def setup(self):
shape = self.options['shape']
part = self.options['part']
lift_coeff_zero_alpha = part['lift_coeff_zero_alpha']
lift_curve_slope_2D = part['lift_curve_slope_2D']
dynamic_pressure_ratio = part['dynamic_pressure_ratio']
downwash_slope = part['downwash_slope']
wing_exposed_ratio = part['wing_exposed_ratio']
fuselage_diameter_span = part['fuselage_diameter_span']
comp = LiftCurveSlopeDenominatorComp(
shape=shape,
lift_curve_slope_2D=lift_curve_slope_2D,
wing_exposed_ratio=wing_exposed_ratio,
fuselage_diameter_span=fuselage_diameter_span,
)
self.add_subsystem('lift_curve_slope_denominator_comp',
comp,
promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='lift_curve_slope',
coeff=2 * np.pi * wing_exposed_ratio * 1.07 *
(1. + fuselage_diameter_span)**2.,
powers_dict=dict(
aspect_ratio=1.,
lift_curve_slope_denominator=-1.,
),
)
self.add_subsystem('lift_curve_slope_comp', comp, promotes=['*'])
comp = LinearCombinationComp(
shape=shape,
out_name='lift_curve_slope_modified',
coeffs_dict=dict(lift_curve_slope=(1 - downwash_slope) *
dynamic_pressure_ratio, ))
self.add_subsystem('lift_curve_slope_modified_comp',
comp,
promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='lift_coeff',
constant=dynamic_pressure_ratio * lift_coeff_zero_alpha,
terms_list=[
(dynamic_pressure_ratio * (1 - downwash_slope),
dict(
lift_curve_slope=1.,
alpha=1.,
)),
(dynamic_pressure_ratio,
dict(
lift_curve_slope=1.,
incidence_angle=1.,
)),
],
)
self.add_subsystem('lift_coeff_comp', comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
module = self.options['options_dictionary']
comp = IndepVarComp()
comp.add_output('throttle', shape=shape)
comp.add_output('sealevel_density', val=1.225, shape=shape)
self.add_subsystem('inputs_comp', comp, promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='available_power',
terms_list=[
(1.132,
dict(
density=1.,
sealevel_density=-1.,
sealevel_power=1.,
)),
(-0.132, dict(sealevel_power=1., )),
],
)
self.add_subsystem('available_power_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='power',
powers_dict=dict(
throttle=1.,
available_power=1.,
),
)
self.add_subsystem('power_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='mass_flow_rate',
coeff=module['brake_specific_fuel_consumption'],
powers_dict=dict(power=1., ),
)
self.add_subsystem('mass_flow_rate_comp', comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
part = self.options['part']
comp = IndepVarComp()
comp.add_output('sweep_30', val=30. * np.pi / 180., shape=shape)
self.add_subsystem('sweep_30_comp', comp, promotes=['*'])
comp = ElementwiseMinComp(
shape=shape,
out_name='sweep_capped_30',
in_names=['sweep', 'sweep_30'],
rho=50.,
)
self.add_subsystem('sweep_capped_30_comp', comp, promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='oswald_efficiency_unswept',
constant=1.14,
terms_list=[
(-1.78 * 0.045, dict(aspect_ratio=0.68, )),
],
)
self.add_subsystem('oswald_efficiency_unswept_comp',
comp,
promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='oswald_efficiency_swept',
constant=-3.1,
terms_list=[
(4.61, dict(cos_sweep=0.15, )),
(-4.61 * 0.045, dict(
aspect_ratio=0.68,
cos_sweep=0.15,
)),
],
)
self.add_subsystem('oswald_efficiency_swept_comp',
comp,
promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='oswald_efficiency',
terms_list=[
(1., dict(oswald_efficiency_unswept=1., )),
(-1. / (30. * np.pi / 180.),
dict(
oswald_efficiency_unswept=1.,
sweep_capped_30=1.,
)),
(1. / (30. * np.pi / 180.),
dict(
oswald_efficiency_swept=1.,
sweep_capped_30=1.,
)),
],
)
self.add_subsystem('oswald_efficiency_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='induced_drag_coeff',
coeff=1. / np.pi,
powers_dict=dict(
lift_coeff=2.,
oswald_efficiency=-1.,
aspect_ratio=-1.,
),
)
self.add_subsystem('induced_drag_coeff_comp', comp, promotes=['*'])
# prob.model.add_subsystem('lift_comp', comp, promotes=['*'])
# comp = thrustComp()
# prob.model.add_subsystem('thrust_comp', comp, promotes=['*'])
# Computes E = L/D for use in the breguet range component
comp = ExecComp('LD = CL/CD')
prob.model.add_subsystem('ld_comp', comp, promotes=['*'])
# comp = ExecComp('TOD = thrust - drag ')
# prob.model.add_subsystem('TOD', comp, promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='LOW',
terms_list=[
(1.0, dict(L=1., )),
(-9.81, dict(emptyTotal=1, )),
],
)
prob.model.add_subsystem('LOW', comp, promotes=['*'])
prob.model.connect('aero_point_0.CL', 'CL')
prob.model.connect('aero_point_0.CD', 'CD')
prob.model.connect('aero_point_0.wing_perf.L', 'L')
