def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Vahana'
vehicle.configuration = 'eVTOL'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 2250. * Units.lb
vehicle.mass_properties.operating_empty = 2250. * Units.lb
vehicle.mass_properties.max_takeoff = 2250. * Units.lb
vehicle.mass_properties.center_of_gravity = [[2.0144, 0., 0.]]
vehicle.reference_area = 10.58275476
vehicle.envelope.ultimate_load = 5.7
vehicle.envelope.limit_load = 3.
# ------------------------------------------------------
# WINGS
# ------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'canard_wing'
wing.aspect_ratio = 11.37706641
wing.sweeps.quarter_chord = 0.0
wing.thickness_to_chord = 0.18
wing.taper = 1.
wing.spans.projected = 6.65
wing.chords.root = 0.95
wing.total_length = 0.95
wing.chords.tip = 0.95
wing.chords.mean_aerodynamic = 0.95
wing.dihedral = 0.0
wing.areas.reference = 6.31
wing.areas.wetted = 12.635
wing.areas.exposed = 12.635
wing.twists.root = 0.
wing.twists.tip = 0.
wing.origin = [[0.1, 0.0, 0.5]]
wing.aerodynamic_center = [0., 0., 0.]
wing.winglet_fraction = 0.0
wing.symmetric = True
# add to vehicle
vehicle.append_component(wing)
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 11.37706641
wing.sweeps.quarter_chord = 0.0
wing.thickness_to_chord = 0.18
wing.taper = 1.
wing.spans.projected = 6.65
wing.chords.root = 0.95
wing.total_length = 0.95
wing.chords.tip = 0.95
wing.chords.mean_aerodynamic = 0.95
wing.dihedral = 0.0
wing.areas.reference = 6.31
wing.areas.wetted = 12.635
wing.areas.exposed = 12.635
wing.twists.root = 0.
wing.twists.tip = 0.
wing.origin = [[5.138, 0.0, 1.54]]
wing.aerodynamic_center = [0., 0., 0.]
wing.winglet_fraction = 0.0
wing.symmetric = True
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------
# FUSELAGE
# ------------------------------------------------------
# FUSELAGE PROPERTIES
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.seats_abreast = 0.
fuselage.seat_pitch = 1.
fuselage.fineness.nose = 1.5
fuselage.fineness.tail = 4.0
fuselage.lengths.nose = 1.7
fuselage.lengths.tail = 2.7
fuselage.lengths.cabin = 1.7
fuselage.lengths.total = 6.1
fuselage.width = 1.15
fuselage.heights.maximum = 1.7
fuselage.heights.at_quarter_length = 1.2
fuselage.heights.at_wing_root_quarter_chord = 1.7
fuselage.heights.at_three_quarters_length = 0.75
fuselage.areas.wetted = 12.97989862
fuselage.areas.front_projected = 1.365211404
fuselage.effective_diameter = 1.318423736
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.
segment.height = 0.09
segment.width = 0.23473
segment.length = 0.
segment.effective_diameter = 0.
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Fuselages.Segment()
segment.tag = 'segment_2'
segment.origin = [0.97675, 0., 0.21977]
segment.percent_x_location = 0.97675 / 6.1
segment.percent_z_location = 0.21977 / 1.19622
segment.height = 0.9027
segment.width = 1.01709
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Fuselages.Segment()
segment.tag = 'segment_3'
segment.origin = [1.93556, 0., 0.39371]
segment.percent_x_location = 1.93556 / 6.1
segment.percent_z_location = 0.39371 / 1.19622
segment.height = 1.30558
segment.width = 1.38871
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Fuselages.Segment()
segment.tag = 'segment_4'
segment.origin = [3.44137, 0., 0.57143]
segment.percent_x_location = 3.44137 / 6.1
segment.percent_z_location = 0.57143 / 1.19622
segment.height = 1.52588
segment.width = 1.47074
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Fuselages.Segment()
segment.tag = 'segment_5'
segment.origin = [4.61031, 0., 0.81577]
segment.percent_x_location = 4.61031 / 6.1
segment.percent_z_location = 0.81577 / 1.19622
segment.height = 1.14788
segment.width = 1.11463
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Fuselages.Segment()
segment.tag = 'segment_6'
segment.origin = [6.1, 0., 1.19622]
segment.percent_x_location = 1.
