def setup(self):
shape = self.options['shape']
#
comp = GeometryComp()
self.add_subsystem('geometry_comp', comp, promotes = ['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'wing_chord',
coeff = 1.,
powers_dict=dict(
wing_area = 1.,
wing_span = -1.,
)
)
self.add_subsystem('wing_chord_comp',comp, promotes = ['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'tail_chord',
coeff = 1.,
powers_dict=dict(
tail_area = 1.,
tail_span = -1.,
)
)
self.add_subsystem('tail_chord_comp', comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
# mode = self.options['mode']
# comp = IndepVarComp()
# comp.add_input('area', val = 0.05)
# comp.add_output('AR', val = 10)
# self.add_subsystem('inputs_comp', comp, promotes=['*'])
# b = sqrt(AR * S)
comp = PowerCombinationComp(shape=shape,
out_name='wing_span',
powers_dict=dict(
AR=0.5,
area=0.5,
))
self.add_subsystem('wing_span_comp', comp, promotes=['*'])
# c = b / AR
oas_shape = (9, )
comp = PowerCombinationComp(shape=shape,
out_name='wing_chord',
powers_dict=dict(
AR=-1.,
wing_span=1.,
))
self.add_subsystem('wing_chord_comp', comp, promotes=['*'])
comp = ScalarExpansionComp(
shape=oas_shape,
out_name='oas_wing_chord',
in_name='wing_chord',
)
self.add_subsystem('oas_wing_chord_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('ref_3km_density', val=0.909122, shape=shape)
comp.add_output('sealevel_density', val=1.225, shape=shape)
self.add_subsystem('inputs_comp', comp, promotes=['*'])
# comp = PowerCombinationComp(
# shape=shape,
# out_name='available_thrust',
# coeff=0.369,
# powers_dict=dict(
# sealevel_thrust=1.,
# mach_number=-0.305,
# density=1.,
# ref_3km_density=-1.,
# ),
# )
# self.add_subsystem('available_thrust_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='available_thrust',
powers_dict=dict(
mach_number=0.,
sealevel_thrust=1.,
density=1.,
sealevel_density=-1.,
),
)
self.add_subsystem('available_thrust_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='thrust',
powers_dict=dict(
throttle=1.,
available_thrust=1.,
),
)
self.add_subsystem('thrust_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='mass_flow_rate',
coeff=module['thrust_specific_fuel_consumption'],
powers_dict=dict(
thrust=1.,
),
)
self.add_subsystem('mass_flow_rate_comp', comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
#computations below:
R = 287.058
gamma = 1.4
comp = PowerCombinationComp( #
shape=shape,
coeff=1 / np.sqrt(gamma * R),
out_name='M_inf',
powers_dict=dict(
speed=1.,
temperature=-0.5,
))
self.add_subsystem('mach_comp', comp, promotes=['*'])
#### Thrust Compcomp = Zerospeed_Thrust()
sealv_dens = 1.225
comp = PowerCombinationComp(shape=shape,
coeff=1 / sealv_dens,
out_name='zerospeed_thrust',
powers_dict=dict(
T_max=1.,
density=1.,
))
self.add_subsystem('zerospeed_thrust_comp', comp, promotes=['*'])
# comp=Specific_Fuel_Consum()
# self.add_subsystem('specific_fuel_consum_comp', comp, promotes=['*'])
comp = Thrust_Ratio()
self.add_subsystem('thrust_ratio_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='avaliable_thrust',
powers_dict=dict(
thrust_ratio=1.,
zerospeed_thrust=1.,
),
)
self.add_subsystem('avaliable_thrust', comp, promotes=['*'])
comp = Thottled_Thrust()
self.add_subsystem('thottled_thrust_comp', comp, promotes=['*'])
mass_flow_rate_coeffecient = 0.61
comp = PowerCombinationComp(
shape=shape,
out_name='mass_flow_rate',
coeff=mass_flow_rate_coeffecient,
powers_dict=dict(thottled_thrust=1., ),
)
self.add_subsystem('mass_flow_comp', comp, promotes=['*'])
def setup(self):
num_times = self.options['num_times']
vec_name = self.options['vec_name']
norm_name = self.options['norm_name']
unit_vec_name = self.options['unit_vec_name']
comp = PowerCombinationComp(
shape=(3, num_times),
out_name='tmp_{}_2'.format(vec_name),
powers_dict={vec_name: 2.},
)
self.add_subsystem('tmp_{}_2_comp'.format(vec_name),