prob.model.connect('dihedral', 'wing.mesh.dihedral.dihedral')
# prob.model.connect('chord', 'wing.mesh.scale_x.chord'[0])
# Import the Scipy Optimizer and set the driver of the problem to use
# it, which defaults to an SLSQP optimization method
# # recorder = om.SqliteRecorder("aero.db")
def setup(self):
shape = self.options['shape']
# module = self.options['options_dictionary']
#
comp = PercentBlownComp()
self.add_subsystem('percent_blown_comp', comp, promotes=['*'])
comp = AxialIntComp()
self.add_subsystem('axial_int_comp', comp, promotes=['*'])
comp = AverageAxialIntComp()
self.add_subsystem('average_axial_int_comp', comp, promotes=['*'])
comp = CLWingComp()
self.add_subsystem('cl_wing_comp', comp, promotes=['*'])
comp = CLTailComp()
self.add_subsystem('cl_tail_comp', comp, promotes=['*'])
comp = CDiWingComp()
self.add_subsystem('cdi_wing_comp', comp, promotes=['*'])
comp = CDiTailComp()
self.add_subsystem('cdi_tail_comp', comp, promotes=['*'])
# comp = ExecComp('wing_lift = wing_CL*q*wing_area')
# self.add_subsystem('wing_lift_comp', comp, promotes= ['*'])
comp = PowerCombinationComp(shape=shape,
out_name='wing_lift',
coeff=0.5,
powers_dict=dict(
wing_CL=1.,
density=1.,
v_inf=2.,
wing_area=1.,
))
self.add_subsystem('wing_lift_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='tail_lift',
coeff=0.5,
powers_dict=dict(
tail_CL=1.,
density=1.,
v_inf=2.,
tail_area=1.,
))
self.add_subsystem('tail_lift_comp', comp, promotes=['*'])
comp = LinearCombinationComp(shape=shape,
out_name='total_lift',
constant=0.,
coeffs_dict=dict(
wing_lift=1.,
tail_lift=1.,
))
self.add_subsystem('total_lift_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='wing_Re',
coeff=1.,
powers_dict=dict(
density=1.,
v_inf=1.,
wing_chord=1.,
dynamic_viscosity=-1.,
))
self.add_subsystem('wing_Re_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='tail_Re',
coeff=1.,
powers_dict=dict(
density=1.,
v_inf=1.,
tail_chord=1.,
dynamic_viscosity=-1.,
))
self.add_subsystem('tail_Re_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='fuselage_Re',
coeff=1.,
powers_dict=dict(
density=1.,
v_inf=1.,
fuselage_length=1.,
dynamic_viscosity=-1.,
))
self.add_subsystem('fuselage_Re_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='vertical_tail_Re',
coeff=1.,
powers_dict=dict(
density=1.,
v_inf=1.,
vertical_tail_mac=1.,
dynamic_viscosity=-1.,
))
self.add_subsystem('vertical_tail_Re_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='mach_number',
coeff=1.,
powers_dict=dict(v_inf=1.,
sonic_speed=-1.))
self.add_subsystem('mach_number_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='wing_skin_friction',
coeff=1.328,
powers_dict=dict(wing_Re=-0.5, ))
self.add_subsystem('wing_skin_friction_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='tail_skin_friction',
coeff=1.328,
powers_dict=dict(tail_Re=-0.5, ))
self.add_subsystem('tail_skin_friction_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='fuselage_skin_friction',
coeff=1.328,
powers_dict=dict(fuselage_Re=-0.5, ))
self.add_subsystem('fuselage_skin_friction_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='vertical_tail_skin_friction',
coeff=1.328,
powers_dict=dict(vertical_tail_Re=-0.5, ))
self.add_subsystem('vertical_tail_skin_friction_comp',
comp,
promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='wing_form_factor_1',
terms_list=[
(100, dict(wing_tc=4., )),
(2, dict(
wing_tc=1.,
wing_chord=-1.,
)),
],
constant=1.,
)
self.add_subsystem('wing_form_factor_1_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='form_factor_mach_component',
coeff=1.34,
powers_dict=dict(mach_number=0.18))
self.add_subsystem('form_factor_mach_component_comp',
comp,
promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='wing_form_factor',
coeff=1.,
powers_dict=dict(
wing_form_factor_1=1.,
form_factor_mach_component=1.,
))
self.add_subsystem('wing_form_factor_comp', comp, promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='tail_form_factor_1',
terms_list=[
(100, dict(tail_tc=4., )),
(2, dict(
tail_tc=1.,
tail_chord=-1.,
)),
],
constant=1.,
)
self.add_subsystem('tail_form_factor_1_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='tail_form_factor',
coeff=1.,
powers_dict=dict(
tail_form_factor_1=1.,
form_factor_mach_component=1.,
))
self.add_subsystem('tail_form_factor_comp', comp, promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='vertical_tail_form_factor_1',
terms_list=[
(100, dict(tail_tc=4., )),
(2, dict(
vertical_tail_tc=1.,
vertical_tail_mac=-1.,
)),
],
constant=1.,
)
self.add_subsystem('vertical_tail_form_factor_1_comp',
comp,
promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='vertical_tail_form_factor',
coeff=1.,
powers_dict=dict(
vertical_tail_form_factor_1=1.,
form_factor_mach_component=1.,
))
self.add_subsystem('vertical_tail_form_factor_comp',
comp,
promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='wing_wetted_area',
coeff=2.3,
powers_dict=dict(wing_area=1., ))
self.add_subsystem('wing_wetted_area_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='tail_wetted_area',
coeff=2.3,
powers_dict=dict(tail_area=1., ))
self.add_subsystem('tail_wetted_area_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='vertical_tail_wetted_area',
coeff=2.3,
powers_dict=dict(vertical_tail_area=1., ))
self.add_subsystem('vertical_tail_wetted_area_comp',
comp,
promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='parasite_drag_wing',
coeff=1.1,
powers_dict=dict(
wing_skin_friction=1.,
wing_form_factor=1.,
wing_wetted_area=1.,
wing_area=-1.,
))
self.add_subsystem('parasite_drag_wing_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='parasite_drag_tail',
coeff=1.1,
powers_dict=dict(
tail_skin_friction=1.,
tail_form_factor=1.,
tail_wetted_area=1.,
wing_area=-1.,
))
self.add_subsystem('parasite_drag_tail_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='parasite_drag_fuselage',
coeff=1.1,
powers_dict=dict(
fuselage_skin_friction=1.,
fuselage_form_factor=1.,
fuselage_wetted_area=1.,
wing_area=-1.,
))
self.add_subsystem('parasite_drag_fuselage_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='parasite_drag_vertical_tail',
coeff=1.1,
powers_dict=dict(
vertical_tail_skin_friction=1.,
vertical_tail_form_factor=1.,
vertical_tail_wetted_area=1.,
wing_area=-1.,
))
self.add_subsystem('parasite_drag_vertical_tail_comp',
comp,
promotes=['*'])
comp = LinearCombinationComp(shape=shape,
out_name='parasite_CD0',
constant=0.,
coeffs_dict=dict(
parasite_drag_wing=1.,
parasite_drag_tail=1.,
parasite_drag_fuselage=1.,
parasite_drag_vertical_tail=1.,
))
self.add_subsystem('parasite_drag_comp', comp, promotes=['*'])
comp = LinearCombinationComp(shape=shape,
out_name='total_CD',
constant=0.,
coeffs_dict=dict(
parasite_CD0=1.,
wing_CDi=1.,
tail_CDi=1.,
))
self.add_subsystem('total_CD_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='total_drag',
coeff=0.5,
powers_dict=dict(
total_CD=1.,
density=1.,
v_inf=2.,
wing_area=1.,
))
self.add_subsystem('total_drag_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='lift_drag_ratio',
coeff=1.,
powers_dict=dict(
total_lift=1.,
total_drag=-1.,
))
self.add_subsystem('lift_drag_ratio', comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
comp = PowerCombinationComp(
shape = shape,
out_name = 'total_avail_energy',
coeff = 3600.,
powers_dict=dict(
battery_mass = 1.,
batter_energy_density = 1.,
)
)
self.add_subsystem('total_avail_energy_comp', comp, promotes = ['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'total_avail_energy_kWh',
coeff = 3600/(1000*3600),
powers_dict=dict(
battery_mass = 1.,
batter_energy_density = 1.,
)
)
self.add_subsystem('total_avail_energy_kWh_comp', comp, promotes = ['*'])
comp = LinearPowerCombinationComp(
shape = shape,
out_name = 'cruise_average_prop_efficiency',
terms_list=[
(1/6, dict(
cruise_tail_right_eff = 1.,
)),
(1/6, dict(
cruise_tail_left_eff = 1.,
)),
(1/6, dict(
cruise_wing_right_outer_eff = 1.,
)),
(1/6, dict(
cruise_wing_right_inner_eff = 1.,
)),
(1/6, dict(
cruise_wing_left_outer_eff = 1.,
)),
(1/6, dict(
cruise_wing_left_inner_eff = 1.,
)),
],
constant = 0.,
)
self.add_subsystem('cruise_average_prop_efficiency_comp', comp, promotes = ['*'])
comp = LinearPowerCombinationComp(
shape = shape,
out_name = 'hover_average_prop_efficiency',
terms_list=[
(1/6, dict(
hover_tail_right_eff = 1.,
)),
(1/6, dict(
hover_tail_left_eff = 1.,
)),
(1/6, dict(
hover_wing_right_outer_eff = 1.,
)),
(1/6, dict(
hover_wing_right_inner_eff = 1.,
)),
(1/6, dict(
hover_wing_left_outer_eff = 1.,
)),
(1/6, dict(
hover_wing_left_inner_eff = 1.,
)),
],
constant = 0.,
)
self.add_subsystem('hover_average_prop_efficiency_comp', comp, promotes = ['*'])
comp = LinearPowerCombinationComp(
shape = shape,
out_name = 'cruise_total_power',
terms_list=[
(1, dict(
cruise_tail_right_power = 1.,
)),
(1, dict(
cruise_tail_left_power = 1.,
)),
(1, dict(
cruise_wing_right_outer_power = 1.,
)),
(1, dict(
cruise_wing_right_inner_power = 1.,
)),
(1, dict(
cruise_wing_left_outer_power = 1.,
)),
(1, dict(
cruise_wing_left_inner_power = 1.,
)),
],
constant = 0.,
)
self.add_subsystem('cruise_total_power_comp', comp, promotes = ['*'])
comp = LinearPowerCombinationComp(