segment.percent_z_location = 1.
segment.height = 0.31818
segment.width = 0.23443
fuselage.Segments.append(segment)
# add to vehicle
vehicle.append_component(fuselage)
#------------------------------------------------------------------
# PROPULSOR
#------------------------------------------------------------------
net = Vectored_Thrust()
net.number_of_engines = 8
net.thrust_angle = 90.0 * Units.degrees # conversion to radians,
net.nacelle_diameter = 0.2921 # https://www.magicall.biz/products/integrated-motor-controller-magidrive/
net.engine_length = 0.106
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 = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95
net.esc = 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(
)
bat.specific_energy = 300. * Units.Wh / Units.kg
bat.resistance = 0.005
bat.max_voltage = net.voltage
bat.mass_properties.mass = 350. * Units.kg
initialize_from_mass(bat, bat.mass_properties.mass)
net.battery = bat
#------------------------------------------------------------------
# Design Rotors
#------------------------------------------------------------------
# atmosphere conditions
speed_of_sound = 340
rho = 1.22
fligth_CL = 0.75
AR = vehicle.wings.main_wing.aspect_ratio
Cd0 = 0.06
Cdi = fligth_CL**2 / (np.pi * AR * 0.98)
Cd = Cd0 + Cdi
# Create propeller geometry
rot = SUAVE.Components.Energy.Converters.Rotor()
rot.y_pitch = 1.850
rot.tip_radius = 0.8875
rot.hub_radius = 0.1
rot.disc_area = np.pi * (rot.tip_radius**2)
rot.design_tip_mach = 0.5
rot.number_blades = 3
rot.freestream_velocity = 10
rot.angular_velocity = rot.design_tip_mach * speed_of_sound / rot.tip_radius
rot.design_Cl = 0.7
rot.design_altitude = 500 * Units.feet
Lift = vehicle.mass_properties.takeoff * 9.81
rot.design_thrust = (Lift * 1.5) / net.number_of_engines
rot.induced_hover_velocity = np.sqrt(
Lift / (2 * rho * rot.disc_area * net.number_of_engines))
rot = propeller_design(rot)
rot.rotation = [1, 1, 1, 1, 1, 1, 1, 1]
# Front Rotors Locations
rot_front = Data()
rot_front.origin = [[0.0, 1.347, 0.5]]
rot_front.symmetric = True
rot_front.x_pitch_count = 1
rot_front.y_pitch_count = 2
rot_front.y_pitch = 1.85
# populating rotors on one side of wing
if rot_front.y_pitch_count > 1:
for n in range(rot_front.y_pitch_count):
if n == 0:
continue
for i in range(len(rot_front.origin)):
propeller_origin = [
rot_front.origin[i][0],
rot_front.origin[i][1] + n * rot_front.y_pitch,
rot_front.origin[i][2]
]
rot_front.origin.append(propeller_origin)
# populating rotors on the other side of the vehicle
if rot_front.symmetric:
for n in range(len(rot_front.origin)):
propeller_origin = [
rot_front.origin[n][0], -rot_front.origin[n][1],
rot_front.origin[n][2]
]
rot_front.origin.append(propeller_origin)
# Rear Rotors Locations
rot_rear = Data()
rot_rear.origin = [[5.138, 1.347, 1.54]]
rot_rear.symmetric = True
rot_rear.x_pitch_count = 1
rot_rear.y_pitch_count = 2
rot_rear.y_pitch = 1.85
# populating rotors on one side of wing
if rot_rear.y_pitch_count > 1:
for n in range(rot_rear.y_pitch_count):
if n == 0:
continue
for i in range(len(rot_rear.origin)):
propeller_origin = [
rot_rear.origin[i][0],
rot_rear.origin[i][1] + n * rot_rear.y_pitch,
rot_rear.origin[i][2]
]
rot_rear.origin.append(propeller_origin)
# populating rotors on the other side of the vehicle
if rot_rear.symmetric:
for n in range(len(rot_rear.origin)):
propeller_origin = [
rot_rear.origin[n][0], -rot_rear.origin[n][1],
rot_rear.origin[n][2]
]
rot_rear.origin.append(propeller_origin)
# Assign all rotors (front and rear) to network
rot.origin = rot_front.origin + rot_rear.origin
# append rotors to vehicle
net.rotor = rot
# Motor
#------------------------------------------------------------------
# Design Motors
#------------------------------------------------------------------
# Propeller (Thrust) motor
motor = SUAVE.Components.Energy.Converters.Motor()
motor.mass_properties.mass = 9. * Units.kg
motor.origin = rot_front.origin + rot_rear.origin
motor.efficiency = 0.935
motor.gear_ratio = 1.
