def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Lift_Cruise_CRM'
vehicle.configuration = 'eVTOL'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 2450. * Units.lb
vehicle.mass_properties.operating_empty = 2250. * Units.lb # Approximate
vehicle.mass_properties.max_takeoff = 2450. * Units.lb # Approximate
vehicle.mass_properties.max_payload = 200. * Units.lb
vehicle.mass_properties.center_of_gravity = [[2.0144, 0.,
0.]] # Approximate
# basic parameters
vehicle.reference_area = 10.76
vehicle.envelope.ultimate_load = 5.7
vehicle.envelope.limit_load = 3.
# ------------------------------------------------------------------
# WINGS
# ------------------------------------------------------------------
# WING PROPERTIES
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.76
wing.sweeps.quarter_chord = 0.0 * Units.degrees
wing.thickness_to_chord = 0.18
wing.taper = 1.
wing.spans.projected = 35.0 * Units.feet
wing.chords.root = 3.25 * Units.feet
wing.total_length = 3.25 * Units.feet
wing.chords.tip = 3.25 * Units.feet
wing.chords.mean_aerodynamic = 3.25 * Units.feet
wing.dihedral = 1.0 * Units.degrees
wing.areas.reference = 113.75 * Units.feet**2
wing.areas.wetted = 227.5 * Units.feet**2
wing.areas.exposed = 227.5 * Units.feet**2
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[1.5, 0., 0.]]
wing.aerodynamic_center = [1.975, 0., 0.]
wing.winglet_fraction = 0.0
wing.symmetric = True
wing.vertical = False
# Segment
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Section_1'
segment.percent_span_location = 0.
segment.twist = 0.
segment.root_chord_percent = 1.5
segment.dihedral_outboard = 1.0 * Units.degrees
segment.sweeps.quarter_chord = 8.5 * Units.degrees
segment.thickness_to_chord = 0.18
wing.Segments.append(segment)
# Segment
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Section_2'
segment.percent_span_location = 0.227
segment.twist = 0.
segment.root_chord_percent = 1.
segment.dihedral_outboard = 1.0 * Units.degrees
segment.sweeps.quarter_chord = 0.0 * Units.degrees
segment.thickness_to_chord = 0.12
wing.Segments.append(segment)
# Segment
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Section_3'
segment.percent_span_location = 1.0
segment.twist = 0.
segment.root_chord_percent = 1.0
segment.dihedral_outboard = 1.0 * Units.degrees
segment.sweeps.quarter_chord = 0.0 * Units.degrees
segment.thickness_to_chord = 0.12
wing.Segments.append(segment)
# Fill out more segment properties automatically
wing = wing_segmented_planform(wing)
# add to vehicle
vehicle.append_component(wing)
# WING PROPERTIES
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_tail'
wing.aspect_ratio = 4.0
wing.sweeps.quarter_chord = 0.0
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.spans.projected = 8.0 * Units.feet
wing.chords.root = 2.0 * Units.feet
wing.total_length = 2.0 * Units.feet
wing.chords.tip = 2.0 * Units.feet
wing.chords.mean_aerodynamic = 2.0 * Units.feet
wing.dihedral = 0. * Units.degrees
wing.areas.reference = 16.0 * Units.feet**2
wing.areas.wetted = 32.0 * Units.feet**2
wing.areas.exposed = 32.0 * Units.feet**2
wing.twists.root = 0. * Units.degrees
wing.twists.tip = 0. * Units.degrees
wing.origin = [[4.0, 0.0, 0.205]]
wing.aerodynamic_center = [4.2, 0., 0.]
wing.symmetric = True
# add to vehicle
vehicle.append_component(wing)
# WING PROPERTIES
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_tail_1'
wing.aspect_ratio = 2.
wing.sweeps.quarter_chord = 20.0 * Units.degrees
wing.thickness_to_chord = 0.12
wing.taper = 0.5
wing.spans.projected = 3.0 * Units.feet
wing.chords.root = 2.0 * Units.feet
wing.total_length = 2.0 * Units.feet
wing.chords.tip = 1.0 * Units.feet
wing.chords.mean_aerodynamic = 1.5 * Units.feet
wing.areas.reference = 4.5 * Units.feet**2
wing.areas.wetted = 9.0 * Units.feet**2
wing.areas.exposed = 9.0 * Units.feet**2
wing.twists.root = 0. * Units.degrees
wing.twists.tip = 0. * Units.degrees
wing.origin = [[4.0, 4.0 * 0.3048, 0.205]]
wing.aerodynamic_center = [4.2, 0, 0]
wing.winglet_fraction = 0.0
wing.vertical = True
wing.symmetric = False
# add to vehicle
vehicle.append_component(wing)
# WING PROPERTIES
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_tail_2'
wing.aspect_ratio = 2.
wing.sweeps.quarter_chord = 20.0 * Units.degrees
wing.thickness_to_chord = 0.12
wing.taper = 0.5
wing.spans.projected = 3.0 * Units.feet
wing.chords.root = 2.0 * Units.feet
wing.total_length = 2.0 * Units.feet
wing.chords.tip = 1.0 * Units.feet
wing.chords.mean_aerodynamic = 1.5 * Units.feet
wing.areas.reference = 4.5 * Units.feet**2
wing.areas.wetted = 9.0 * Units.feet**2
wing.areas.exposed = 9.0 * Units.feet**2
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[4.0, -4.0 * 0.3048, 0.205]]
wing.aerodynamic_center = [4.2, 0, 0]
wing.winglet_fraction = 0.0
wing.vertical = True
wing.symmetric = False
# add to vehicle
vehicle.append_component(wing)
# ---------------------------------------------------------------
# FUSELAGE
# ---------------------------------------------------------------
# FUSELAGE PROPERTIES
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.configuration = 'Tube_Wing'
fuselage.seats_abreast = 2.
fuselage.seat_pitch = 3.
fuselage.fineness.nose = 0.88
fuselage.fineness.tail = 1.13
fuselage.lengths.nose = 3.2 * Units.feet
fuselage.lengths.tail = 6.4 * Units.feet
fuselage.lengths.cabin = 6.4 * Units.feet
fuselage.lengths.total = 5.1
fuselage.width = 5.85 * Units.feet
fuselage.heights.maximum = 4.65 * Units.feet
fuselage.heights.at_quarter_length = 3.75 * Units.feet
fuselage.heights.at_wing_root_quarter_chord = 4.65 * Units.feet
fuselage.heights.at_three_quarters_length = 4.26 * Units.feet
fuselage.areas.wetted = 236. * Units.feet**2
fuselage.areas.front_projected = 0.14 * Units.feet**2
fuselage.effective_diameter = 5.85 * Units.feet
fuselage.differential_pressure = 0.