comp,
promotes=['*'])
comp = ArrayContractionComp(
shape=(3, num_times),
contract_indices=[0],
out_name='tmp_{}_2'.format(norm_name),
in_name='tmp_{}_2'.format(vec_name),
)
self.add_subsystem('tmp_{}_2_comp'.format(norm_name),
comp,
promotes=['*'])
comp = PowerCombinationComp(
shape=(num_times, ),
out_name=norm_name,
powers_dict={'tmp_{}_2'.format(norm_name): 0.5},
)
self.add_subsystem('{}_comp'.format(norm_name), comp, promotes=['*'])
comp = ArrayExpansionComp(
shape=(3, num_times),
expand_indices=[0],
out_name='tmp_{}_expanded'.format(norm_name),
in_name=norm_name,
)
self.add_subsystem('tmp_{}_expanded_comp'.format(norm_name),
comp,
promotes=['*'])
comp = PowerCombinationComp(shape=(3, num_times),
out_name=unit_vec_name,
powers_dict={
vec_name: 1.,
'tmp_{}_expanded'.format(norm_name):
-1.,
})
self.add_subsystem('{}_comp'.format(unit_vec_name),
comp,
promotes=['*'])
def setup(self):
shape = self.options['shape']
size = int(np.prod(shape))
group = Group()
comp = PowerCombinationComp(
shape=shape,
out_name='altitude_km',
coeff=1.e-3,
powers_dict=dict(altitude=1., ),
)
self.add_subsystem('altitude_km_comp', comp, promotes=['*'])
comp = TemperatureComp(shape=shape)
self.add_subsystem('temperature_comp', comp, promotes=['*'])
comp = PressureComp(shape=shape)
self.add_subsystem('pressure_comp', comp, promotes=['*'])
comp = DensityComp(shape=shape)
self.add_subsystem('density_comp', comp, promotes=['*'])
comp = SonicSpeedComp(shape=shape)
self.add_subsystem('sonic_speed_comp', comp, promotes=['*'])
comp = ViscosityComp(shape=shape)
self.add_subsystem('viscosity_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='mach_number',
powers_dict=dict(
speed=1.,
sonic_speed=-1.,
),
)
self.add_subsystem('mach_number_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='dynamic_pressure',
coeff=0.5,
powers_dict=dict(
density=1.,
speed=2.,
),
)
self.add_subsystem('dynamic_pressure_comp', comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
comp = IndepVarComp()
comp.add_output('C_L')
comp.add_output('L_t', val=0.2)
comp.add_output('area')
self.add_subsystem('inputs_comp', comp, promotes=['*'])
# L = CL^1 0.5 rho^1 V^2 S^1
comp = PowerCombinationComp(shape=shape,
out_name='L_w',
coeff=0.5,
powers_dict=dict(
C_L=1.,
density=1.,
speed=2.,
area=1.,
))
self.add_subsystem('wing_lift_comp', comp, promotes=['*'])
# L = 1. x L_w + 1. x L_t
comp = LinearCombinationComp(shape=shape,
out_name='L',
constant=0.,
coeffs_dict=dict(
L_w=1.,
L_t=1.,
))
self.add_subsystem('total_lift_comp', comp, promotes=['*'])
def setup(self):
num_times = self.options['num_times']
in1_name = self.options['in1_name']
in2_name = self.options['in2_name']
out_name = self.options['out_name']
shape = (3, num_times)
comp = PowerCombinationComp(
shape=shape,
out_name='tmp_{}_multiplied'.format(out_name),
powers_dict={
in1_name: 1.,
in2_name: 2.,
},
)
self.add_subsystem('tmp_{}_multiplied_comp'.format(out_name), comp, promotes=['*'])
comp = ArrayContractionComp(
shape=shape,
contract_indices=[0],
out_name='tmp_{}_summed'.format(out_name),
in_name='tmp_{}_multiplied'.format(out_name),
)
self.add_subsystem('{}_summed_comp'.format(out_name), comp, promotes=['*'])
comp = ArrayExpansionComp(
shape=shape,
expand_indices=[0],
in_name='tmp_{}_summed'.format(out_name),
out_name=out_name,
)
self.add_subsystem('{}_comp'.format(out_name), comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
comp = ExecComp('thrust_torque_hover = thrust * wing_span',
shape=shape)
self.add_subsystem('thrust_torque_hover_comp', comp, promotes=['*'])
comp = ExecComp('drag_torque_hover = drag * radius * 1.5', shape=shape)
self.add_subsystem('drag_torque_hover_comp', comp, promotes=['*'])
comp = LinearCombinationComp(
shape=shape,
in_names=['thrust_torque_hover', 'drag_torque_hover'],
out_name='vertical_torque',
coeffs=[1., -1.])