motor.gearbox_efficiency = 1. # Gear box efficiency
motor.nominal_voltage = bat.max_voltage * 3 / 4
motor.propeller_radius = rot.tip_radius
motor.no_load_current = 2.0
motor = size_optimal_motor(motor, rot)
net.motor = motor
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
# append motor origin spanwise locations onto wing data structure
motor_origins_front = np.array(rot_front.origin)
vehicle.wings['canard_wing'].motor_spanwise_locations = np.multiply(
0.19, motor_origins_front[:, 1])
motor_origins_rear = np.array(rot_rear.origin)
vehicle.wings['main_wing'].motor_spanwise_locations = np.multiply(
0.19, motor_origins_rear[:, 1])
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.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 main():
'''This script checks the functions in in Motor.py used to compute motor torques
and output voltage and currents'''
# Propeller
prop = SUAVE.Components.Energy.Converters.Propeller()
prop.number_blades = 2.0
prop.freestream_velocity = 50.0
prop.angular_velocity = 209.43951023931953
prop.tip_radius = 1.5
prop.hub_radius = 0.05
prop.design_Cl = 0.7
prop.design_altitude = 0.0 * Units.km
prop.design_thrust = 2271.2220451593753
prop = propeller_design(prop)
# Motor
#------------------------------------------------------------------
# Design Motors
#------------------------------------------------------------------
# Propeller (Thrust) motor
motor = SUAVE.Components.Energy.Converters.Motor()
motor.mass_properties.mass = 9. * Units.kg
motor.efficiency = 0.935
motor.gear_ratio = 1.
motor.gearbox_efficiency = 1. # Gear box efficiency
motor.no_load_current = 2.0
motor.propeller_radius = prop.tip_radius
motor.nominal_voltage = 400
motor = size_optimal_motor(motor, prop)
# Propeller (Thrust) motor
motor_low_fid = SUAVE.Components.Energy.Converters.Motor_Lo_Fid()
motor_low_fid.motor_efficiency = 0.98
motor_low_fid.rated_power = 1000
motor_low_fid.rated_voltage = 200
motor_low_fid.mass_properties.mass = 9. * Units.kg
size_from_mass(motor_low_fid)
# Find the operating conditions
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmosphere_conditions = atmosphere.compute_values(prop.design_altitude)
V = prop.freestream_velocity
conditions = Data()
conditions.freestream = Data()
conditions.propulsion = Data()
conditions.frames = Data()
conditions.frames.body = Data()
conditions.frames.inertial = Data()
conditions.freestream.update(atmosphere_conditions)
conditions.freestream.dynamic_viscosity = atmosphere_conditions.dynamic_viscosity
conditions.freestream.velocity = np.array([[V, 0, 0]])
conditions.propulsion.throttle = np.array([[1.0]])
conditions.frames.body.transform_to_inertial = np.array([np.eye(3)])
conditions.propulsion.propeller_power_coefficient = np.array([[0.02]])
#------------------------------------
# Motor Omega Function
#------------------------------------
# create copy of motor to test functions
motor_1 = motor