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_0'
segment.percent_x_location = 0.
segment.percent_z_location = -0.267 / 4.10534
segment.height = 0.1
segment.width = 0.1
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_1'
segment.percent_x_location = 0.2579 / 4.10534
segment.percent_z_location = -0.05881 / 1.372
segment.height = 0.5201
segment.width = 0.75
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_2'
segment.percent_x_location = 0.9939 / 4.10534
segment.percent_z_location = -0.0446 / 4.10534
segment.height = 1.18940
segment.width = 1.42045
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_3'
segment.percent_x_location = 1.95060 / 4.10534
segment.percent_z_location = 0
segment.height = 1.37248
segment.width = 1.35312
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_4'
segment.percent_x_location = 3.02797 / 4.10534
segment.percent_z_location = 0.25 / 4.10534
segment.height = 0.6
segment.width = 0.4
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_5'
segment.percent_x_location = 1.
segment.percent_z_location = 0.42522 / 4.10534
segment.height = 0.05
segment.width = 0.05
fuselage.Segments.append(segment)
# add to vehicle
vehicle.append_component(fuselage)
#-------------------------------------------------------------------
# INNER BOOMS
#-------------------------------------------------------------------
long_boom = SUAVE.Components.Fuselages.Fuselage()
long_boom.tag = 'boom_1r'
long_boom.configuration = 'boom'
long_boom.origin = [[0.543, 1.630, -0.326]]
long_boom.seats_abreast = 0.
long_boom.seat_pitch = 0.0
long_boom.fineness.nose = 0.950
long_boom.fineness.tail = 1.029
long_boom.lengths.nose = 0.2
long_boom.lengths.tail = 0.2
long_boom.lengths.cabin = 2.5
long_boom.lengths.total = 3.5
long_boom.width = 0.15
long_boom.heights.maximum = 0.15
long_boom.heights.at_quarter_length = 0.15
long_boom.heights.at_three_quarters_length = 0.15
long_boom.heights.at_wing_root_quarter_chord = 0.15
long_boom.areas.wetted = 0.018
long_boom.areas.front_projected = 0.018
long_boom.effective_diameter = 0.15
long_boom.differential_pressure = 0.
long_boom.symmetric = True
long_boom.index = 1
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_1'
segment.percent_x_location = 0.
segment.percent_z_location = 0.0
segment.height = 0.05
segment.width = 0.05
long_boom.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_2'
segment.percent_x_location = 0.2 / 5.6
segment.percent_z_location = 0.
segment.height = 0.15
segment.width = 0.15
long_boom.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_3'
segment.percent_x_location = 5.4 / 5.6
segment.percent_z_location = 0.
segment.height = 0.15
segment.width = 0.15
long_boom.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_4'
segment.percent_x_location = 1.
segment.percent_z_location = 0.
segment.height = 0.05
segment.width = 0.05
long_boom.Segments.append(segment)
# add to vehicle
vehicle.append_component(long_boom)
# add left long boom
long_boom = deepcopy(vehicle.fuselages.boom_1r)
long_boom.origin[0][1] = -long_boom.origin[0][1]
long_boom.tag = 'Boom_1L'
long_boom.index = 1
vehicle.append_component(long_boom)
#-------------------------------------------------------------------
# OUTER BOOMS
#-------------------------------------------------------------------
short_boom = SUAVE.Components.Fuselages.Fuselage()
short_boom.tag = 'boom_2r'
short_boom.configuration = 'boom'
short_boom.origin = [[0.543, 2.826, -0.326]]
short_boom.seats_abreast = 0.
short_boom.seat_pitch = 0.0
short_boom.fineness.nose = 0.950
short_boom.fineness.tail = 1.029
short_boom.lengths.nose = 0.2
short_boom.lengths.tail = 0.2
short_boom.lengths.cabin = 2.0
short_boom.lengths.total = 3.3
short_boom.width = 0.15
short_boom.heights.maximum = 0.15
short_boom.heights.at_quarter_length = 0.15
short_boom.heights.at_three_quarters_length = 0.15
short_boom.heights.at_wing_root_quarter_chord = 0.15
short_boom.areas.wetted = 0.018
short_boom.areas.front_projected = 0.018
short_boom.effective_diameter = 0.15
short_boom.differential_pressure = 0.
short_boom.y_pitch_count = 2
short_boom.y_pitch = 1.196
short_boom.symmetric = True
short_boom.index = 1
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_1'
segment.percent_x_location = 0.
segment.percent_z_location = 0.0
segment.height = 0.05
segment.width = 0.05
short_boom.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_2'
segment.percent_x_location = 0.2 / 3.3
segment.percent_z_location = 0.
segment.height = 0.15
segment.width = 0.15
short_boom.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_3'
segment.percent_x_location = 3.1 / 3.3
segment.percent_z_location = 0.
segment.height = 0.15
segment.width = 0.15
short_boom.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_4'
segment.percent_x_location = 1.
segment.percent_z_location = 0.
segment.height = 0.05
segment.width = 0.05
short_boom.Segments.append(segment)
# add to vehicle
vehicle.append_component(short_boom)
# add outer right boom
short_boom = deepcopy(vehicle.fuselages.boom_2r)
short_boom.origin[0][1] = short_boom.y_pitch + short_boom.origin[0][1]
short_boom.tag = 'boom_3r'
short_boom.index = 1
vehicle.append_component(short_boom)
# add inner left boom
short_boom = deepcopy(vehicle.fuselages.boom_2r)
short_boom.origin[0][1] = -(short_boom.origin[0][1])
short_boom.tag = 'boom_2l'
short_boom.index = 1
vehicle.append_component(short_boom)
short_boom = deepcopy(vehicle.fuselages.boom_2r)
short_boom.origin[0][1] = -(short_boom.origin[0][1] + short_boom.y_pitch)
short_boom.tag = 'boom_3l'
short_boom.index = 1
vehicle.append_component(short_boom)
#------------------------------------------------------------------
# Nacelles
#------------------------------------------------------------------
rotor_nacelle = SUAVE.Components.Nacelles.Nacelle()
rotor_nacelle.tag = 'rotor_nacelle'
rotor_nacelle_origins = [[0.543, 1.63, -0.126], [0.543, -1.63, -0.126],
[3.843, 1.63, -0.126], [3.843, -1.63, -0.126],
[0.543, 2.826, -0.126], [0.543, -2.826, -0.126],
[3.843, 2.826, -0.126], [3.843, -2.826, -0.126],
[0.543, 4.022, -0.126], [0.543, -4.022, -0.126],
[3.843, 4.022, -0.126], [3.843, -4.022, -0.126]]
rotor_nacelle.length = 0.25
rotor_nacelle.diameter = 0.25
rotor_nacelle.orientation_euler_angles = [0, -90 * Units.degrees, 0.]