shape = shape,
out_name = 'hover_total_power',
terms_list=[
(1, dict(
hover_tail_right_power = 1.,
)),
(1, dict(
hover_tail_left_power = 1.,
)),
(1, dict(
hover_wing_right_outer_power = 1.,
)),
(1, dict(
hover_wing_right_inner_power = 1.,
)),
(1, dict(
hover_wing_left_outer_power = 1.,
)),
(1, dict(
hover_wing_left_inner_power = 1.,
)),
],
constant = 0.,
)
self.add_subsystem('hover_total_power_comp', comp, promotes = ['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'cruise_time',
coeff = 1.,
powers_dict = dict(
distance = 1.,
v_inf = -1.,
)
)
self.add_subsystem('cruise_time', comp, promotes = ['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'cruise_energy_expenditure_kWh',
coeff = 1/3600000,
powers_dict=dict(
cruise_time = 1.,
cruise_total_power = 1.,
)
)
self.add_subsystem('cruise_energy_expenditure_comp', comp, promotes = ['*'])
comp = LinearCombinationComp(
shape = shape,
out_name = 'total_flight_time',
constant = 0.,
coeffs_dict=dict(
cruise_time = 1.,
t_tol = 1.,
)
)
self.add_subsystem('total_flight_time_comp', comp, promotes = ['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'trips_per_flight_hour',
coeff = 3600.,
powers_dict=dict(
total_flight_time = -1.,
)
)
self.add_subsystem('trips_per_flight_hour', comp, promotes= ['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'hover_energy_expenditure_kWh',
coeff = 1/1000,
powers_dict=dict(
t_tol = 1.,
hover_total_power = 1.,
)
)
self.add_subsystem('hover_energy_expenditure_comp', comp, promotes = ['*'])
comp = LinearCombinationComp(
shape = shape,
out_name = 'energy_expenditure_per_trip_kWh',
constant = 0.,
coeffs_dict=dict(
hover_energy_expenditure_kWh = 1.,
cruise_energy_expenditure_kWh = 1.,
)
)
self.add_subsystem('energy_expenditure_per_trip_comp',comp, promotes = ['*'])
comp = LinearCombinationComp(
shape = shape,
out_name = 'energy_remaining',
constant = 0.,
coeffs_dict=dict(
total_avail_energy =1.,
cruise_energy_expenditure_kWh = -1.,
hover_energy_expenditure_kWh = -1.,
)
)
self.add_subsystem('energy_remaining_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'trips_per_charge',
coeff = 1/(3600*1000),
powers_dict=dict(
total_avail_energy = 1.,
energy_expenditure_per_trip_kWh = -1.,
)
)
self.add_subsystem('trips_per_charge_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'aircraft_range',
coeff = 1,
powers_dict = dict(
distance = 1.,
trips_per_charge = 1.,
)
)
self.add_subsystem('aircraft_range_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'design_range_energy_expenditure',
coeff = 1.,
powers_dict=dict(
distance = 1.,
GrossWeight = 1.,
cruise_average_prop_efficiency = -1.,
lift_drag_ratio = -1.,
)
)
self.add_subsystem('design_range_energy_expenditure_comp', comp, promotes = ['*'])
comp = LinearCombinationComp(
shape = shape,
out_name = 'energy_remaining_1',
constant = 0.,
coeffs_dict=dict(
total_avail_energy =1.,
design_range_energy_expenditure = -1.,
)
)
self.add_subsystem('energy_remaining_1_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'Electric_Range_Equation',
coeff = 1.,
powers_dict=dict(
cruise_average_prop_efficiency = 1.,
batter_energy_density = 1.,
lift_drag_ratio = 1.,
battery_mass = 1.,
GrossWeight = -1.,
)
)
self.add_subsystem('Electric_Range_Equation_comp', comp, promotes = ['*'])
def setup(self):
shape = self.options['shape']
aircraft = self.options['aircraft']
geometry = self.options['geometry']
options_dictionary = self.options['options_dictionary']
comp = IndepVarComp()
comp.add_output('dummy_var')
self.add_subsystem('inputs_comp', comp, promotes=['*'])
for part in geometry.children:
name = part['name']
group = Group()
# Passthrough for area
if isinstance(part, LiftingSurfaceGeometry):
comp = LinearCombinationComp(
shape=shape,
out_name='_area',
coeffs_dict=dict(
area=1.,
),
)
group.add_subsystem('area_comp', comp, promotes=['*'])
else:
comp = IndepVarComp()
comp.add_output('_area', shape=shape)
group.add_subsystem('area_comp', comp, promotes=['*'])
# Cosine of sweep - useful for many calculations that follow
if isinstance(part, LiftingSurfaceGeometry):
def func(sweep):
return np.cos(sweep)
def deriv(sweep):
return (-np.sin(sweep))
comp = GeneralOperationComp(
shape=shape,
out_name='cos_sweep',
in_names=['sweep'],
func=func,
deriv=deriv,
)
group.add_subsystem('cos_sweep_comp', comp, promotes=['*'])
# Lift coefficient
if isinstance(part, LiftingSurfaceGeometry):
lift_group = LiftGroup(
shape=shape,
part=part,
)
group.add_subsystem('lift_group', lift_group, promotes=['*'])
elif isinstance(part, PartGeometry):
comp = LinearCombinationComp(