# Define function specific inputs
voltage_1 = 400
motor_1.inputs.voltage = np.array([[voltage_1]])
# Run Motor Omega Function
omega_1 = motor_1.omega(conditions)
torque_1 = motor_1.outputs.torque[0][0]
#------------------------------------
# Motor Current Function
#------------------------------------
# create copy of motor to test functions
motor_2 = motor
# Define function specific inputs
motor_2.inputs.voltage = np.array([[voltage_1]])
motor_2.outputs.omega = np.array([[prop.angular_velocity]])
# Run Motor Current Function
i, etam = motor_2.current(conditions)
current_2 = i[0][0]
#------------------------------------
# Motor Torque Function
#------------------------------------
# create copy of motor to test functions
motor_3 = motor
# Define function specific inputs
motor_3.inputs.voltage = np.array([[voltage_1]])
motor_3.inputs.omega = np.array([[prop.angular_velocity]])
# Run Motor Torque Function
motor_3.torque(conditions)
torque_3 = motor_3.outputs.torque[0][0]
#------------------------------------
# Motor Voltage-Current Function
#------------------------------------
# create copy of motor to test functions
motor_4 = motor
# Define function specific inputs
motor_4.inputs.torque = np.array([[torque_1]])
# Run Motor Voltage-Current Function
motor_4.voltage_current(conditions)
voltage_4 = motor_4.outputs.voltage[0][0]
current_4 = motor_4.outputs.current[0][0]
#------------------------------------
# Low Fidelity Motor
#------------------------------------
motor_low_fid.inputs.voltage = np.array([[voltage_1]])
p, i = motor_low_fid.power_lo(conditions)
power_out = p[0][0]
current = i[0][0]
# Truth values
omega_1_truth = 209.32373481
torque_1_truth = 1051.64631117327
current_2_truth = 332.1671891793585
torque_3_truth = 630.0492434009769
voltage_4_truth = 400.22093117369883
current_4_truth = 553.0983628781883
power_out_truth = 1960.0
error = Data()
error.omega_test = np.max(np.abs(omega_1_truth - omega_1[0]))
error.torque_test_1 = np.max(np.abs(torque_1_truth - torque_1))
error.current_test_1 = np.max(np.abs(current_2_truth - current_2))
error.torque_test_2 = np.max(np.abs(torque_3_truth - torque_3))
error.voltage_test = np.max(np.abs(voltage_4_truth - voltage_4))
error.current_test_2 = np.max(np.abs(current_4_truth - current_4))
error.power_out_test = np.max(np.abs(power_out_truth - power_out))
print('Errors:')
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1e-6)
return
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'multicopter'
vehicle.configuration = 'eVTOL'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 2080. * Units.lb
vehicle.mass_properties.operating_empty = 1666. * Units.lb
vehicle.mass_properties.max_takeoff = 2080. * Units.lb
vehicle.mass_properties.center_of_gravity = [2.6, 0., 0.]
# This needs updating
vehicle.passengers = 5
vehicle.reference_area = 73 * Units.feet**2
vehicle.envelope.ultimate_load = 5.7
vehicle.envelope.limit_load = 3.