self.add_subsystem('vertical_torque_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='vertical_shaft_power',
coeff=1.,
powers_dict=dict(
vertical_torque=1.,
hover_wing_angular_speed=1.,
))
self.add_subsystem('vertical_shaft_power_comp', comp, promotes=['*'])
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']
# find = self.options['find']
comp = PowerCombinationComp(
shape=shape,
out_name='altitude_km',
coeff=1.e-3,
powers_dict=dict(altitude=1., ),
)
self.add_subsystem('altitude_km_comp', comp, promotes=['*'])
comp = TemperatureComp(shape=shape)
self.add_subsystem('temperature_comp', comp, promotes=['*'])
comp = PressureComp(shape=shape)
self.add_subsystem('pressure_comp', comp, promotes=['*'])
comp = DensityComp(shape=shape)
self.add_subsystem('density_comp', comp, promotes=['*'])
comp = SonicSpeedComp(shape=shape)
self.add_subsystem('sonic_speed_comp', comp, promotes=['*'])
# comp = ViscosityComp(shape=shape)
# self.add_subsystem('viscosity_comp', comp, promotes=['*'])
# if find == 'angle':
# comp = PowerCombinationComp(
# shape=shape,
# out_name='speed',
# powers_dict=dict(
# mach_number=1.,
# sonic_speed=1.,
# ),
# )
# self.add_subsystem('speed_comp', comp, promotes=['*'])
# comp = PowerCombinationComp(
# shape=shape,
# out_name='dynamic_pressure',
# coeff=0.5,
# powers_dict=dict(
# density=1.,
# speed=2.,
# ),
# )
# self.add_subsystem('dynamic_pressure_comp', comp, promotes=['*'])
# else:
# pass
# need to edit mach number comp in atmosphere to find speed given sonic speed and mach number (input)
# then connect this output speed to the dynamic_pressure_comp speed input
def setup(self):
shape = self.options['shape']
comp = PowerCombinationComp(
shape=shape,
out_name='aspect_ratio',
powers_dict=dict(
wing_span=1.,
mean_chord=-1.,
),
)
self.add_subsystem('aspect_ratio', 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']
# comp = IndepVarComp()
# comp.add_output('hover_wing_angular_speed')
# # if design variable, add as output in IVC
# self.add_subsystem('inputs_comp', comp, promotes = ['*'])
# make connections in run_group (aero_geom_group to this one for wing_span)
# r = b/2/(cos(sweep))
comp = ExecComp('radius = wing_span/2/(cos(sweep*pi/180))',
shape=shape)
self.add_subsystem('radius_comp', comp, promotes=['*'])
# ExecComp defines the equation and calculates given the equation/inputs
# Need to connect sweep/wingspan to this Group and then can compute the
# hover velocity below
# V = 2pi*RPM/60*.75*radius or V = 2pi*RPM/60*.75* b/2/(cos(sweep))
# V = omega * r
comp = PowerCombinationComp(shape=shape,
coeff=.75,
out_name='hover_drag_velocity',
powers_dict=dict(
hover_wing_angular_speed=1.,
radius=1.,
))
self.add_subsystem('hover_drag_velocity_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
coeff=.5,
out_name='hover_torque_velocity',
powers_dict=dict(
hover_wing_angular_speed=1.,
wing_span=1.,
))
self.add_subsystem('hover_torque_velocity_comp', comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
## Need CDv CD0 CL0 CLa
#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=['*'])
comp = PowerCombinationComp(
shape=shape,
coeff=1/2,
out_name='drag',
powers_dict=dict(
speed=2.,
density=1,
drag_coeff = 1.,
)
)
self.add_subsystem('drag_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='Lift',
powers_dict=dict(
drag = 1.,
lift_to_drag_ratio = 1
)
)
self.add_subsystem('lift_comp', comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