rotor_nacelle.flow_through = False
nac_segment = SUAVE.Components.Lofted_Body_Segment.Segment()
nac_segment.tag = 'segment_1'
nac_segment.percent_x_location = 0.0
nac_segment.height = 0.2
nac_segment.width = 0.2
rotor_nacelle.append_segment(nac_segment)
nac_segment = SUAVE.Components.Lofted_Body_Segment.Segment()
nac_segment.tag = 'segment_2'
nac_segment.percent_x_location = 0.25
nac_segment.height = 0.25
nac_segment.width = 0.25
rotor_nacelle.append_segment(nac_segment)
nac_segment = SUAVE.Components.Lofted_Body_Segment.Segment()
nac_segment.tag = 'segment_3'
nac_segment.percent_x_location = 0.5
nac_segment.height = 0.3
nac_segment.width = 0.3
rotor_nacelle.append_segment(nac_segment)
nac_segment = SUAVE.Components.Lofted_Body_Segment.Segment()
nac_segment.tag = 'segment_4'
nac_segment.percent_x_location = 0.75
nac_segment.height = 0.25
nac_segment.width = 0.25
rotor_nacelle.append_segment(nac_segment)
nac_segment = SUAVE.Components.Lofted_Body_Segment.Segment()
nac_segment.tag = 'segment_5'
nac_segment.percent_x_location = 1.0
nac_segment.height = 0.2
nac_segment.width = 0.2
rotor_nacelle.append_segment(nac_segment)
rotor_nacelle.areas.wetted = np.pi * rotor_nacelle.diameter * rotor_nacelle.length + 0.5 * np.pi * rotor_nacelle.diameter**2
for idx in range(12):
nacelle = deepcopy(rotor_nacelle)
nacelle.tag = 'nacelle_' + str(idx)
nacelle.origin = [rotor_nacelle_origins[idx]]
vehicle.append_component(nacelle)
#------------------------------------------------------------------
# network
#------------------------------------------------------------------
net = Lift_Cruise()
net.number_of_lift_rotor_engines = 12
net.number_of_propeller_engines = 1
net.nacelle_diameter = 0.6 * Units.feet
net.engine_length = 0.5 * Units.feet
net.areas = Data()
net.areas.wetted = np.pi * net.nacelle_diameter * net.engine_length + 0.5 * np.pi * net.nacelle_diameter**2
net.voltage = 500.
#------------------------------------------------------------------
# Design Electronic Speed Controller
#------------------------------------------------------------------
lift_rotor_esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller(
)
lift_rotor_esc.efficiency = 0.95
net.lift_rotor_esc = lift_rotor_esc
propeller_esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller(
)
propeller_esc.efficiency = 0.95
net.propeller_esc = propeller_esc
#------------------------------------------------------------------
# Design Payload
#------------------------------------------------------------------
payload = SUAVE.Components.Energy.Peripherals.Avionics()
payload.power_draw = 0.
payload.mass_properties.mass = 200. * Units.kg
net.payload = payload
#------------------------------------------------------------------
# Design Avionics
#------------------------------------------------------------------
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 200. * Units.watts
net.avionics = avionics
#------------------------------------------------------------------
# Design Battery
#------------------------------------------------------------------
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion_LiNiMnCoO2_18650(
)
bat.mass_properties.mass = 500. * Units.kg
bat.max_voltage = net.voltage
initialize_from_mass(bat)
# Here we, are going to assume a battery pack module shape. This step is optional but
# required for thermal analysis of tge pack
number_of_modules = 10
bat.module_config.total = int(
np.ceil(bat.pack_config.total / number_of_modules))
bat.module_config.normal_count = int(
np.ceil(bat.module_config.total / bat.pack_config.series))
bat.module_config.parallel_count = int(
np.ceil(bat.module_config.total / bat.pack_config.parallel))
net.battery = bat
#------------------------------------------------------------------
# Design Rotors and Propellers
#------------------------------------------------------------------
# atmosphere and flight conditions for propeller/rotor design
g = 9.81 # gravitational acceleration
S = vehicle.reference_area # reference area
speed_of_sound = 340 # speed of sound
rho = 1.22 # reference density
fligth_CL = 0.75 # cruise target lift coefficient
AR = vehicle.wings.main_wing.aspect_ratio # aspect ratio
Cd0 = 0.06 # profile drag
Cdi = fligth_CL**2 / (np.pi * AR * 0.98) # induced drag
Cd = Cd0 + Cdi # total drag
V_inf = 110. * Units['mph'] # freestream velocity
Drag = S * (0.5 * rho * V_inf**2) * Cd # cruise drag
Hover_Load = vehicle.mass_properties.takeoff * g # hover load
net.identical_propellers = True
net.identical_lift_rotors = True
# Thrust Propeller
propeller = SUAVE.Components.Energy.Converters.Propeller()
propeller.number_of_blades = 3
propeller.freestream_velocity = V_inf
propeller.tip_radius = 1.0668
propeller.hub_radius = 0.21336
propeller.design_tip_mach = 0.5
propeller.angular_velocity = propeller.design_tip_mach * speed_of_sound / propeller.tip_radius
propeller.design_Cl = 0.7
propeller.design_altitude = 1000 * Units.feet
propeller.design_thrust = (Drag * 2.5) / net.number_of_propeller_engines
propeller.variable_pitch = True
propeller.airfoil_geometry = ['../Vehicles/Airfoils/NACA_4412.txt']
propeller.airfoil_polars = [[
'../Vehicles/Airfoils/Polars/NACA_4412_polar_Re_50000.txt',
'../Vehicles/Airfoils/Polars/NACA_4412_polar_Re_100000.txt',
'../Vehicles/Airfoils/Polars/NACA_4412_polar_Re_200000.txt',
'../Vehicles/Airfoils/Polars/NACA_4412_polar_Re_500000.txt',
'../Vehicles/Airfoils/Polars/NACA_4412_polar_Re_1000000.txt'
]]
propeller.airfoil_polar_stations = [
0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0
]
propeller = propeller_design(propeller,
number_of_airfoil_section_points=50)
propeller.origin = [[16. * 0.3048, 0., 2.02 * 0.3048]]
net.propellers.append(propeller)