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 1
wing.spans.projected = 0.01
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 = 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.append_segment(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.append_segment(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.append_segment(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.append_segment(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.append_segment(segment)
# add to vehicle
vehicle.append_component(fuselage)
#------------------------------------------------------------------
# PROPULSOR
#------------------------------------------------------------------
net = Vectored_Thrust()
net.number_of_engines = 6
net.thrust_angle = 90. * Units.degrees
net.nacelle_diameter = 0.6 * Units.feet # need to check
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 = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95
net.esc = 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(
)
bat.specific_energy = 350. * 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
#------------------------------------------------------------------
# atmosphere and flight conditions for propeller/rotor design
g = 9.81 # gravitational acceleration
speed_of_sound = 340 # speed of sound
rho = 1.22 # reference density
Hover_Load = vehicle.mass_properties.takeoff * g # hover load
design_tip_mach = 0.7 # design tip mach number
rotor = SUAVE.Components.Energy.Converters.Rotor()
rotor.tip_radius = 3.95 * Units.feet
rotor.hub_radius = 0.6 * Units.feet
rotor.disc_area = np.pi * (rotor.tip_radius**2)
rotor.number_blades = 3
rotor.freestream_velocity = 500. * Units['ft/min']
rotor.angular_velocity = (design_tip_mach *
speed_of_sound) / rotor.tip_radius
rotor.design_Cl = 0.8
rotor.design_altitude = 1000 * Units.feet
rotor.design_thrust = (Hover_Load / net.number_of_engines) * 2.
rotor = propeller_design(rotor)
rotor.induced_hover_velocity = np.sqrt(
Hover_Load / (2 * rho * rotor.disc_area * net.number_of_engines))
# propulating propellers on the other side of the vehicle
rotor.origin = []
for fuselage in vehicle.fuselages:
if fuselage.tag == 'fuselage':
continue
else:
rotor.origin.append(fuselage.origin[0])
# append propellers to vehicle
net.rotor = rotor
#------------------------------------------------------------------
# Design Motors
#------------------------------------------------------------------
# Motor
motor = SUAVE.Components.Energy.Converters.Motor()
motor.efficiency = 0.95
motor.nominal_voltage = bat.max_voltage
motor.mass_properties.mass = 3. * Units.kg
motor.origin = rotor.origin
motor.propeller_radius = rotor.tip_radius
motor.gear_ratio = 1.0
motor.gearbox_efficiency = 1.0
motor.no_load_current = 4.0
motor = size_optimal_motor(motor, rotor)
net.motor = motor
# Define motor sizing parameters
max_power = rotor.design_power * 1.2
max_torque = rotor.design_torque * 1.2
# test high temperature superconducting motor weight function
mass = hts_motor(max_power)
# test NDARC motor weight function
mass = nasa_motor(max_torque)
# test air cooled motor weight function
mass = air_cooled_motor(max_power)
motor.mass_properties.mass = mass
net.motor = motor
vehicle.append_component(net)
vehicle.weight_breakdown = empty(vehicle, None)
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'multicopter'
vehicle.configuration = 'eVTOL'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 2080. * Units.lb
vehicle.mass_properties.operating_empty = 1666. * Units.lb
vehicle.mass_properties.max_takeoff = 2080. * Units.lb
vehicle.mass_properties.center_of_gravity = [[2.6, 0., 0.]]
# This needs updating
vehicle.passengers = 5
vehicle.reference_area = 73 * Units.feet**2
vehicle.envelope.ultimate_load = 5.7
vehicle.envelope.limit_load = 3.
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 1.
wing.spans.projected = 0.1
wing.chords.root = 0.1
wing.chords.tip = 0.1
wing.origin = [[2.6, 0., 0.]]