# comp = IndepVarComp()
# comp.add_output('C_D')
# comp.add_output('C_L')
# comp.add_output('speed')
# comp.add_output('density')
# comp.add_output('area')
# self.add_subsystem('inputs_comp', comp, promotes=['*'])
# # D = 0.5 * rho * v^2 * C_D * S
# comp = PowerCombinationComp(
# shape=shape,
# out_name='cruise_drag',
# coeff=0.5,
# powers_dict=dict(
# area=1.,
# C_D=1,
# speed=2.,
# density=1.
# )
# )
# self.add_subsystem('cruise_drag_comp', comp, promotes=['*'])
# # L = 0.5 * rho * v^2 * C_L * S
# comp = PowerCombinationComp(
# shape=shape,
# out_name='cruise_lift',
# coeff=0.5,
# powers_dict=dict(
# area=1.,
# C_L=1,
# speed=2.,
# density=1.
# )
# )
# self.add_subsystem('cruise_lift_comp', comp, promotes=['*'])
# L_D = C_L/C_D
comp = PowerCombinationComp(shape=shape,
out_name='L_D',
powers_dict=dict(C_L=1, C_D=-1.))
self.add_subsystem('L_D_comp', comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
comp = IndepVarComp()
comp.add_output('motor_efficiency')
comp.add_output('voltage')
self.add_subsystem('inputs_comp', comp, promotes = ['*'])
comp = PowerCombinationComp(
shape = shape,
out_name = 'propeller_shaft_power',
coeff = 1.,
powers_dict = dict(
motor_efficiency = 1.,
voltage = 1.,
current = 1.,
)
)
self.add_subsystem('propeller_shaft_power_comp', comp)
def setup(self):
shape = self.options['shape']
g = self.options['g']
EMD = self.options['EMD']
W0 = self.options['W0']
Wb = self.options['Wb']
# comp = IndepVarComp()
# comp.add_output('efficiency') # Propellor Efficiency
# comp.add_output('LD') # Lift to Drag Ratio
# self.add_subsystem('inputs_comp', comp, promotes=['*'])
# # self.add_subsystem('inputs_comp', comp)
comp = PowerCombinationComp(shape=shape,
out_name='range',
coeff=EMD / g * Wb / W0,
powers_dict=dict(
efficiency=1.,
L_D=1.,
))
self.add_subsystem('range_comp', comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
module = self.options['options_dictionary']
comp = IndepVarComp()
comp.add_output('mass', shape=shape)
comp.add_output('normalized_torque', shape=shape)
comp.add_output('angular_speed', shape=shape)
for var_name in [
'magnetic_flux_density',
'line_current_density',
'number_of_poles_per_phase',
'hysteresis_coeff',
'copper_resistivity',
'eta_slot',
'eta_fill',
]:
comp.add_output(var_name, val=module[var_name], shape=shape)
self.add_subsystem('inputs_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='supply_frequency',
coeff=(60 / (2 * np.pi)) * (1 / 120),
powers_dict=dict(
number_of_poles_per_phase=1.,
angular_speed=1.,
),
)
self.add_subsystem('supply_frequency_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='continuous_torque',
coeff=module['torque_mass_coeff'],
powers_dict=dict(mass=module['torque_mass_power'], ),
)
self.add_subsystem('continuous_torque_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='continuous_power',
coeff=module['specific_power'],
powers_dict=dict(mass=1., ),
)
self.add_subsystem('continuous_power_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='flux_weakening_torque',
powers_dict=dict(
continuous_power=1.,
angular_speed=-1.,
),
)
self.add_subsystem('flux_weakening_torque_comp', comp, promotes=['*'])
comp = ElementwiseMinComp(
shape=shape,
out_name='available_torque',
in_names=['continuous_torque', 'flux_weakening_torque'],
rho=1.e-1,
)
self.add_subsystem('available_torque_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='torque',
powers_dict=dict(
normalized_torque=1.,
available_torque=1.,
),
)
self.add_subsystem('torque_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='shaft_power',
powers_dict=dict(
torque=1.,
angular_speed=1.,
),
)
self.add_subsystem('shaft_power_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='mass_stator',
coeff=0.53,
powers_dict=dict(mass=1.),
)
self.add_subsystem('mass_stator_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='mass_rotor',