# Lift Rotors
lift_rotor = SUAVE.Components.Energy.Converters.Lift_Rotor()
lift_rotor.tip_radius = 2.8 * Units.feet
lift_rotor.hub_radius = 0.35 * Units.feet
lift_rotor.number_of_blades = 2
lift_rotor.design_tip_mach = 0.65
lift_rotor.disc_area = np.pi * (lift_rotor.tip_radius**2)
lift_rotor.freestream_velocity = 500. * Units['ft/min']
lift_rotor.angular_velocity = lift_rotor.design_tip_mach * speed_of_sound / lift_rotor.tip_radius
lift_rotor.design_Cl = 0.7
lift_rotor.design_altitude = 20 * Units.feet
lift_rotor.design_thrust = Hover_Load / (
net.number_of_lift_rotor_engines - 1
) # contingency for one-engine-inoperative condition
lift_rotor.variable_pitch = True
lift_rotor.airfoil_geometry = ['../Vehicles/Airfoils/NACA_4412.txt']
lift_rotor.airfoil_polars = [[
'../Vehicles/Airfoils/Polars/NACA_4412_polar_Re_50000.txt',
'../Vehicles/Airfoils/Polars/NACA_4412_polar_Re_100000.txt',
'../Vehicles/Airfoils/Polars/NACA_4412_polar_Re_200000.txt',
'../Vehicles/Airfoils/Polars/NACA_4412_polar_Re_500000.txt',
'../Vehicles/Airfoils/Polars/NACA_4412_polar_Re_1000000.txt'
]]
lift_rotor.airfoil_polar_stations = [
0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0
]
lift_rotor = propeller_design(lift_rotor)
# Appending rotors with different origins
rotations = [1, -1, 1, -1, 1, -1, 1, -1, 1, -1, 1, -1]
origins = [[0.543, 1.63, -0.126], [0.543, -1.63, -0.126],
[3.843, 1.63, -0.126], [3.843, -1.63, -0.126],
[0.543, 2.826, -0.126], [0.543, -2.826, -0.126],
[3.843, 2.826, -0.126], [3.843, -2.826, -0.126],
[0.543, 4.022, -0.126], [0.543, -4.022, -0.126],
[3.843, 4.022, -0.126], [3.843, -4.022, -0.126]]
for ii in range(12):
lift_rotor = deepcopy(lift_rotor)
lift_rotor.tag = 'lift_rotor'
lift_rotor.rotation = rotations[ii]
lift_rotor.origin = [origins[ii]]
net.lift_rotors.append(lift_rotor)
net.number_of_lift_rotor_engines = 12
# append propellers to vehicle
net.lift_rotor = lift_rotor
#------------------------------------------------------------------
# Design Motors
#------------------------------------------------------------------
# Propeller (Thrust) motor
propeller_motor = SUAVE.Components.Energy.Converters.Motor()
propeller_motor.efficiency = 0.95
propeller_motor.nominal_voltage = bat.max_voltage
propeller_motor.mass_properties.mass = 2.0 * Units.kg
propeller_motor.origin = propeller.origin
propeller_motor.propeller_radius = propeller.tip_radius
propeller_motor.no_load_current = 2.0
propeller_motor = size_optimal_motor(propeller_motor, propeller)
net.propeller_motors.append(propeller_motor)
# Rotor (Lift) Motor
lift_rotor_motor = SUAVE.Components.Energy.Converters.Motor()
lift_rotor_motor.efficiency = 0.85
lift_rotor_motor.nominal_voltage = bat.max_voltage * 3 / 4
lift_rotor_motor.mass_properties.mass = 3. * Units.kg
lift_rotor_motor.origin = lift_rotor.origin
lift_rotor_motor.propeller_radius = lift_rotor.tip_radius
lift_rotor_motor.gearbox_efficiency = 1.0
lift_rotor_motor.no_load_current = 4.0
lift_rotor_motor = size_optimal_motor(lift_rotor_motor, lift_rotor)
# Appending motors with different origins
for _ in range(12):
lift_rotor_motor = deepcopy(lift_rotor_motor)
lift_rotor_motor.tag = 'motor'
net.lift_rotor_motors.append(lift_rotor_motor)
# append motor origin spanwise locations onto wing data structure
vehicle.append_component(net)
# Add extra drag sources from motors, props, and landing gear. All of these hand measured
motor_height = .25 * Units.feet
motor_width = 1.6 * Units.feet
propeller_width = 1. * Units.inches
propeller_height = propeller_width * .12
main_gear_width = 1.5 * Units.inches
main_gear_length = 2.5 * Units.feet
nose_gear_width = 2. * Units.inches
nose_gear_length = 2. * Units.feet
nose_tire_height = (0.7 + 0.4) * Units.feet
nose_tire_width = 0.4 * Units.feet
main_tire_height = (0.75 + 0.5) * Units.feet
main_tire_width = 4. * Units.inches
total_excrescence_area_spin = 12.*motor_height*motor_width + 2.*main_gear_length*main_gear_width \
+ nose_gear_width*nose_gear_length + 2*main_tire_height*main_tire_width\
+ nose_tire_height*nose_tire_width
total_excrescence_area_no_spin = total_excrescence_area_spin + 12 * propeller_height * propeller_width
vehicle.excrescence_area_no_spin = total_excrescence_area_no_spin
vehicle.excrescence_area_spin = total_excrescence_area_spin
vehicle.wings['main_wing'].motor_spanwise_locations = np.multiply(
2. / 36.25, [
-5.435, -5.435, -9.891, -9.891, -14.157, -14.157, 5.435, 5.435,
9.891, 9.891, 14.157, 14.157
])
vehicle.wings['main_wing'].winglet_fraction = 0.0
vehicle.wings['main_wing'].thickness_to_chord = 0.18
vehicle.wings['main_wing'].chords.mean_aerodynamic = 0.9644599977664836
vehicle.weight_breakdown = empty(vehicle)
compute_component_centers_of_gravity(vehicle)
vehicle.center_of_gravity()
return vehicle
def vsp_read(tag, units_type='SI',specified_network=None):
"""This reads an OpenVSP vehicle geometry and writes it into a SUAVE vehicle format.
Includes wings, fuselages, and propellers.
Assumptions:
1. OpenVSP vehicle is composed of conventionally shaped fuselages, wings, and propellers.
1a. OpenVSP fuselage: generally narrow at nose and tail, wider in center).
1b. Fuselage is designed in VSP as it appears in real life. That is, the VSP model does not rely on
superficial elements such as canopies, stacks, or additional fuselages to cover up internal lofting oddities.
1c. This program will NOT account for multiple geometries comprising the fuselage. For example: a wingbox mounted beneath
is a separate geometry and will NOT be processed.
2. Fuselage origin is located at nose. VSP file origin can be located anywhere, preferably at the forward tip
of the vehicle or in front (to make all X-coordinates of vehicle positive).
