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)