shape=shape,
out_name='dummy_comp_var',
coeffs_dict=dict(
ref_area=1.,
alpha=1.,
wetted_area=1.,
characteristic_length=1.,
),
)
group.add_subsystem('dummy_comp', comp, promotes=['*'])
comp = IndepVarComp()
comp.add_output('lift_coeff', val=0., shape=shape)
group.add_subsystem('lift_coeff_comp', comp, promotes=['*'])
else:
comp = LinearCombinationComp(
shape=shape,
out_name='dummy_comp_var',
coeffs_dict=dict(
alpha=1.,
),
)
group.add_subsystem('dummy_comp', comp, promotes=['*'])
comp = IndepVarComp()
comp.add_output('lift_coeff', val=0., shape=shape)
group.add_subsystem('lift_coeff_comp', comp, promotes=['*'])
# Induced drag coefficient
if isinstance(part, LiftingSurfaceGeometry):
induced_drag_group = InducedDragGroup(
shape=shape,
part=part,
)
group.add_subsystem('induced_drag_group', induced_drag_group, promotes=['*'])
else:
comp = IndepVarComp()
comp.add_output('induced_drag_coeff', val=0., shape=shape)
group.add_subsystem('induced_drag_coeff_comp', comp, promotes=['*'])
# Skin friction coefficient
skin_friction_group = SkinFrictionGroup(
shape=shape,
aircraft=aircraft,
part=part,
)
group.add_subsystem('skin_friction_group', skin_friction_group, promotes=['*'])
# Parasite drag coefficient---form factor
if isinstance(part, LiftingSurfaceGeometry):
thickness_chord = part['thickness_chord']
max_thickness_location = part['max_thickness_location']
comp = PowerCombinationComp(
shape=shape,
out_name='form_factor',
coeff=1.34 * (1 + 0.6 / max_thickness_location * thickness_chord + 100. * thickness_chord ** 4),
powers_dict=dict(
mach_number=0.18,
cos_sweep=0.28,
),
)
group.add_subsystem('form_factor_comp', comp, promotes=['*'])
elif isinstance(part, BodyGeometry):
fuselage_aspect_ratio = part['fuselage_aspect_ratio']
comp = IndepVarComp()
comp.add_output('form_factor', val=1 + 60. / fuselage_aspect_ratio ** 3. + fuselage_aspect_ratio / 400., shape=shape)
group.add_subsystem('form_factor_comp', comp, promotes=['*'])
# Parasite drag coefficient---interference factor
comp = IndepVarComp()
comp.add_output('interference_factor', val=part['interference_factor'], shape=shape)
group.add_subsystem('interference_factor_comp', comp, promotes=['*'])
# Parasite drag coefficient
if isinstance(part, (LiftingSurfaceGeometry, BodyGeometry)):
comp = PowerCombinationComp(
shape=shape,
out_name='parasite_drag_coeff',
powers_dict=dict(
skin_friction_coeff=1.,
form_factor=1.,
interference_factor=1.,
wetted_area=1.,
ref_area=-1.,
),
)
group.add_subsystem('parasite_drag_coeff_comp', comp, promotes=['*'])
elif isinstance(part, PartGeometry):
comp = IndepVarComp()
comp.add_output('parasite_drag_coeff', val=part['parasite_drag_coeff'], shape=shape)
group.add_subsystem('parasite_drag_coeff_comp', comp, promotes=['*'])
else:
comp = IndepVarComp()
comp.add_output('parasite_drag_coeff', val=0., shape=shape)
group.add_subsystem('parasite_drag_coeff_comp', comp, promotes=['*'])
# Wave drag coefficient
if isinstance(part, LiftingSurfaceGeometry):
airfoil_technology_factor = part['airfoil_technology_factor']
thickness_chord = part['thickness_chord']
comp = LinearPowerCombinationComp(
shape=shape,
out_name='critical_mach_number',
constant=-(0.1 / 80.) ** (1. / 3.),
terms_list=[
(airfoil_technology_factor, dict(
cos_sweep=-1.,
)),
(-thickness_chord, dict(
cos_sweep=-2.,
)),
(-0.1, dict(
cos_sweep=-3.,
lift_coeff=1.,
)),
],
)
group.add_subsystem('critical_mach_number_comp', comp, promotes=['*'])
comp = WaveDragCoeffComp(shape=shape)
group.add_subsystem('wave_drag_coeff_comp', comp, promotes=['*'])
else:
comp = IndepVarComp()
comp.add_output('wave_drag_coeff', val=0., shape=shape)
group.add_subsystem('wave_drag_coeff_comp', comp, promotes=['*'])
self.add_subsystem('{}_group'.format(name), group, promotes=[
'density',
'speed',
'ref_area',
'dynamic_viscosity',
'alpha',
'mach_number',
])
#
names = []
lift_coeff_names = []
lift_coeff_connects = []
area_names = []
area_connects = []
for part in geometry.children:
name = part['name']
lift_coeff_name = '{}_group_lift_coeff'.format(name)
src_lift_coeff_name = '{}_group.lift_coeff'.format(name)
area_name = '{}_group_area'.format(name)
src_area_name = '{}_group._area'.format(name)
lift_coeff_names.append(lift_coeff_name)
lift_coeff_connects.append((src_lift_coeff_name, lift_coeff_name))
area_names.append(area_name)
area_connects.append((src_area_name, area_name))
names.append(name)
comp = LinearPowerCombinationComp(
shape=shape,
out_name='lift_coeff',
terms_list=[
(1., {
lift_coeff_name: 1.,
area_name: 1.,
'ref_area': -1.,
})
for lift_coeff_name, area_name in zip(lift_coeff_names, area_names)