wing.symbolic = True
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 = 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.Lofted_Body_Segment.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.append_segment(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.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.append_segment(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.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.append_segment(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.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.append_segment(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.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.append_segment(segment)
# add to vehicle
vehicle.append_component(fuselage)
# -----------------------------------------------------------------
# Design the Nacelle
# -----------------------------------------------------------------
nacelle = SUAVE.Components.Nacelles.Nacelle()
nacelle.diameter = 0.6 * Units.feet # need to check
nacelle.length = 0.5 * Units.feet
nacelle.tag = 'nacelle_1'
nacelle.areas.wetted = np.pi * nacelle.diameter * nacelle.length + 0.5 * np.pi * nacelle.diameter**2
nacelle.origin = [[0., 2., 1.4]]
vehicle.append_component(nacelle)
nacelle_2 = deepcopy(nacelle)
nacelle_2.tag = 'nacelle_2'
nacelle_2.origin = [[0.0, -2., 1.4]]
vehicle.append_component(nacelle_2)
nacelle_3 = deepcopy(nacelle)
nacelle_3.tag = 'nacelle_3'
nacelle_3.origin = [[2.5, 4., 1.4]]
vehicle.append_component(nacelle_3)
nacelle_4 = deepcopy(nacelle)
nacelle_4.tag = 'nacelle_4'
nacelle_4.origin = [[2.5, -4., 1.4]]
vehicle.append_component(nacelle_4)
nacelle_5 = deepcopy(nacelle)
nacelle_5.tag = 'nacelle_5'
nacelle_5.origin = [[5.0, 2., 1.4]]
vehicle.append_component(nacelle_5)
nacelle_6 = deepcopy(nacelle)
nacelle_6.tag = 'nacelle_6'
nacelle_6.origin = [[5.0, -2., 1.4]]
vehicle.append_component(nacelle_6)
#------------------------------------------------------------------
# Network
#------------------------------------------------------------------
net = SUAVE.Components.Energy.Networks.Battery_Propeller()
net.number_of_lift_rotor_engines = 6
net.nacelle_diameter = 0.6 * Units.feet # need to check
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.
net.identical_lift_rotors = True
#------------------------------------------------------------------
# Design Electronic Speed Controller
#------------------------------------------------------------------
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95
net.esc = 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 = 300. * Units.kg
bat.max_voltage = net.voltage
initialize_from_mass(bat)
net.battery = bat
#------------------------------------------------------------------
# Design Rotors
#------------------------------------------------------------------
# atmosphere and flight conditions for propeller/lift_rotor design
g = 9.81 # gravitational acceleration
speed_of_sound = 340 # speed of sound
Hover_Load = vehicle.mass_properties.takeoff * g # hover load
design_tip_mach = 0.7 # design tip mach number
lift_rotor = SUAVE.Components.Energy.Converters.Lift_Rotor()
lift_rotor.tip_radius = 3.95 * Units.feet
lift_rotor.hub_radius = 0.6 * Units.feet
lift_rotor.disc_area = np.pi * (lift_rotor.tip_radius**2)
lift_rotor.number_of_blades = 3
lift_rotor.freestream_velocity = 10.0
lift_rotor.angular_velocity = (design_tip_mach *
speed_of_sound) / lift_rotor.tip_radius
lift_rotor.design_Cl = 0.7
lift_rotor.design_altitude = 1000 * Units.feet
lift_rotor.design_thrust = Hover_Load / (
net.number_of_lift_rotor_engines - 1
) # contingency for one-engine-inoperative condition
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
origins = [[0., 2., 1.4], [0.0, -2., 1.4], [2.5, 4., 1.4], [2.5, -4., 1.4],
[5.0, 2., 1.4], [5.0, -2., 1.4]]
for ii in range(6):
lift_rotor = deepcopy(lift_rotor)
lift_rotor.tag = 'lift_rotor'
lift_rotor.origin = [origins[ii]]
net.lift_rotors.append(lift_rotor)
#------------------------------------------------------------------
# Design Motors
#------------------------------------------------------------------
# Motor
lift_motor = SUAVE.Components.Energy.Converters.Motor()
lift_motor.efficiency = 0.95
lift_motor.nominal_voltage = bat.max_voltage * 0.5
lift_motor.mass_properties.mass = 3. * Units.kg
lift_motor.origin = lift_rotor.origin
lift_motor.propeller_radius = lift_rotor.tip_radius
lift_motor.no_load_current = 2.0
lift_motor = size_optimal_motor(lift_motor, lift_rotor)
net.lift_motor = lift_motor
# Define motor sizing parameters
max_power = lift_rotor.design_power * 1.2
max_torque = lift_rotor.design_torque * 1.2
# test high temperature superconducting motor weight function
mass = hts_motor(max_power)
# test NDARC motor weight function
mass = nasa_motor(max_torque)
# test air cooled motor weight function
mass = air_cooled_motor(max_power)
lift_motor.mass_properties.mass = mass
# Appending motors with different origins
for ii in range(6):
lift_rotor_motor = deepcopy(lift_motor)
lift_rotor_motor.tag = 'motor'
net.lift_rotor_motors.append(lift_rotor_motor)
vehicle.append_component(net)
vehicle.weight_breakdown = empty(vehicle)
compute_component_centers_of_gravity(vehicle)
vehicle.center_of_gravity()
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Tiltwing'
vehicle.configuration = 'eVTOL'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 2250. * Units.lb
vehicle.mass_properties.operating_empty = 2250. * Units.lb
vehicle.mass_properties.max_takeoff = 2250. * Units.lb
vehicle.mass_properties.center_of_gravity = [[ 2.0144, 0. , 0.]]
