def test_oad_process(cleanup):
"""
Test for the overall aircraft design process.
"""
problem = FASTOADProblemConfigurator(pth.join(INPUT_FOLDER_PATH, "oad_process.toml")).get_problem()
problem.model.aicraft.set_input_defaults('data:geometry:horizontal_tail:sweep_25', val=10., units='deg')
ref_inputs = pth.join(INPUT_FOLDER_PATH, XML_NAME)
get_problem_after_setup(problem).write_needed_inputs(ref_inputs, VariableXmlStandardFormatter())
problem.read_inputs()
print('\n')
problem.setup(check=True)
problem.set_solver_print(level=2)
with Timer(name="Mass-performance loop:"):
problem.run_model()
problem.write_outputs()
if not pth.exists(RESULTS_FOLDER_PATH):
os.mkdir(RESULTS_FOLDER_PATH)
om.view_connections(
problem, outfile=pth.join(RESULTS_FOLDER_PATH, "connections.html"), show_browser=False
)
om.n2(problem, outfile=pth.join(RESULTS_FOLDER_PATH, "n2.html"), show_browser=False)
# 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:max_payload"]
+ problem["data:mission:sizing:fuel"],
rtol=5e-2,
)
assert_allclose(problem.get_val("data:mission:sizing:fuel", units="kg"), 203.65, atol=1)
# noinspection PyTypeChecker
assert_allclose(problem.get_val("data:weight:aircraft:max_payload", units="kg"), 400.0, atol=1)
# noinspection PyTypeChecker
assert_allclose(problem["data:handling_qualities:static_margin"], 0.08515, atol=1e-2)
# noinspection PyTypeChecker
assert_allclose(problem.get_val("data:weight:aircraft:MTOW", units="kg"), 1650.24, atol=1)
# noinspection PyTypeChecker
assert_allclose(problem.get_val("data:weight:aircraft:payload", units="kg"), 360., atol=1)
# noinspection PyTypeChecker
assert_allclose(problem.get_val("data:weight:aircraft:OWE", units="kg"), 1046.61, atol=1)
# noinspection PyTypeChecker
assert_allclose(problem.get_val("data:mission:sizing:main_route:cruise:fuel", units="kg"), 166.405, atol=1)
def test_oad_process(cleanup):
"""
Test for the overall aircraft design process.
"""
problem = FASTOADProblemConfigurator(
pth.join(DATA_FOLDER_PATH, "oad_process.toml")).get_problem()
ref_inputs = pth.join(DATA_FOLDER_PATH, "beechcraft_76.xml")
get_problem_after_setup(problem).write_needed_inputs(
ref_inputs, VariableXmlStandardFormatter())
problem.read_inputs()
print('\n')
problem.setup(check=True)
problem.set_solver_print(level=2)
problem.run_model()
problem.write_outputs()
if not pth.exists(RESULTS_FOLDER_PATH):
os.mkdir(RESULTS_FOLDER_PATH)
om.view_connections(problem,
outfile=pth.join(RESULTS_FOLDER_PATH,
"connections.html"),
show_browser=False)
om.n2(problem,
outfile=pth.join(RESULTS_FOLDER_PATH, "n2.html"),
show_browser=False)
# 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:max_payload"] +
problem["data:mission:sizing:fuel"],
rtol=5e-2,
)
def _run_problem(
configuration_file_path: str,
overwrite: bool = False,
mode="run_model",
auto_scaling: bool = False,
) -> FASTOADProblem:
"""
Runs problem according to provided file
:param configuration_file_path: problem definition
:param overwrite: if True, output file will be overwritten
:param mode: 'run_model' or 'run_driver'
:param auto_scaling: if True, automatic scaling is performed for design variables and constraints
:return: the OpenMDAO problem after run
"""
problem = FASTOADProblemConfigurator(configuration_file_path).get_problem(
read_inputs=True, auto_scaling=auto_scaling)
outputs_path = pth.normpath(problem.output_file_path)
if not overwrite and pth.exists(outputs_path):
raise FastFileExistsError(
"Problem not run because output file %s already exists. "
"Use overwrite=True to bypass." % outputs_path,
outputs_path,
)
problem.setup()
start_time = process_time()
if mode == "run_model":
problem.run_model()
problem.optim_failed = False # Actually, we don't know
else:
problem.optim_failed = problem.run_driver()
end_time = process_time()
computation_time = round(end_time - start_time, 2)
problem.write_outputs()
if problem.optim_failed:
_LOGGER.error("Optimization failed after " + str(computation_time) +
" seconds")
else:
_LOGGER.info("Computation finished after " + str(computation_time) +
" seconds")
_LOGGER.info("Problem outputs written in %s", outputs_path)
return problem
def run_non_regression_test(
conf_file,
legacy_result_file,
result_dir,
use_xfoil=False,
vars_to_check=None,
tolerance=5.0e-3,
check_weight_perfo_loop=True,
):
results_folder_path = pth.join(RESULTS_FOLDER_PATH, result_dir)
configuration_file_path = pth.join(results_folder_path, conf_file)
# Copy of configuration file and generation of problem instance ------------------
api.generate_configuration_file(configuration_file_path) # just ensure folders are created...
