def test_api_eval(cleanup):
results_folder_path = pth.join(RESULTS_FOLDER_PATH, "api_eval")
configuration_file_path = pth.join(results_folder_path, "oad_process.toml")
# Generation of configuration file ----------------------------------------
api.generate_configuration_file(configuration_file_path, True)
# Generation of inputs ----------------------------------------------------
# We get the same inputs as in tutorial notebook
source_xml = pth.join(root_folder_path, "src", "fastoad", "notebooks",
"tutorial", "data", "CeRAS01_baseline.xml")
api.generate_inputs(configuration_file_path, source_xml, overwrite=True)
# Run model ---------------------------------------------------------------
problem = api.evaluate_problem(configuration_file_path, True)
# Check that weight-performances loop correctly converged
assert_allclose(
problem["data:weight:aircraft:OWE"],
problem["data:weight:airframe:mass"] +
problem["data:weight:propulsion:mass"] +
problem["data:weight:systems:mass"] +
problem["data:weight:furniture:mass"] +
problem["data:weight:crew:mass"],
atol=1,
)
assert_allclose(
problem["data:weight:aircraft:MZFW"],
problem["data:weight:aircraft:OWE"] +
problem["data:weight:aircraft:max_payload"],
atol=1,
)
assert_allclose(
problem["data:weight:aircraft:MTOW"],
problem["data:weight:aircraft:OWE"] +
problem["data:weight:aircraft:payload"] +
problem["data:mission:sizing:needed_block_fuel"],
atol=1,
)
assert_allclose(problem["data:handling_qualities:static_margin"],
-0.071146,
atol=1e-3)
assert_allclose(problem["data:geometry:wing:MAC:at25percent:x"],
16.0,
atol=1e-2)
assert_allclose(problem["data:weight:aircraft:MTOW"], 76796, atol=1)
assert_allclose(problem["data:geometry:wing:area"], 131.26, atol=1e-2)
assert_allclose(problem["data:geometry:vertical_tail:area"],
27.49,
atol=1e-2)
assert_allclose(problem["data:geometry:horizontal_tail:area"],
33.99,
atol=1e-2)
assert_allclose(problem["data:mission:sizing:needed_block_fuel"],
20708,
atol=1)
def test_api_optim(cleanup):
results_folder_path = pth.join(RESULTS_FOLDER_PATH, "api_optim")
configuration_file_path = pth.join(results_folder_path, "oad_process.toml")
# Generation of configuration file ----------------------------------------
api.generate_configuration_file(configuration_file_path, True)
# Generation of inputs ----------------------------------------------------
# We get the same inputs as in tutorial notebook
source_xml = pth.join(root_folder_path, "src", "fastoad", "notebooks",
"tutorial", "data", "CeRAS01_baseline.xml")
api.generate_inputs(configuration_file_path, source_xml, overwrite=True)
# Run optim ---------------------------------------------------------------
problem = api.optimize_problem(configuration_file_path, True)
assert not problem.optim_failed
# Check that weight-performances loop correctly converged
assert_allclose(
problem["data:weight:aircraft:OWE"],
problem["data:weight:airframe:mass"] +
problem["data:weight:propulsion:mass"] +
problem["data:weight:systems:mass"] +
problem["data:weight:furniture:mass"] +
problem["data:weight:crew:mass"],
atol=1,
)
assert_allclose(
problem["data:weight:aircraft:MZFW"],
problem["data:weight:aircraft:OWE"] +
problem["data:weight:aircraft:max_payload"],
atol=1,
)
assert_allclose(
problem["data:weight:aircraft:MTOW"],
problem["data:weight:aircraft:OWE"] +
problem["data:weight:aircraft:payload"] +
problem["data:mission:sizing:needed_block_fuel"],