vehicle.passengers = 1
vehicle.reference_area = 10.58275476
vehicle.envelope.ultimate_load = 5.7
vehicle.envelope.limit_load = 3.
# ------------------------------------------------------
# WINGS
# ------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'canard_wing'
wing.aspect_ratio = 11.37706641
wing.sweeps.quarter_chord = 0.0
wing.thickness_to_chord = 0.18
wing.taper = 1.
wing.spans.projected = 6.65
wing.chords.root = 0.95
wing.total_length = 0.95
wing.chords.tip = 0.95
wing.chords.mean_aerodynamic = 0.95
wing.dihedral = 0.0
wing.areas.reference = 6.31
wing.areas.wetted = 12.635
wing.areas.exposed = 12.635
wing.twists.root = 0.
wing.twists.tip = 0.
wing.origin = [[0.1, 0.0 , 0.0]]
wing.aerodynamic_center = [0.3, 0.0 , 0.0]
wing.winglet_fraction = 0.0
wing.symmetric = True
# add to vehicle
vehicle.append_component(wing)
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = 11.37706641
wing.sweeps.quarter_chord = 0.0
wing.thickness_to_chord = 0.18
wing.taper = 1.
wing.spans.projected = 6.65
wing.chords.root = 0.95
wing.total_length = 0.95
wing.chords.tip = 0.95
wing.chords.mean_aerodynamic = 0.95
wing.dihedral = 0.0
wing.areas.reference = 6.31
wing.areas.wetted = 12.635
wing.areas.exposed = 12.635
wing.twists.root = 0.
wing.twists.tip = 0.
wing.origin = [[ 5.138, 0.0 , 1.323 ]] # for images 1.54
wing.aerodynamic_center = [ 5.3, 0.0 , 1.323 ]
wing.winglet_fraction = 0.0
wing.symmetric = True
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------
# FUSELAGE
# ------------------------------------------------------
# FUSELAGE PROPERTIES
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.seats_abreast = 0.
fuselage.seat_pitch = 1.
fuselage.fineness.nose = 1.5
fuselage.fineness.tail = 4.0
fuselage.lengths.nose = 1.7
fuselage.lengths.tail = 2.7
fuselage.lengths.cabin = 1.7
fuselage.lengths.total = 6.1
fuselage.width = 1.15
fuselage.heights.maximum = 1.7
fuselage.heights.at_quarter_length = 1.2
fuselage.heights.at_wing_root_quarter_chord = 1.7
fuselage.heights.at_three_quarters_length = 0.75
fuselage.areas.wetted = 12.97989862
fuselage.areas.front_projected = 1.365211404
fuselage.effective_diameter = 1.318423736
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.
segment.height = 0.09
segment.width = 0.23473
segment.length = 0.
segment.effective_diameter = 0.