coeff=0.47,
powers_dict=dict(mass=1.),
)
self.add_subsystem('mass_rotor_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='outer_diameter',
coeff=96.9,
powers_dict=dict(mass=0.344, ),
)
self.add_subsystem('outer_diameter_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='motor_length',
coeff=0.35,
powers_dict=dict(outer_diameter=1., ),
)
self.add_subsystem('motor_length_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='stator_diameter',
coeff=0.5,
powers_dict=dict(outer_diameter=1., ),
)
self.add_subsystem('stator_diameter_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='shaft_diameter',
coeff=0.085,
powers_dict=dict(outer_diameter=1., ),
)
self.add_subsystem('shaft_diameter_comp', comp, promotes=['*'])
comp = LinearCombinationComp(
shape=shape,
out_name='stator_thickness',
coeffs_dict=dict(stator_diameter=.5, shaft_diameter=-.5),
)
self.add_subsystem('stator_thickness_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='eddy_loss',
coeff=1.1 * (1 / 50)**1.5,
powers_dict=dict(
supply_frequency=1.5,
mass_stator=1.,
magnetic_flux_density=2.,
),
)
self.add_subsystem('eddy_loss_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='hysteresis_loss',
powers_dict=dict(supply_frequency=1.,
mass_rotor=1.,
magnetic_flux_density=2.,
hysteresis_coeff=1.),
)
self.add_subsystem('hysteresis_loss_comp', comp, promotes=['*'])
comp = LinearCombinationComp(
shape=shape,
out_name='iron_loss',
coeffs_dict=dict(hysteresis_loss=1., eddy_loss=1.),
)
self.add_subsystem('iron_loss_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='heat_loss_nominal',
coeff=0.5,
powers_dict=dict(shaft_diameter=1.,
motor_length=1.,
copper_resistivity=1.,
line_current_density=2.,
eta_slot=-1.,
eta_fill=-1.,
stator_thickness=-1.),
)
self.add_subsystem('heat_loss_nominal_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='heat_loss',
powers_dict=dict(heat_loss_nominal=1., normalized_torque=2.),
)
self.add_subsystem('heat_loss_comp', comp, promotes=['*'])
comp = LinearCombinationComp(
shape=shape,
out_name='input_power',
coeffs_dict=dict(shaft_power=1., iron_loss=1., heat_loss=1.),
)
self.add_subsystem('input_power_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='motor_efficiency',
coeff=100,
powers_dict=dict(
shaft_power=1.,
input_power=-1.,
),
)
self.add_subsystem('motor_efficiency_comp', comp, promotes=['*'])
def setup(self):
num_times = self.options['num_times']
num_cp = self.options['num_cp']
step_size = self.options['step_size']
cubesat = self.options['cubesat']
mtx = self.options['mtx']
shape = (3, num_times)
thrust_unit_vec = np.outer(
np.array([1., 0., 0.]),
np.ones(num_times),
)
comp = IndepVarComp()
comp.add_output('thrust_unit_vec_b_3xn', val=thrust_unit_vec)
comp.add_output('thrust_scalar_mN_cp', val=1.e-3 * np.ones(num_cp))
comp.add_output('initial_propellant_mass', 0.17)
comp.add_design_var('thrust_scalar_mN_cp', lower=0., upper=20000)
self.add_subsystem('inputs_comp', comp, promotes=['*'])
comp = MtxVecComp(
num_times=num_times,
mtx_name='rot_mtx_i_b_3x3xn',
vec_name='thrust_unit_vec_b_3xn',
out_name='thrust_unit_vec_3xn',
)
self.add_subsystem('thrust_unit_vec_3xn_comp', comp, promotes=['*'])
comp = LinearCombinationComp(
shape=(num_cp, ),
out_name='thrust_scalar_cp',
coeffs_dict=dict(thrust_scalar_mN_cp=1.e-3),
)
self.add_subsystem('thrust_scalar_cp_comp', comp, promotes=['*'])
comp = BsplineComp(
num_pt=num_times,
num_cp=num_cp,
jac=mtx,
in_name='thrust_scalar_cp',
out_name='thrust_scalar',
)
self.add_subsystem('thrust_scalar_comp', comp, promotes=['*'])
comp = ArrayExpansionComp(
shape=shape,
expand_indices=[0],
in_name='thrust_scalar',
out_name='thrust_scalar_3xn',
)
self.add_subsystem('thrust_scalar_3xn_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='thrust_3xn',
powers_dict=dict(
thrust_unit_vec_3xn=1.,
thrust_scalar_3xn=1.,
),
)