3. Written for OpenVSP 3.21.1
Source:
N/A
Inputs:
1. A tag for an XML file in format .vsp3.
2. Units_type set to 'SI' (default) or 'Imperial'
3. User-specified network
Outputs:
Writes SUAVE vehicle with these geometries from VSP: (All values default to SI. Any other 2nd argument outputs Imperial.)
Wings.Wing. (* is all keys)
origin [m] in all three dimensions
spans.projected [m]
chords.root [m]
chords.tip [m]
aspect_ratio [-]
sweeps.quarter_chord [radians]
twists.root [radians]
twists.tip [radians]
thickness_to_chord [-]
dihedral [radians]
symmetric <boolean>
tag <string>
areas.reference [m^2]
areas.wetted [m^2]
Segments.
tag <string>
twist [radians]
percent_span_location [-] .1 is 10%
root_chord_percent [-] .1 is 10%
dihedral_outboard [radians]
sweeps.quarter_chord [radians]
thickness_to_chord [-]
airfoil <NACA 4-series, 6 series, or airfoil file>
Fuselages.Fuselage.
origin [m] in all three dimensions
width [m]
lengths.
total [m]
nose [m]
tail [m]
heights.
maximum [m]
at_quarter_length [m]
at_three_quarters_length [m]
effective_diameter [m]
fineness.nose [-] ratio of nose section length to fuselage effective diameter
fineness.tail [-] ratio of tail section length to fuselage effective diameter
areas.wetted [m^2]
tag <string>
segment[]. (segments are in ordered container and callable by number)
vsp.shape [point,circle,round_rect,general_fuse,fuse_file]
vsp.xsec_id <10 digit string>
percent_x_location
percent_z_location
height
width
length
effective_diameter
tag
vsp.xsec_num <integer of fuselage segment quantity>
vsp.xsec_surf_id <10 digit string>
Propellers.Propeller.
location[X,Y,Z] [radians]
rotation[X,Y,Z] [radians]
tip_radius [m]
hub_radius [m]
thrust_angle [radians]
Properties Used:
N/A
"""
vsp.ClearVSPModel()
vsp.ReadVSPFile(tag)
vsp_fuselages = []
vsp_wings = []
vsp_props = []
vsp_nacelles = []
vsp_nacelle_type = []
vsp_geoms = vsp.FindGeoms()
geom_names = []
vehicle = SUAVE.Vehicle()
vehicle.tag = tag
if units_type == 'SI':
units_type = 'SI'
elif units_type == 'inches':
units_type = 'inches'
else:
units_type = 'imperial'
# The two for-loops below are in anticipation of an OpenVSP API update with a call for GETGEOMTYPE.
# This print function allows user to enter VSP GeomID manually as first argument in vsp_read functions.
print("VSP geometry IDs: ")
# Label each geom type by storing its VSP geom ID.
for geom in vsp_geoms:
geom_name = vsp.GetGeomName(geom)
geom_names.append(geom_name)
print(str(geom_name) + ': ' + geom)
# --------------------------------
# AUTOMATIC VSP ENTRY & PROCESSING
# --------------------------------
for geom in vsp_geoms:
geom_name = vsp.GetGeomName(geom)
geom_type = vsp.GetGeomTypeName(str(geom))
if geom_type == 'Fuselage':
vsp_fuselages.append(geom)
if geom_type == 'Wing':
vsp_wings.append(geom)
if geom_type == 'Propeller':
vsp_props.append(geom)
if (geom_type == 'Stack') or (geom_type == 'BodyOfRevolution'):
vsp_nacelle_type.append(geom_type)
vsp_nacelles.append(geom)
# --------------------------------------------------
# Read Fuselages
# --------------------------------------------------
for fuselage_id in vsp_fuselages:
sym_planar = vsp.GetParmVal(fuselage_id, 'Sym_Planar_Flag', 'Sym') # Check for symmetry
sym_origin = vsp.GetParmVal(fuselage_id, 'Sym_Ancestor_Origin_Flag', 'Sym')
if sym_planar == 2. and sym_origin == 1.:
num_fus = 2
sym_flag = [1,-1]
else:
num_fus = 1
sym_flag = [1]
for fux_idx in range(num_fus): # loop through fuselages on aircraft
fuselage = read_vsp_fuselage(fuselage_id,fux_idx,sym_flag[fux_idx],units_type)
vehicle.append_component(fuselage)
# --------------------------------------------------
# Read Wings
# --------------------------------------------------
for wing_id in vsp_wings:
wing = read_vsp_wing(wing_id, units_type)
vehicle.append_component(wing)
# --------------------------------------------------
# Read Nacelles
# --------------------------------------------------
for nac_id, nacelle_id in enumerate(vsp_nacelles):
nacelle = read_vsp_nacelle(nacelle_id,vsp_nacelle_type[nac_id], units_type)
vehicle.append_component(nacelle)
# --------------------------------------------------
# Read Propellers/Rotors and assign to a network
# --------------------------------------------------
# Initialize rotor network elements
number_of_lift_rotor_engines = 0
number_of_propeller_engines = 0
lift_rotors = Data()
propellers = Data()
for prop_id in vsp_props:
prop = read_vsp_propeller(prop_id,units_type)
prop.tag = vsp.GetGeomName(prop_id)
if prop.orientation_euler_angles[1] >= 70 * Units.degrees:
lift_rotors.append(prop)
number_of_lift_rotor_engines += 1
else:
propellers.append(prop)
number_of_propeller_engines += 1
if specified_network == None:
# If no network specified, assign a network
if number_of_lift_rotor_engines>0 and number_of_propeller_engines>0:
net = Lift_Cruise()
else:
net = Battery_Propeller()
else:
net = specified_network
# Create the rotor network
if net.tag == "Lift_Cruise":
# Lift + Cruise network
for i in range(number_of_lift_rotor_engines):
net.lift_rotors.append(lift_rotors[list(lift_rotors.keys())[i]])
net.number_of_lift_rotor_engines = number_of_lift_rotor_engines
for i in range(number_of_propeller_engines):
net.propellers.append(propellers[list(propellers.keys())[i]])
net.number_of_propeller_engines = number_of_propeller_engines
elif net.tag == "Battery_Propeller":
# Append all rotors as propellers for the battery propeller network
for i in range(number_of_lift_rotor_engines):
# Accounts for multicopter configurations
net.propellers.append(lift_rotors[list(lift_rotors.keys())[i]])
for i in range(number_of_propeller_engines):
net.propellers.append(propellers[list(propellers.keys())[i]])
net.number_of_propeller_engines = number_of_lift_rotor_engines + number_of_propeller_engines
vehicle.networks.append(net)
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Lift_Cruise_CRM'
vehicle.configuration = 'eVTOL'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 2450. * Units.lb
vehicle.mass_properties.operating_empty = 2250. * Units.lb # Approximate
vehicle.mass_properties.max_takeoff = 2450. * Units.lb # Approximate
vehicle.mass_properties.center_of_gravity = [2.0144, 0. , 0. ] # Approximate
# basic parameters
vehicle.reference_area = 10.76
vehicle.envelope.ultimate_load = 5.7
vehicle.envelope.limit_load = 3.