],
)
self.add_subsystem('lift_coeff_comp', comp, promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='drag_coeff',
terms_list=[
(1., {
'{}_group_induced_drag_coeff'.format(name): 1.,
area_name: 1.,
'ref_area': -1.,
})
for name, area_name in zip(names, area_names)
] + [
(1., {
'{}_group_parasite_drag_coeff'.format(name): 1.,
# area_name: 0.,
# 'ref_area': 0.,
})
for name, area_name in zip(names, area_names)
] + [
(1., {
'{}_group_wave_drag_coeff'.format(name): 1.,
area_name: 1.,
'ref_area': -1.,
})
for name, area_name in zip(names, area_names)
],
)
self.add_subsystem('drag_coeff_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='lift_to_drag_ratio',
powers_dict=dict(
lift_coeff=1.,
drag_coeff=-1.,
),
)
self.add_subsystem('lift_to_drag_ratio_comp', comp, promotes=['*'])
for src, tgt in lift_coeff_connects:
self.connect(src, tgt)
for src, tgt in area_connects:
self.connect(src, tgt)
for name in names:
self.connect(
'{}_group.induced_drag_coeff'.format(name),
'{}_group_induced_drag_coeff'.format(name),
)
self.connect(
'{}_group.parasite_drag_coeff'.format(name),
'{}_group_parasite_drag_coeff'.format(name),
)
self.connect(
'{}_group.wave_drag_coeff'.format(name),
'{}_group_wave_drag_coeff'.format(name),
)
def setup(self):
shape = self.options['shape']
# module = self.options['options_dictionary']
#
comp = LinearCombinationComp(shape=shape,
out_name='vertical_hover_equilibrium',
constant=0.,
coeffs_dict=dict(
hover_total_thrust=1.,
GrossWeight=-1.,
))
self.add_subsystem('vertical_hover_equilibrium_comp',
comp,
promotes=['*'])
comp = LinearCombinationComp(shape=shape,
out_name='vertical_cruise_equilibrium',
constant=0.,
coeffs_dict=dict(
total_lift=1.,
GrossWeight=-1.,
))
self.add_subsystem('vertical_cruise_equilibrium_comp',
comp,
promotes=['*'])
comp = LinearCombinationComp(shape=shape,
out_name='horizontal_cruise_equilibrium',
constant=0.,
coeffs_dict=dict(
cruise_total_thrust=1.,
total_drag=-1.,
))
self.add_subsystem('horizontal_cruise_equilibrium_comp',
comp,
promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='cruise_rolling_moment_equilibrium',
terms_list=[
(0.2, dict(
cruise_wing_right_inner_thrust=1.,
wing_span=1.,
)),
(0.5, dict(
cruise_wing_right_outer_thrust=1.,
wing_span=1.,
)),
(0.5, dict(
cruise_tail_right_thrust=1.,
tail_span=1.,
)),
(-0.2, dict(
cruise_wing_left_inner_thrust=1.,
wing_span=1.,
)),
(-0.5, dict(
cruise_wing_left_outer_thrust=1.,
wing_span=1.,
)),
(-0.5, dict(
cruise_tail_left_thrust=1.,
tail_span=1.,
)),
],
constant=0.,
)
self.add_subsystem('cruise_rolling_moment_equilibrium_comp',
comp,
promotes=['*'])
comp = LinearCombinationComp(shape=shape,
out_name='wing_lift_moment_arm',
constant=0.,
coeffs_dict=dict(
xcg=1.,
nose_wing_c4=-1.,
))
self.add_subsystem('wing_lift_moment_arm_comp', comp, promotes=['*'])
comp = LinearCombinationComp(shape=shape,
out_name='tail_lift_moment_arm',
constant=0.,
coeffs_dict=dict(
nose_tail_c4=1.,
xcg=-1.,
))
self.add_subsystem('tail_lift_moment_arm_comp', comp, promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='pitching_moment_equilibrium',
terms_list=[
(1, dict(
wing_lift_moment_arm=1.,
wing_lift=1.,
)),
(-1, dict(
tail_lift_moment_arm=1.,
tail_lift=1.,
)),
],
constant=0.,
)
self.add_subsystem('pitching_moment_equilibrium_comp',
comp,
promotes=['*'])
def setup(self):
shape = self.options['shape']
comp = PressureComp()
self.add_subsystem('pressure_comp', comp, promotes=['*'])
comp = TemperatureComp()
self.add_subsystem('temperature_comp', comp, promotes=['*'])
comp = DensityComp()
self.add_subsystem('density_comp', comp, promotes=['*'])
R = 287.058
gamma = 1.4
comp = PowerCombinationComp( #
shape=shape,
coeff=1 / np.sqrt(gamma * R),
out_name='M_inf',
powers_dict=dict(
velocity_ms=1.,
temperature=-0.5,
))
self.add_subsystem('mach_comp', comp, promotes=['*'])
## Need CDv CD0 CL0 CLa
comp = LinearPowerCombinationComp(
shape=shape,
out_name='CL',
terms_list=[
(1., dict(
alpha=1.,
CLa=1.,
)),
(1., dict(CL0=1., )),
],
)
self.add_subsystem('CL_comp', comp, promotes=['*'])
comp = WaveDragCoeffComp()
self.add_subsystem('CDw_comp', comp, promotes=['*'])
e = 0.7
comp = PowerCombinationComp(shape=shape,
coeff=1 / (np.pi * e),
out_name='CDi',
powers_dict=dict(
CL=2.,
aspect_ratio=-1,
))
self.add_subsystem('CDi_comp', comp, promotes=['*'])
comp = LinearCombinationComp(
shape=shape,
in_names=['CDi', 'CDv', 'CDw', 'CD0'],
out_name='CD',
coeffs=[1., 1., 1., 1.],
)
self.add_subsystem('CD_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
coeff=1 / 2,
out_name='drag',