self.add_subsystem('thrust_3xn_comp', comp, promotes=['*'])
comp = LinearCombinationComp(
shape=(num_times, ),
out_name='mass_flow_rate',
coeffs_dict=dict(thrust_scalar=-1. /
(cubesat['acceleration_due_to_gravity'] *
cubesat['specific_impulse'])))
self.add_subsystem('mass_flow_rate_comp', comp, promotes=['*'])
comp = PropellantMassRK4Comp(
num_times=num_times,
step_size=step_size,
)
self.add_subsystem('propellant_mass_rk4_comp', comp, promotes=['*'])
comp = ExecComp(
'total_propellant_used=propellant_mass[0] - propellant_mass[-1]',
propellant_mass=np.empty(num_times),
)
self.add_subsystem('total_propellant_used_comp', comp, promotes=['*'])
def setup(self):
shape = self.options['shape']
module = self.options['options_dictionary']
blade_solidity = module['blade_solidity']
integrated_design_lift_coeff = module['integrated_design_lift_coeff']
comp = IndepVarComp()
comp.add_output('radius_scalar')
self.add_subsystem('inputs_comp', comp, promotes=['*'])
comp = ScalarExpansionComp(
shape=shape,
out_name='radius',
in_name='radius_scalar',
)
self.add_subsystem('radius_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='diameter',
coeff=2.,
powers_dict=dict(radius=1., ))
self.add_subsystem('diameter_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='rotational_speed',
coeff=1. / 2. / np.pi,
powers_dict=dict(angular_speed=1., ))
self.add_subsystem('rotational_speed_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='power_coeff',
powers_dict=dict(
shaft_power=1.,
density=-1.,
rotational_speed=-3.,
diameter=-5.,
))
self.add_subsystem('power_coeff_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='tip_speed',
powers_dict=dict(
radius=1.,
angular_speed=1.,
))
self.add_subsystem('tip_speed_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='tip_mach',
powers_dict=dict(
tip_speed=1.,
sonic_speed=-1.,
))
self.add_subsystem('tip_mach_comp', comp, promotes=['*'])
comp = FlowAngleComp(shape=shape)
self.add_subsystem('flow_angle_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='advance_ratio',
coeff=np.pi,
powers_dict=dict(
speed=1.,
tip_speed=-1.,
))
self.add_subsystem('advance_ratio_comp', comp, promotes=['*'])
comp = GlauertFactorComp(shape=shape)
self.add_subsystem('glauert_factor_comp', comp, promotes=['*'])
comp = BladeDragCoeffComp(
shape=shape,
integrated_design_lift_coeff=integrated_design_lift_coeff)
self.add_subsystem('blade_drag_coeff_comp', comp, promotes=['*'])
comp = Eta1Comp(shape=shape, blade_solidity=blade_solidity)
self.add_subsystem('eta1_comp', comp, promotes=['*'])
comp = Eta2Comp(shape=shape)
self.add_subsystem('eta2_comp', comp, promotes=['*'])
comp = Eta3Comp(shape=shape, blade_solidity=blade_solidity)
self.add_subsystem('eta3_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='efficiency',
powers_dict=dict(
eta1=1.,
eta2=1.,
eta3=1.,
))
self.add_subsystem('efficiency_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='thrust_coeff',
powers_dict=dict(
efficiency=1.,
power_coeff=1.,
advance_ratio=-1.,
))
self.add_subsystem('thrust_coeff_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='thrust',
powers_dict=dict(
thrust_coeff=1.,
density=1.,
rotational_speed=2.,
diameter=4.,
))
self.add_subsystem('thrust_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='blade_loading_coeff',
coeff=1. / blade_solidity,
powers_dict=dict(thrust_coeff=1., ))
self.add_subsystem('blade_loading_coeff_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='figure_of_merit',
coeff=1. / np.sqrt(2 * np.pi),
powers_dict=dict(
thrust=1.5,
density=-0.5,
radius=-1.,
shaft_power=-1.,
))
self.add_subsystem('figure_of_merit_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='area',
coeff=np.pi,
powers_dict=dict(radius=2., ))
self.add_subsystem('area_comp', comp, promotes=['*'])
comp = PowerCombinationComp(shape=shape,
out_name='disk_loading_lb_ft2',