shutil.copy(pth.join(DATA_FOLDER_PATH, conf_file), configuration_file_path)
problem = FASTOADProblemConfigurator(configuration_file_path).get_problem()
# Next trick is needed for overloading option setting from TOML file
if use_xfoil and (system() == "Windows" or xfoil_path):
problem.model.aerodynamics_landing._OPTIONS["use_xfoil"] = True
if system() != "Windows":
problem.model.aerodynamics_landing._OPTIONS["xfoil_exe_path"] = xfoil_path
# BTW we narrow computed alpha range for sake of CPU time
problem.model.aerodynamics_landing._OPTIONS["xfoil_alpha_min"] = 18.0
problem.model.aerodynamics_landing._OPTIONS["xfoil_alpha_max"] = 22.0
# Generation and reading of inputs ----------------------------------------
ref_inputs = pth.join(DATA_FOLDER_PATH, legacy_result_file)
get_problem_after_setup(problem).write_needed_inputs(ref_inputs, VariableLegacy1XmlFormatter())
problem.read_inputs()
problem.setup()
# Run model ---------------------------------------------------------------
problem.run_model()
problem.write_outputs()
om.view_connections(
problem, outfile=pth.join(results_folder_path, "connections.html"), show_browser=False
)
if check_weight_perfo_loop:
# 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,
)
ref_var_list = VariableIO(
pth.join(DATA_FOLDER_PATH, legacy_result_file), formatter=VariableLegacy1XmlFormatter(),
).read()
row_list = []
for ref_var in ref_var_list:
try:
value = problem.get_val(ref_var.name, units=ref_var.units)[0]
except KeyError:
continue
row_list.append(
{
"name": ref_var.name,
"units": ref_var.units,
"ref_value": ref_var.value[0],
"value": value,
}
)
df = pd.DataFrame(row_list)
df["rel_delta"] = (df.value - df.ref_value) / df.ref_value
df["rel_delta"][(df.ref_value == 0) & (abs(df.value) <= 1e-10)] = 0.0
df["abs_rel_delta"] = np.abs(df.rel_delta)
pd.set_option("display.max_rows", None)
pd.set_option("display.max_columns", None)
pd.set_option("display.width", 1000)
pd.set_option("display.max_colwidth", 120)
print(df.sort_values(by=["abs_rel_delta"]))
if vars_to_check is not None:
for name in vars_to_check:
row = df.loc[df.name == name]
assert_allclose(row.ref_value, row.value, rtol=tolerance)
# assert np.all(df.abs_rel_delta.loc[df.name == name] < tolerance)
else:
assert np.all(df.abs_rel_delta < tolerance)
def test_oad_process(cleanup):
"""
Test the overall aircraft design process without and with optimization.
"""
test = FASTOADProblemConfigurator(
pth.join(INPUT_FOLDER_PATH, "oad_process.toml"))
problem = FASTOADProblemConfigurator(
pth.join(INPUT_FOLDER_PATH, "oad_process.toml")).get_problem()
recorder = om.SqliteRecorder("cases.sql")
ref_inputs = pth.join(INPUT_FOLDER_PATH, XML_NAME)
get_problem_after_setup(problem).write_needed_inputs(
ref_inputs, VariableXmlStandardFormatter())
problem.read_inputs()
print('\n')
problem.setup(check=True)
solver = problem.model.nonlinear_solver
solver.add_recorder(recorder)
problem.run_model()
problem.write_outputs()
if not pth.exists(RESULTS_FOLDER_PATH):
os.mkdir(RESULTS_FOLDER_PATH)
om.view_connections(problem,
outfile=pth.join(RESULTS_FOLDER_PATH,
"connections.html"),
show_browser=False)
om.n2(problem,
outfile=pth.join(RESULTS_FOLDER_PATH, "n2.html"),
show_browser=False)
# 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,
)
if XML_NAME == "cirrus_sr22.xml":
assert_allclose(problem.get_val("data:mission:sizing:fuel",
units="kg"),
258.831,
atol=1)
# noinspection PyTypeChecker
assert_allclose(
problem["data:handling_qualities:stick_fixed_static_margin"],
0.0728,
atol=1e-2)
# noinspection PyTypeChecker
assert_allclose(problem.get_val("data:weight:aircraft:MTOW",
units="kg"),
1629.7406025,
atol=1)
# noinspection PyTypeChecker
assert_allclose(problem.get_val("data:weight:aircraft:OWE",
units="kg"),
1030.9167,
atol=1)
else:
assert_allclose(problem.get_val("data:mission:sizing:fuel",
units="kg"),
228.624,
atol=1)
# noinspection PyTypeChecker
assert_allclose(
problem["data:handling_qualities:stick_fixed_static_margin"],
0.0252,
atol=1e-2)
# noinspection PyTypeChecker
assert_allclose(problem.get_val("data:weight:aircraft:MTOW",
units="kg"),
1678.863295,
atol=1)
# noinspection PyTypeChecker
assert_allclose(problem.get_val("data:weight:aircraft:OWE",
units="kg"),
1090.2524,
atol=1)