# ------------------------------------------------------------------
# WINGS
# ------------------------------------------------------------------
# WING PROPERTIES
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 10.76
wing.sweeps.quarter_chord = 0.0 * Units.degrees
wing.thickness_to_chord = 0.18
wing.taper = 1.
wing.span_efficiency = 0.9
wing.spans.projected = 35.0 * Units.feet
wing.chords.root = 3.25 * Units.feet
wing.total_length = 3.25 * Units.feet
wing.chords.tip = 3.25 * Units.feet
wing.chords.mean_aerodynamic = 3.25 * Units.feet
wing.dihedral = 1.0 * Units.degrees
wing.areas.reference = 113.75 * Units.feet**2
wing.areas.wetted = 227.5 * Units.feet**2
wing.areas.exposed = 227.5 * Units.feet**2
wing.twists.root = 4.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [1.5, 0., 0. ]
wing.aerodynamic_center = [1.975 , 0., 0.]
wing.winglet_fraction = 0.0
wing.symmetric = True
wing.vertical = False
# Segment
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Section_1'
segment.percent_span_location = 0.
segment.twist = 0.
segment.root_chord_percent = 1.5
segment.dihedral_outboard = 1.0 * Units.degrees
segment.sweeps.quarter_chord = 8.5 * Units.degrees
segment.thickness_to_chord = 0.18
wing.Segments.append(segment)
# Segment
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Section_2'
segment.percent_span_location = 0.227
segment.twist = 0.
segment.root_chord_percent = 1.
segment.dihedral_outboard = 1.0 * Units.degrees
segment.sweeps.quarter_chord = 0.0 * Units.degrees
segment.thickness_to_chord = 0.12
wing.Segments.append(segment)
# Segment
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Section_3'
segment.percent_span_location = 1.0
segment.twist = 0.
segment.root_chord_percent = 1.0
segment.dihedral_outboard = 1.0 * Units.degrees
segment.sweeps.quarter_chord = 0.0 * Units.degrees
segment.thickness_to_chord = 0.12
wing.Segments.append(segment)
# add to vehicle
vehicle.append_component(wing)
# WING PROPERTIES
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_tail'
wing.aspect_ratio = 4.0
wing.sweeps.quarter_chord = 0.0
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.span_efficiency = 0.9
wing.spans.projected = 8.0 * Units.feet
wing.chords.root = 2.0 * Units.feet
wing.total_length = 2.0 * Units.feet
wing.chords.tip = 2.0 * Units.feet
wing.chords.mean_aerodynamic = 2.0 * Units.feet
wing.dihedral = 0. * Units.degrees
wing.areas.reference = 16.0 * Units.feet**2
wing.areas.wetted = 32.0 * Units.feet**2
wing.areas.exposed = 32.0 * Units.feet**2
wing.twists.root = 0. * Units.degrees
wing.twists.tip = 0. * Units.degrees
wing.origin = [14.0*0.3048 , 0.0 , 0.205 ]
wing.aerodynamic_center = [15.0*0.3048 , 0., 0.]
wing.symmetric = True
# add to vehicle
vehicle.append_component(wing)
# WING PROPERTIES
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_tail_1'
wing.aspect_ratio = 2.
wing.sweeps.quarter_chord = 20.0 * Units.degrees
wing.thickness_to_chord = 0.12
wing.taper = 0.5
wing.span_efficiency = 0.9
wing.spans.projected = 3.0 * Units.feet
wing.chords.root = 2.0 * Units.feet
wing.total_length = 2.0 * Units.feet
wing.chords.tip = 1.0 * Units.feet
wing.chords.mean_aerodynamic = 1.5 * Units.feet
wing.areas.reference = 4.5 * Units.feet**2
wing.areas.wetted = 9.0 * Units.feet**2
wing.areas.exposed = 9.0 * Units.feet**2
wing.twists.root = 0. * Units.degrees
wing.twists.tip = 0. * Units.degrees
wing.origin = [14.0*0.3048 , 4.0*0.3048 , 0.205 ]
wing.aerodynamic_center = 0.0
wing.winglet_fraction = 0.0
wing.vertical = True
wing.symmetric = False
# add to vehicle
vehicle.append_component(wing)
# WING PROPERTIES
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_tail_2'
wing.aspect_ratio = 2.
wing.sweeps.quarter_chord = 20.0 * Units.degrees
wing.thickness_to_chord = 0.12
wing.taper = 0.5
wing.span_efficiency = 0.9
wing.spans.projected = 3.0 * Units.feet
wing.chords.root = 2.0 * Units.feet
wing.total_length = 2.0 * Units.feet
wing.chords.tip = 1.0 * Units.feet
wing.chords.mean_aerodynamic = 1.5 * Units.feet
wing.areas.reference = 4.5 * Units.feet**2
wing.areas.wetted = 9.0 * Units.feet**2
wing.areas.exposed = 9.0 * Units.feet**2
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [14.0*0.3048 , -4.0*0.3048 , 0.205 ]
wing.aerodynamic_center = 0.0
wing.winglet_fraction = 0.0
wing.vertical = True
wing.symmetric = False
# add to vehicle
vehicle.append_component(wing)
# ---------------------------------------------------------------
# FUSELAGE
# ---------------------------------------------------------------
# FUSELAGE PROPERTIES
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.configuration = 'Tube_Wing'
fuselage.origin = [[0. , 0., 0.]]
fuselage.seats_abreast = 2.
fuselage.seat_pitch = 3.
fuselage.fineness.nose = 0.88
fuselage.fineness.tail = 1.13
fuselage.lengths.nose = 3.2 * Units.feet
fuselage.lengths.tail = 6.4 * Units.feet
fuselage.lengths.cabin = 6.4 * Units.feet
fuselage.lengths.total = 16.0 * Units.feet
fuselage.width = 5.85 * Units.feet
fuselage.heights.maximum = 4.65 * Units.feet
fuselage.heights.at_quarter_length = 3.75 * Units.feet
fuselage.heights.at_wing_root_quarter_chord = 4.65 * Units.feet
fuselage.heights.at_three_quarters_length = 4.26 * Units.feet
fuselage.areas.wetted = 236. * Units.feet**2
fuselage.areas.front_projected = 0.14 * Units.feet**2
fuselage.effective_diameter = 5.85 * Units.feet
fuselage.differential_pressure = 0.