coeff=units('lbf/ft^2', 'N/m^2'),
powers_dict=dict(
thrust=1.,
area=-1.,
))
self.add_subsystem('disk_loading_lb_ft2_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=['*'])
def setup(self):
shape = self.options['shape']
aircraft = self.options['aircraft']
part = self.options['part']
skin_friction_roughness = part['skin_friction_roughness']
laminar_pctg = part['laminar_pctg']
comp = PowerCombinationComp(
shape=shape,
out_name='Re',
powers_dict=dict(
density=1.,
speed=1.,
characteristic_length=1.,
dynamic_viscosity=-1.,
),
)
self.add_subsystem('Re_comp', comp, promotes=['*'])
if aircraft['regime'] == 'subsonic':
comp = PowerCombinationComp(
shape=shape,
out_name='Re_cutoff',
coeff=38.21 * skin_friction_roughness**-1.053,
powers_dict=dict(characteristic_length=1.053, ),
)
self.add_subsystem('Re_cutoff_comp', comp, promotes=['*'])
elif aircraft['regime'] in ['transonic', 'supersonic']:
comp = PowerCombinationComp(
shape=shape,
out_name='Re_cutoff',
coeff=44.62 * skin_friction_roughness**-1.053,
powers_dict=dict(
characteristic_length=1.053,
mach_number=1.16,
),
)
self.add_subsystem('Re_cutoff_comp', comp, promotes=['*'])
else:
raise Exception()
comp = ElementwiseMinComp(
shape=shape,
out_name='Re_turbulent_min',
in_names=['Re', 'Re_cutoff'],
rho=1e-3,
)
self.add_subsystem('Re_turbulent_min_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='skin_friction_coeff_laminar',
coeff=1.328,
powers_dict=dict(Re=-0.5, ),
)
self.add_subsystem('skin_friction_coeff_laminar_comp',
comp,
promotes=['*'])
def func(Re, M):
Cf = 0.455 / (np.log(Re) / np.log(10))**2.58 / (1 +
0.144 * M**2)**0.65
return Cf
def deriv(Re, M):
dCf_dRe = -2.58 * 0.455 / (
np.log(Re) / np.log(10))**3.58 * 1 / Re / np.log(10) / (
1 + 0.144 * M**2)**0.65
dCf_dM = 0.455 / (np.log(Re) / np.log(10))**2.58 * -0.65 / (
1 + 0.144 * M**2)**1.65 * 2 * 0.144 * M
return (dCf_dRe, dCf_dM)
comp = GeneralOperationComp(
shape=shape,
out_name='skin_friction_coeff_turbulent',
in_names=['Re_turbulent_min', 'mach_number'],
func=func,
deriv=deriv,
)
self.add_subsystem('skin_friction_coeff_turbulent_comp',
comp,
promotes=['*'])
comp = LinearCombinationComp(
shape=shape,
out_name='skin_friction_coeff',
coeffs_dict=dict(
skin_friction_coeff_laminar=laminar_pctg / 100.,
skin_friction_coeff_turbulent=1 - laminar_pctg / 100.,
),
)
self.add_subsystem('skin_friction_coeff_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=['*'])
def setup(self):
shape = self.options['shape']
comp = PowerCombinationComp(
shape=shape,
out_name='altitude_km',
coeff=1.e-3,
powers_dict=dict(altitude=1., ),
)
self.add_subsystem('altitude_km_comp', comp, promotes=['*'])
comp = TemperatureComp(shape=shape)
self.add_subsystem('temperature_comp', comp, promotes=['*'])
comp = PressureComp(shape=shape)
self.add_subsystem('pressure_comp', comp, promotes=['*'])
comp = DensityComp(shape=shape)
self.add_subsystem('density_comp', comp, promotes=['*'])
comp = SonicSpeedComp(shape=shape)
self.add_subsystem('sonic_speed_comp', comp, promotes=['*'])
comp = ViscosityComp(shape=shape)
self.add_subsystem('viscosity_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='re',
powers_dict=dict(
dynamic_viscosity=-1,
characteristic_length=1,
v=1,
),
)
self.add_subsystem('reynolds_number_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='Mach_number',
powers_dict=dict(
v=1.,
sonic_speed=-1.,
),
)
self.add_subsystem('Mach_number_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='rho',
powers_dict=dict(density=1., ),
)
self.add_subsystem('rho_comp', comp, promotes=['*'])
comp = PowerCombinationComp(
shape=shape,
out_name='dynamic_pressure',
coeff=0.5,
powers_dict=dict(
rho=1.,
v=2.,
),
)
self.add_subsystem('dynamic_pressure_comp', comp, promotes=['*'])
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 = ['*'])
comp.add_design_var('alpha', lower=0.)