powers_dict=dict(
velocity_ms=2.,
density=1,
CD=1.,
))
self.add_subsystem('drag_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='LD', #lift over drag
powers_dict=dict(
CL=1.,
CD=-1.,
))
self.add_subsystem('lift_over_drag_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='Lift',
powers_dict=dict(drag=1., LD=1))
self.add_subsystem('lift_comp', comp, promotes=['*'])
comp = ExecComp('LD = CL/CD')
prob.model.add_subsystem('ld_comp', comp, promotes=['*'])
comp = ExecComp(
'tot_weight = (fuelburn + emptyTotal*4.45/9.81 + 42760) * 9.81')
prob.model.add_subsystem('total_weight_calculation', comp, promotes=['*'])
# comp = ExecComp('1 - L / tot_weight')
# prob.model.add_subsystem('total_weight_comp', comp, promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='LOW',
terms_list=[
(-1, dict(
L=1,
tot_weight=-1,
)),
],
constant=1,
)
prob.model.add_subsystem('LOW', comp, promotes=['*'])
comp = LinearCombinationComp(
shape=shape,
out_name='TOD',
coeffs_dict=dict(
thrust=1e3,
D=-1,
),
)
def setup(self):
shape = self.options['shape']
aircraft = self.options['aircraft']
comp = IndepVarComp()
comp.add_output('CL_max', val=aircraft['CL_max'], shape=shape)
comp.add_output('CL_takeoff', val=aircraft['CL_takeoff'], shape=shape)
comp.add_output('climb_gradient',
val=aircraft['climb_gradient'],
shape=shape)
comp.add_output('turn_load_factor',
val=aircraft['turn_load_factor'],
shape=shape)
comp.add_output('TOP', val=aircraft['TOP'], shape=shape)
comp.add_output('takeoff_density',
val=aircraft['takeoff_density'],
shape=shape)
comp.add_output('sealevel_density', val=1.225, shape=shape)
comp.add_output('stall_speed',
val=aircraft['stall_speed'],
shape=shape)
comp.add_output('climb_speed',
val=aircraft['climb_speed'],
shape=shape)
comp.add_output('turn_speed', val=aircraft['turn_speed'], shape=shape)
comp.add_output('landing_distance',
val=aircraft['landing_distance'],
shape=shape)
comp.add_output('approach_distance',
val=aircraft['approach_distance'],
shape=shape)
comp.add_output('wing_loading',
val=aircraft['wing_loading'],
shape=shape)
comp.add_output('thrust_to_weight',
val=aircraft['thrust_to_weight'],
shape=shape)
comp.add_output('ref_wing_loading',
val=aircraft['ref_wing_loading'],
shape=shape)
comp.add_output('ref_thrust_to_weight',
val=aircraft['ref_thrust_to_weight'],
shape=shape)
comp.add_design_var('wing_loading', indices=[0], lower=0.)
comp.add_design_var('thrust_to_weight', indices=[0], lower=0.)
self.add_subsystem('inputs_comp', comp, promotes=['*'])
#
comp = PowerCombinationComp(
shape=shape,
out_name='wing_loading_lbf_ft2',
powers_dict=dict(wing_loading=1., ),
coeff=units('lbf/ft^2', 'N/m^2'),
)
self.add_subsystem('wing_loading_lbf_ft2_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='ref_power_to_weight',
powers_dict=dict(
ref_thrust_to_weight=1.,
cruise_speed=1.,
propulsive_efficiency=-1.,
),
)
self.add_subsystem('ref_power_to_weight_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='power_to_weight',
powers_dict=dict(
thrust_to_weight=1.,
cruise_speed=1.,
propulsive_efficiency=-1.,
),
)
self.add_subsystem('power_to_weight_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='wing_area',
powers_dict=dict(
gross_weight=1.,
wing_loading=-1.,
),
)
self.add_subsystem('wing_area_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='max_thrust',
powers_dict=dict(
gross_weight=1.,
thrust_to_weight=1.,
),
)
self.add_subsystem('max_thrust_comp', comp, promotes=['*'])
#
comp = StallWingLoadingComp(shape=shape)
self.add_subsystem('stall_wing_loading_comp', comp, promotes=['*'])
comp = ClimbThrustToWeightComp(shape=shape)
self.add_subsystem('climb_thrust_to_weight_comp', comp, promotes=['*'])
comp = TurnThrustToWeightComp(shape=shape)
self.add_subsystem('turn_thrust_to_weight_comp', comp, promotes=['*'])
if aircraft['thrust_source_type'] == 'jet':
TakeoffWingLoadingComp = JetTakeoffWingLoadingComp
elif aircraft['thrust_source_type'] == 'propeller':
TakeoffWingLoadingComp = PropellerTakeoffWingLoadingComp
else:
raise Exception()
comp = TakeoffWingLoadingComp(shape=shape)
self.add_subsystem('takeoff_wing_loading_comp', comp, promotes=['*'])
comp = LandingWingLoadingComp(shape=shape)
self.add_subsystem('landing_wing_loading_comp', comp, promotes=['*'])
#
for con_name in [
'stall',
'takeoff',
'landing',
]:
comp = LinearCombinationComp(
shape=shape,
out_name='{}_wing_loading_constraint'.format(con_name),
coeffs_dict={
'wing_loading': 1.,
'{}_wing_loading'.format(con_name): -1.,
},
)
comp.add_constraint('{}_wing_loading_constraint'.format(con_name),
indices=[0],
upper=0.)