# Segment
segment = SUAVE.Components.Fuselages.Segment()
segment.tag = 'segment_1'
segment.origin = [0., 0. ,0.]
segment.percent_x_location = 0.
segment.percent_z_location = 0.0
segment.height = 0.1 * Units.feet
segment.width = 0.1 * Units.feet
segment.length = 0.
segment.effective_diameter = 0.1 * Units.feet
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Fuselages.Segment()
segment.tag = 'segment_2'
segment.origin = [4.*0.3048 , 0. ,0.1*0.3048 ]
segment.percent_x_location = 0.25
segment.percent_z_location = 0.05
segment.height = 3.75 * Units.feet
segment.width = 5.65 * Units.feet
segment.length = 3.2 * Units.feet
segment.effective_diameter = 5.65 * Units.feet
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Fuselages.Segment()
segment.tag = 'segment_3'
segment.origin = [8.*0.3048 , 0. ,0.34*0.3048 ]
segment.percent_x_location = 0.5
segment.percent_z_location = 0.071
segment.height = 4.65 * Units.feet
segment.width = 5.55 * Units.feet
segment.length = 3.2 * Units.feet
segment.effective_diameter = 5.55 * Units.feet
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Fuselages.Segment()
segment.tag = 'segment_4'
segment.origin = [12.*0.3048 , 0. ,0.77*0.3048 ]
segment.percent_x_location = 0.75
segment.percent_z_location = 0.089
segment.height = 4.73 * Units.feet
segment.width = 4.26 * Units.feet
segment.length = 3.2 * Units.feet
segment.effective_diameter = 4.26 * Units.feet
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Fuselages.Segment()
segment.tag = 'segment_5'
segment.origin = [16.*0.3048 , 0. ,2.02*0.3048 ]
segment.percent_x_location = 1.0
segment.percent_z_location = 0.158
segment.height = 0.67 * Units.feet
segment.width = 0.33 * Units.feet
segment.length = 3.2 * Units.feet
segment.effective_diameter = 0.33 * Units.feet
fuselage.Segments.append(segment)
# add to vehicle
vehicle.append_component(fuselage)
#-------------------------------------------------------------------
# BOOMS
#-------------------------------------------------------------------
boom = SUAVE.Components.Fuselages.Fuselage()
boom.tag = 'Boom_1R'
boom.configuration = 'Boom'
boom.origin = [[0.718,7.5*0.3048 , -0.15 ]]
boom.seats_abreast = 0.
boom.seat_pitch = 0.0
boom.fineness.nose = 0.950
boom.fineness.tail = 1.029
boom.lengths.nose = 0.5 * Units.feet
boom.lengths.tail = 0.5 * Units.feet
boom.lengths.cabin = 9.0 * Units.feet
boom.lengths.total = 10 * Units.feet
boom.width = 0.5 * Units.feet
boom.heights.maximum = 0.5 * Units.feet
boom.heights.at_quarter_length = 0.5 * Units.feet
boom.heights.at_three_quarters_length = 0.5 * Units.feet
boom.heights.at_wing_root_quarter_chord = 0.5 * Units.feet
boom.areas.wetted = 18 * Units.feet**2
boom.areas.front_projected = 0.26 * Units.feet**2
boom.effective_diameter = 0.5 * Units.feet
boom.differential_pressure = 0.
boom.y_pitch_count = 2
boom.y_pitch = (72/12)*0.3048
boom.symmetric = True
boom.boom_pitch = 6 * Units.feet
boom.index = 1
# add to vehicle
vehicle.append_component(boom)
# create pattern of booms on one side
original_boom_origin = boom.origin
if boom.y_pitch_count > 1 :
for n in range(boom.y_pitch_count):
if n == 0:
continue
else:
index = n+1
boom = deepcopy(vehicle.fuselages.boom_1r)
boom.origin[0][1] = n*boom.boom_pitch + original_boom_origin[0][1]
boom.tag = 'Boom_' + str(index) + 'R'
boom.index = n
vehicle.append_component(boom)
if boom.symmetric :
for n in range(boom.y_pitch_count):
index = n+1
boom = deepcopy(vehicle.fuselages.boom_1r)
boom.origin[0][1] = -n*boom.boom_pitch - original_boom_origin[0][1]
boom.tag = 'Boom_' + str(index) + 'L'
boom.index = n
vehicle.append_component(boom)
#------------------------------------------------------------------
# PROPULSOR
#------------------------------------------------------------------
net = Lift_Cruise()
net.number_of_engines_lift = 12
net.number_of_engines_forward = 1
net.thrust_angle_lift = 90. * Units.degrees
net.thrust_angle_forward = 0.
net.nacelle_diameter = 0.6 * Units.feet
net.engine_length = 0.5 * Units.feet
net.areas = Data()
net.areas.wetted = np.pi*net.nacelle_diameter*net.engine_length + 0.5*np.pi*net.nacelle_diameter**2
net.voltage = 500.
#------------------------------------------------------------------
# Design Electronic Speed Controller
#------------------------------------------------------------------
esc_lift = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc_lift.efficiency = 0.95
net.esc_lift = esc_lift
esc_thrust = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc_thrust.efficiency = 0.95
net.esc_forward = esc_thrust
#------------------------------------------------------------------
# Design Payload
#------------------------------------------------------------------
payload = SUAVE.Components.Energy.Peripherals.Avionics()
payload.power_draw = 0.