atol=1,
)
# Design Variable
assert_allclose(problem["data:geometry:wing:MAC:at25percent:x"],
17.076,
atol=1e-3)
# Constraint
assert_allclose(problem["data:handling_qualities:static_margin"],
0.05,
rtol=1e-5)
# Objective
assert_allclose(problem["data:mission:sizing:needed_block_fuel"],
20837,
atol=1)
def est_api(cleanup):
# Generation of inputs ----------------------------------------------------
# We get the same inputs as in tutorial notebook
DATA_FOLDER_PATH = pth.join(NOTEBOOKS_PATH, "tutorial", "data")
WORK_FOLDER_PATH = pth.join(NOTEBOOKS_PATH, "tutorial", "workdir")
configuration_file = pth.join(WORK_FOLDER_PATH, "oad_process.toml")
SOURCE_FILE = pth.join(DATA_FOLDER_PATH, XML_NAME)
_api.generate_configuration_file(configuration_file, overwrite=True)
# Run 800NM model ---------------------------------------------------------
api.generate_inputs(configuration_file, SOURCE_FILE, overwrite=True)
api.evaluate_problem(configuration_file, True)
OUTPUT_FILE = pth.join(WORK_FOLDER_PATH, 'problem_outputs.xml')
Beechcraft_800nm_OUTPUT_FILE = pth.join(WORK_FOLDER_PATH, 'problem_outputs_Beechcraft_800nm_mda.xml')
copy(OUTPUT_FILE, Beechcraft_800nm_OUTPUT_FILE)
# Run 1000NM model --------------------------------------------------------
viewer = VariableViewer()
viewer.load(SOURCE_FILE)
index = np.where(viewer.dataframe['Name'] == 'data:TLAR:range')[0][0]
viewer.dataframe.at[index, 'Value'] = 1000.0
viewer.save(SOURCE_FILE)
api.generate_inputs(configuration_file, SOURCE_FILE, overwrite=True)
api.evaluate_problem(configuration_file, True)
OUTPUT_FILE = pth.join(WORK_FOLDER_PATH, 'problem_outputs.xml')
Beechcraft_1000nm_OUTPUT_FILE = pth.join(WORK_FOLDER_PATH, 'problem_outputs_Beechcraft_1000nm_mda.xml')
copy(OUTPUT_FILE, Beechcraft_1000nm_OUTPUT_FILE)
# Try geometry plot -------------------------------------------------------
fig = wing_geometry_plot(Beechcraft_800nm_OUTPUT_FILE, name='Beechcraft 800 nm MDA')
fig = wing_geometry_plot(Beechcraft_1000nm_OUTPUT_FILE, name='Beechcraft 1000 nm MDA', fig=fig)
fig.show()
fig = aircraft_geometry_plot(Beechcraft_800nm_OUTPUT_FILE, name='Beechcraft 800 nm MDA')
fig = aircraft_geometry_plot(Beechcraft_1000nm_OUTPUT_FILE, name='Beechcraft 1000 nm MDA', fig=fig)
fig.show()
# Try mass breakdown ------------------------------------------------------
fig = mass_breakdown_sun_plot(Beechcraft_800nm_OUTPUT_FILE)
fig.show()
fig = mass_breakdown_bar_plot(Beechcraft_800nm_OUTPUT_FILE, name='Beechcraft 800 nm MDA')
fig = mass_breakdown_bar_plot(Beechcraft_1000nm_OUTPUT_FILE, name='Beechcraft 1000 nm MDA', fig=fig)
fig.show()
# Run optimization --------------------------------------------------------
viewer = VariableViewer()
viewer.load(SOURCE_FILE)
index = np.where(viewer.dataframe['Name'] == 'data:TLAR:range')[0][0]
viewer.dataframe.at[index, 'Value'] = 800.0
viewer.save(SOURCE_FILE)
api.generate_inputs(configuration_file, SOURCE_FILE, overwrite=True)
problem = api.optimize_problem(configuration_file, True)
assert not problem.optim_failed
# Check that weight-performances loop correctly converged
assert_allclose(
problem["data:weight:aircraft:OWE"],
problem["data:weight:airframe:mass"]
+ problem["data:weight:propulsion:mass"]
+ problem["data:weight:systems:mass"]
+ problem["data:weight:furniture:mass"]
+ problem["data:weight:crew:mass"],
atol=1,
)
assert_allclose(
problem["data:weight:aircraft:MZFW"],