self.add_subsystem(
'{}_wing_loading_constraint_comp'.format(con_name),
comp,
promotes=['*'])
for con_name in [
'climb',
'turn',
]:
comp = LinearCombinationComp(
shape=shape,
out_name='{}_thrust_to_weight_constraint'.format(con_name),
coeffs_dict={
'thrust_to_weight': -1.,
'{}_thrust_to_weight'.format(con_name): 1.,
},
)
comp.add_constraint(
'{}_thrust_to_weight_constraint'.format(con_name),
indices=[0],
upper=0.)
self.add_subsystem(
'{}_thrust_to_weight_constraint_comp'.format(con_name),
comp,
promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='{}_power_to_weight'.format(con_name),
powers_dict={
'{}_thrust_to_weight'.format(con_name): 1.,
'cruise_speed': 1.,
'propulsive_efficiency': -1.,
},
)
self.add_subsystem('{}_power_to_weight_comp'.format(con_name),
comp,
promotes=['*'])
a = 0.5
comp = LinearPowerCombinationComp(
shape=shape,
out_name='sizing_performance_objective',
terms_list=[
(1 - a, dict(
thrust_to_weight=1.,
ref_thrust_to_weight=-1.,
)),
(-a, dict(
wing_loading=1.,
ref_wing_loading=-1.,
)),
],
)
self.add_subsystem(
'sizing_performance_objective_comp'.format(con_name),
comp,
promotes=['*'])
def setup(self):
shape = self.options['shape']
comp = PowerCombinationComp(shape=shape,
out_name='total_avail_energy',
coeff=3600.,
powers_dict=dict(
battery_mass=1.,
batter_energy_density=1.,
))
self.add_subsystem('total_avail_energy_comp', comp, promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='cruise_average_prop_efficiency',
terms_list=[
(1 / 6, dict(cruise_tail_right_eff=1., )),
(1 / 6, dict(cruise_tail_left_eff=1., )),
(1 / 6, dict(cruise_wing_right_outer_eff=1., )),
(1 / 6, dict(cruise_wing_right_inner_eff=1., )),
(1 / 6, dict(cruise_wing_left_outer_eff=1., )),
(1 / 6, dict(cruise_wing_left_inner_eff=1., )),
],
constant=0.,
)
self.add_subsystem('cruise_average_prop_efficiency_comp',
comp,
promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='hover_average_prop_efficiency',
terms_list=[
(1 / 6, dict(hover_tail_right_eff=1., )),
(1 / 6, dict(hover_tail_left_eff=1., )),
(1 / 6, dict(hover_wing_right_outer_eff=1., )),
(1 / 6, dict(hover_wing_right_inner_eff=1., )),
(1 / 6, dict(hover_wing_left_outer_eff=1., )),
(1 / 6, dict(hover_wing_left_inner_eff=1., )),
],
constant=0.,
)
self.add_subsystem('hover_average_prop_efficiency_comp',
comp,
promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='cruise_total_power',
terms_list=[
(1, dict(cruise_tail_right_power=1., )),
(1, dict(cruise_tail_left_power=1., )),
(1, dict(cruise_wing_right_outer_power=1., )),
(1, dict(cruise_wing_right_inner_power=1., )),
(1, dict(cruise_wing_left_outer_power=1., )),
(1, dict(cruise_wing_left_inner_power=1., )),
],
constant=0.,
)
self.add_subsystem('cruise_total_power_comp', comp, promotes=['*'])
comp = LinearPowerCombinationComp(
shape=shape,
out_name='hover_total_power',
terms_list=[
(1, dict(hover_tail_right_power=1., )),
(1, dict(hover_tail_left_power=1., )),
(1, dict(hover_wing_right_outer_power=1., )),
(1, dict(hover_wing_right_inner_power=1., )),
(1, dict(hover_wing_left_outer_power=1., )),
(1, dict(hover_wing_left_inner_power=1., )),
],
constant=0.,
)
self.add_subsystem('hover_total_power_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='cruise_time',
coeff=1.,
powers_dict=dict(
trip_length=1.,
v_inf=-1.,
))
self.add_subsystem('cruise_time', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='cruise_energy_expenditure',
coeff=1.,
powers_dict=dict(
cruise_time=1.,
cruise_total_power=1.,
))
self.add_subsystem('cruise_energy_expenditure_comp',
comp,
promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='hover_energy_expenditure',
powers_dict=dict(
hover_time=1.,
hover_total_power=1.,
))
self.add_subsystem('hover_energy_expenditure_comp',
comp,
promotes=['*'])
comp = LinearCombinationComp(shape=shape,
out_name='energy_expenditure_per_trip',
constant=0.,
coeffs_dict=dict(
hover_energy_expenditure=1.,
cruise_energy_expenditure=1.,
))
self.add_subsystem('energy_expenditure_per_trip_comp',
comp,
promotes=['*'])
comp = LinearCombinationComp(shape=shape,
out_name='energy_remaining',
constant=0.,
coeffs_dict=dict(
total_avail_energy=1.,
cruise_energy_expenditure=-1.,
hover_energy_expenditure=-1.,
))
self.add_subsystem('energy_remaining_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='tips_per_charge',
powers_dict=dict(
total_avail_energy=1.,
energy_expenditure_per_trip=-1.,
))
self.add_subsystem('trips_per_charge', comp, promotes=['*'])