payload.mass_properties.mass = 200. * Units.kg
net.payload = payload
#------------------------------------------------------------------
# Design Avionics
#------------------------------------------------------------------
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 200. * Units.watts
net.avionics = avionics
#------------------------------------------------------------------
# Design Battery
#------------------------------------------------------------------
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion()
bat.specific_energy = 300. * Units.Wh/Units.kg
bat.resistance = 0.005
bat.max_voltage = net.voltage
bat.mass_properties.mass = 300. * Units.kg
initialize_from_mass(bat, bat.mass_properties.mass)
net.battery = bat
#------------------------------------------------------------------
# Design Rotors and Propellers
#------------------------------------------------------------------
# atmosphere and flight conditions for propeller/rotor design
g = 9.81 # gravitational acceleration
S = vehicle.reference_area # reference area
speed_of_sound = 340 # speed of sound
rho = 1.22 # reference density
fligth_CL = 0.75 # cruise target lift coefficient
AR = vehicle.wings.main_wing.aspect_ratio # aspect ratio
Cd0 = 0.06 # profile drag
Cdi = fligth_CL**2/(np.pi*AR*0.98) # induced drag
Cd = Cd0 + Cdi # total drag
V_inf = 110.* Units['mph'] # freestream velocity
Drag = S * (0.5*rho*V_inf**2 )*Cd # cruise drag
Hover_Load = vehicle.mass_properties.takeoff*g # hover load
# Thrust Propeller
propeller = SUAVE.Components.Energy.Converters.Propeller()
propeller.number_blades = 3
propeller.number_of_engines = net.number_of_engines_forward
propeller.freestream_velocity = V_inf
propeller.tip_radius = 1.0668
propeller.hub_radius = 0.21336
propeller.design_tip_mach = 0.65
propeller.angular_velocity = propeller.design_tip_mach *speed_of_sound /propeller.tip_radius
propeller.design_Cl = 0.7
propeller.design_altitude = 1. * Units.km
propeller.design_thrust = (Drag*2.5)/net.number_of_engines_forward
propeller = propeller_design(propeller)
propeller.origin = [[16.*0.3048 , 0. ,2.02*0.3048 ]]
net.propeller = propeller
# Lift Rotors
rotor = SUAVE.Components.Energy.Converters.Rotor()
rotor.tip_radius = 2.8 * Units.feet
rotor.hub_radius = 0.35 * Units.feet
rotor.number_blades = 2
rotor.design_tip_mach = 0.65
rotor.number_of_engines = net.number_of_engines_lift
rotor.disc_area = np.pi*(rotor.tip_radius**2)
rotor.induced_hover_velocity = np.sqrt(Hover_Load/(2*rho*rotor.disc_area*net.number_of_engines_lift))
rotor.freestream_velocity = 500. * Units['ft/min']
rotor.angular_velocity = rotor.design_tip_mach* speed_of_sound /rotor.tip_radius
rotor.design_Cl = 0.7
rotor.design_altitude = 20 * Units.feet
rotor.design_thrust = (Hover_Load * 2.5 )/net.number_of_engines_lift
rotor.x_pitch_count = 2
rotor.y_pitch_count = vehicle.fuselages['boom_1r'].y_pitch_count
rotor.y_pitch = vehicle.fuselages['boom_1r'].y_pitch
rotor = propeller_design(rotor)
rotor.origin = vehicle.fuselages['boom_1r'].origin
rotor.symmetric = True
# populating propellers on one side of wing
if rotor.y_pitch_count > 1 :
for n in range(rotor.y_pitch_count):
if n == 0:
continue
propeller_origin = [rotor.origin[0][0] , rotor.origin[0][1] + n*rotor.y_pitch ,rotor.origin[0][2]]
rotor.origin.append(propeller_origin)
# populating propellers on one side of the vehicle
if rotor.x_pitch_count > 1 :
relative_prop_origins = np.linspace(0,vehicle.fuselages['boom_1r'].lengths.total,rotor.x_pitch_count)
for n in range(len(rotor.origin)):
for m in range(len(relative_prop_origins)-1):
propeller_origin = [rotor.origin[n][0] + relative_prop_origins[m+1] , rotor.origin[n][1] ,rotor.origin[n][2] ]
rotor.origin.append(propeller_origin)
# propulating propellers on the other side of thevehicle
if rotor.symmetric :
for n in range(len(rotor.origin)):
propeller_origin = [rotor.origin[n][0] , -rotor.origin[n][1] ,rotor.origin[n][2] ]
rotor.origin.append(propeller_origin)
# re-compute number of lift rotors if changed
net.number_of_engines_lift = len(rotor.origin)
# append propellers to vehicle
net.rotor = rotor
#------------------------------------------------------------------
# Design Motors
#------------------------------------------------------------------
# Propeller (Thrust) motor
motor_forward = SUAVE.Components.Energy.Converters.Motor()
motor_forward.efficiency = 0.95
motor_forward.nominal_voltage = bat.max_voltage *3/4
motor_forward.mass_properties.mass = 2.0 * Units.kg
motor_forward.origin = propeller.origin
motor_forward.propeller_radius = propeller.tip_radius
motor_forward.gear_ratio = 1.
motor_forward.gearbox_efficiency = 1. # Gear box efficiency
motor_forward.no_load_current = 2.0
motor_forward = compute_optimal_motor_parameters(motor_forward,propeller)
net.motor_forward = motor_forward
# Rotor (Lift) Motor
motor_lift = SUAVE.Components.Energy.Converters.Motor()
motor_lift.efficiency = 0.95
motor_lift.nominal_voltage = bat.max_voltage
motor_lift.mass_properties.mass = 3. * Units.kg
motor_lift.origin = rotor.origin
motor_lift.propeller_radius = rotor.tip_radius
motor_lift.gear_ratio = 1.0
motor_lift.gearbox_efficiency = 1.0
motor_lift.no_load_current = 4.0
motor_lift = compute_optimal_motor_parameters(motor_lift,rotor)
net.motor_lift = motor_lift
# append motor origin spanwise locations onto wing data structure
vehicle.append_component(net)
# Add extra drag sources from motors, props, and landing gear. All of these hand measured
motor_height = .25 * Units.feet
motor_width = 1.6 * Units.feet
propeller_width = 1. * Units.inches
propeller_height = propeller_width *.12
main_gear_width = 1.5 * Units.inches
main_gear_length = 2.5 * Units.feet
nose_gear_width = 2. * Units.inches
nose_gear_length = 2. * Units.feet
nose_tire_height = (0.7 + 0.4) * Units.feet
nose_tire_width = 0.4 * Units.feet
main_tire_height = (0.75 + 0.5) * Units.feet
main_tire_width = 4. * Units.inches
total_excrescence_area_spin = 12.*motor_height*motor_width + 2.*main_gear_length*main_gear_width \
+ nose_gear_width*nose_gear_length + 2*main_tire_height*main_tire_width\
+ nose_tire_height*nose_tire_width
total_excrescence_area_no_spin = total_excrescence_area_spin + 12*propeller_height*propeller_width
vehicle.excrescence_area_no_spin = total_excrescence_area_no_spin
vehicle.excrescence_area_spin = total_excrescence_area_spin
vehicle.wings['main_wing'].motor_spanwise_locations = np.multiply(
2./36.25,
[-5.435, -5.435, -9.891, -9.891, -14.157, -14.157,
5.435, 5.435, 9.891, 9.891, 14.157, 14.157])
vehicle.wings['main_wing'].winglet_fraction = 0.0
vehicle.wings['main_wing'].thickness_to_chord = 0.18
vehicle.wings['main_wing'].chords.mean_aerodynamic = 0.9644599977664836
return vehicle