def test_unit_simplify(self):
comp = Component()
comp.add_input('y', units='ft*ft/ft')
comp.add_output('z', units='ft*ft/ft')
self.assertEqual(comp._static_var_rel2meta['y']['units'], 'ft')
self.assertEqual(comp._static_var_rel2meta['z']['units'], 'ft')
def setup(self, component: Component):
component.add_input("data:propulsion:IC_engine:max_power",
np.nan,
units="W")
component.add_input("data:propulsion:IC_engine:fuel_type", np.nan)
component.add_input("data:propulsion:IC_engine:strokes_nb", np.nan)
component.add_input("data:TLAR:v_cruise", np.nan, units="m/s")
component.add_input("data:mission:sizing:main_route:cruise:altitude",
np.nan,
units="m")
def setup(self, component: Component):
component.add_input("data:TLAR:v_cruise", np.nan, units="m/s")
component.add_input("data:mission:sizing:main_route:cruise:altitude",
np.nan,
units="m")
def setup(self, component: Component):
component.add_input("data:propulsion:rubber_engine:bypass_ratio",
np.nan)
component.add_input(
"data:propulsion:rubber_engine:overall_pressure_ratio", np.nan)
component.add_input(
"data:propulsion:rubber_engine:turbine_inlet_temperature",
np.nan,
units="K")
component.add_input("data:propulsion:MTO_thrust", np.nan, units="N")
component.add_input("data:propulsion:rubber_engine:maximum_mach",
np.nan)
component.add_input("data:propulsion:rubber_engine:design_altitude",
np.nan,
units="m")
component.add_input(
"data:propulsion:rubber_engine:delta_t4_climb",
-50,
desc="As it is a delta, unit is K or °C, but is not "
"specified to avoid OpenMDAO making unwanted conversion",
)
component.add_input(
"data:propulsion:rubber_engine:delta_t4_cruise",
-100,
desc="As it is a delta, unit is K or °C, but is not "
"specified to avoid OpenMDAO making unwanted conversion",
)
def setup(self, component: Component):
component.add_input("data:propulsion:dummy_engine:max_thrust", 1.2e5, units="N")
component.add_input("data:propulsion:dummy_engine:max_sfc", 1.5e-5, units="kg/N/s")
component.add_input("data:geometry:propulsion:engine_count", 2)