problem["data:weight:aircraft:OWE"] + problem["data:weight:aircraft:max_payload"],
atol=1,
)
assert_allclose(
problem["data:weight:aircraft:MTOW"],
problem["data:weight:aircraft:OWE"]
+ problem["data:weight:aircraft:payload"]
+ problem["data:mission:sizing:fuel"],
atol=1,
)
# Design Variable
assert_allclose(problem["data:geometry:wing:MAC:at25percent:x"], 17.06, atol=1e-1)
# Constraint
assert_allclose(problem["data:handling_qualities:static_margin"], 0.05, atol=1e-2)
# Objective
assert_allclose(problem["data:mission:sizing:fuel"], 20565, atol=50)
def test_api(cleanup):
# Generation of inputs ----------------------------------------------------
# We get the same inputs as in tutorial notebook
configuration_file = pth.join(NOTEBOOKS_PATH, "tutorial", "workdir",
"oad_process.toml")
source_file = pth.join(NOTEBOOKS_PATH, "tutorial", "data",
"beechcraft_76.xml")
_api.generate_configuration_file(configuration_file, overwrite=True)
api.generate_inputs(configuration_file, source_file, overwrite=True)
# Run model ---------------------------------------------------------------
problem = api.evaluate_problem(configuration_file, True)
# Check that weight-performances loop correctly converged
assert_allclose(
problem["data:weight:aircraft:OWE"],
problem["data:weight:airframe:mass"] +
problem["data:weight:propulsion:mass"] +
problem["data:weight:systems:mass"] +
problem["data:weight:furniture:mass"],
rtol=5e-2,
)
assert_allclose(
problem["data:weight:aircraft:MZFW"],
problem["data:weight:aircraft:OWE"] +
problem["data:weight:aircraft:max_payload"],
rtol=5e-2,
)
assert_allclose(
problem["data:weight:aircraft:MTOW"],
problem["data:weight:aircraft:OWE"] +
problem["data:weight:aircraft:payload"] +
problem["data:mission:sizing:fuel"],
rtol=5e-2,
)
assert_allclose(problem["data:handling_qualities:static_margin"],
-0.005519,
atol=1e-3)
assert_allclose(problem["data:geometry:wing:MAC:at25percent:x"],
16.5,
atol=1e-2)
assert_allclose(problem["data:weight:aircraft:MTOW"], 77065, atol=1)
assert_allclose(problem["data:geometry:wing:area"], 130.29, atol=1e-2)
assert_allclose(problem["data:geometry:vertical_tail:area"],
27.65,
atol=1e-2)
assert_allclose(problem["data:geometry:horizontal_tail:area"],
35.25,
atol=1e-2)
assert_allclose(problem["data:mission:sizing:fuel"], 20494, atol=1)
# Run optim ---------------------------------------------------------------
problem = api.optimize_problem(configuration_file, True)
assert not problem.optim_failed
# Check that weight-performances loop correctly converged
assert_allclose(
problem["data:weight:aircraft:OWE"],
problem["data:weight:airframe:mass"] +
problem["data:weight:propulsion:mass"] +
problem["data:weight:systems:mass"] +
problem["data:weight:furniture:mass"] +
problem["data:weight:crew:mass"],
atol=1,
)
assert_allclose(
problem["data:weight:aircraft:MZFW"],
problem["data:weight:aircraft:OWE"] +
problem["data:weight:aircraft:max_payload"],
atol=1,
)
assert_allclose(
problem["data:weight:aircraft:MTOW"],
problem["data:weight:aircraft:OWE"] +
problem["data:weight:aircraft:payload"] +
problem["data:mission:sizing:fuel"],
atol=1,
)
# Design Variable
assert_allclose(problem["data:geometry:wing:MAC:at25percent:x"],
17.06,
atol=1e-1)
# Constraint
assert_allclose(problem["data:handling_qualities:static_margin"],
0.05,
atol=1e-2)
# Objective
assert_allclose(problem["data:mission:sizing:fuel"], 20565, atol=50)