'
)
assert_check_partials(partial_data, atol=1e-12, rtol=1e-12)
if __name__ == '__main__':
unittest.main()