model.add_subsystem('inputs_comp', comp, promotes=['*'])
comp = CLComp()
model.add_subsystem('cl_comp', comp, promotes=['*'])
e = 0.7
if 1:
comp = CDiComp(e=e)
model.add_subsystem('cdi_comp', comp, promotes=['*'])
else:
from lsdo_utils.api import PowerCombinationComp
comp = PowerCombinationComp(shape=(1, ),
out_name='CDi',
coeff=1. / np.pi / e,
powers_dict=dict(
CL=2.,
AR=-1.,
))
model.add_subsystem('cdi_comp', comp, promotes=['*'])
comp = ExecComp('CD = CD0 + CDi')
model.add_subsystem('cd_comp', comp, promotes=['*'])
comp = ExecComp('LD = CL/CD')
comp.add_objective('LD', scaler=-1.)
model.add_subsystem('ld_comp', comp, promotes=['*'])
prob.model = model
prob.driver = ScipyOptimizeDriver()
def setup(self):
num_times = self.options['num_times']
num_cp = self.options['num_cp']
cubesat = self.options['cubesat']
mtx = self.options['mtx']
comp = IndepVarComp()
# comp.add_output('roll_cp', val=2. * np.pi * np.random.rand(num_cp))
# comp.add_output('pitch_cp', val=2. * np.pi * np.random.rand(num_cp))
comp.add_output('roll_cp', val=np.ones(num_cp))
comp.add_output('pitch_cp', val=np.ones(num_cp))
comp.add_design_var('roll_cp')
comp.add_design_var('pitch_cp')
self.add_subsystem('inputs_comp', comp, promotes=['*'])
for var_name in ['roll', 'pitch']:
comp = BsplineComp(
num_pt=num_times,
num_cp=num_cp,
jac=mtx,
in_name='{}_cp'.format(var_name),
out_name=var_name,
)
self.add_subsystem('{}_comp'.format(var_name),
comp,
promotes=['*'])
comp = RotMtxBIComp(num_times=num_times)
self.add_subsystem('rot_mtx_b_i_3x3xn_comp', comp, promotes=['*'])
comp = ArrayReorderComp(
in_shape=(3, 3, num_times),
out_shape=(3, 3, num_times),
in_subscripts='ijn',
out_subscripts='jin',
in_name='rot_mtx_b_i_3x3xn',
out_name='rot_mtx_i_b_3x3xn',
)
self.add_subsystem('rot_mtx_i_b_3x3xn_comp', comp, promotes=['*'])
#
for var_name in [
'times',
'roll',
'pitch',
]:
comp = FiniteDifferenceComp(
num_times=num_times,
in_name=var_name,
out_name='d{}'.format(var_name),
)
self.add_subsystem('d{}_comp'.format(var_name),
comp,
promotes=['*'])
rad_deg = np.pi / 180.
for var_name in [
'roll',
'pitch',
]:
comp = PowerCombinationComp(shape=(num_times, ),
out_name='{}_rate'.format(var_name),
powers_dict={
'd{}'.format(var_name): 1.,
'dtimes': -1.,
})
comp.add_constraint('{}_rate'.format(var_name),
lower=-10. * rad_deg,
upper=10. * rad_deg,
linear=True)
self.add_subsystem('{}_rate_comp'.format(var_name),
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),
)