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_1'
segment.percent_x_location = 0.97675/6.1
segment.percent_z_location = 0.21977/6.1
segment.height = 0.9027
segment.width = 1.01709
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_2'
segment.percent_x_location = 1.93556/6.1
segment.percent_z_location = 0.39371/6.1
segment.height = 1.30558
segment.width = 1.38871
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_3'
segment.percent_x_location = 3.44137/6.1
segment.percent_z_location = 0.57143/6.1
segment.height = 1.52588
segment.width = 1.47074
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_4'
segment.percent_x_location = 4.61031/6.1
segment.percent_z_location = 0.81577/6.1
segment.height = 1.14788
segment.width = 1.11463
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 = 1.19622/6.1
segment.height = 0.31818
segment.width = 0.23443
fuselage.Segments.append(segment)
# add to vehicle
vehicle.append_component(fuselage)
#------------------------------------------------------------------
# network
#------------------------------------------------------------------
net = SUAVE.Components.Energy.Networks.Battery_Propeller()
net.number_of_propeller_engines = 8
net.thrust_angle = 0.0 * Units.degrees # conversion to radians,
net.nacelle_diameter = 0.2921 # https://www.magicall.biz/products/integrated-motor-controller-magidrive/
net.engine_length = 0.95
net.areas = Data()
net.areas.wetted = np.pi*net.nacelle_diameter*net.engine_length + 0.5*np.pi*net.nacelle_diameter**2
net.voltage = 400.
net.identical_propellers = True
#------------------------------------------------------------------
# Design Electronic Speed Controller
#------------------------------------------------------------------
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95
net.esc = esc
# Component 6 the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 10. #Watts
payload.mass_properties.mass = 0.0 * Units.kg
net.payload = payload
# Component 7 the Avionics
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 20. #Watts
net.avionics = avionics
#------------------------------------------------------------------
# Design Battery
#------------------------------------------------------------------
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion_LiNiMnCoO2_18650()
bat.mass_properties.mass = 200. * 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
# Component 9 Miscellaneous Systems
sys = SUAVE.Components.Systems.System()
sys.mass_properties.mass = 5 # kg
#------------------------------------------------------------------
# Nacelles
#------------------------------------------------------------------
nacelle = SUAVE.Components.Nacelles.Nacelle()
nacelle.diameter = 0.2921
nacelle.length = 0.95
nacelle_origins = [[-0.2, 1.347, 0.0], [-0.2, 3.2969999999999997, 0.0],
[-0.2, -1.347, 0.0], [-0.2, -3.2969999999999997, 0.0],
[4.938, 1.347, 1.54], [4.938, 3.2969999999999997, 1.54],
[4.938, -1.347, 1.54], [4.938, -3.2969999999999997, 1.54]]
nacelle.areas.wetted = np.pi*nacelle.diameter*nacelle.length + 0.5*np.pi*nacelle.diameter**2
for idx in range(8):
nacelle = deepcopy(nacelle)
nacelle.tag = 'nacelle_' + str(idx)
nacelle.origin = [nacelle_origins[idx]]
vehicle.append_component(nacelle)
#------------------------------------------------------------------
# Design Rotors
#------------------------------------------------------------------
# atmosphere conditions
speed_of_sound = 340
# Create propeller geometry
prop = SUAVE.Components.Energy.Converters.Propeller() # This is truly a prop because the default of the mission is pointing forward
prop.tip_radius = 0.8875
prop.hub_radius = 0.15
prop.disc_area = np.pi*(prop.tip_radius**2)
prop.design_tip_mach = 0.5
prop.number_of_blades = 3
prop.freestream_velocity = 10
prop.angular_velocity = prop.design_tip_mach*speed_of_sound/prop.tip_radius
prop.design_Cl = 0.7
prop.design_altitude = 500 * Units.feet
Hover_Load = vehicle.mass_properties.takeoff*9.81
prop.design_thrust = Hover_Load/(net.number_of_propeller_engines-1) # contingency for one-engine-inoperative condition
prop.airfoil_geometry = ['../Vehicles/Airfoils/NACA_4412.txt']
prop.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' ]]
prop.airfoil_polar_stations = [0,0,0,0,0,0,0,0,0,0,0,0,0,0,0,0,0,0,0,0]
prop = propeller_design(prop)
prop.rotation = 1
# Front Rotors Locations
origins = [[-0.2, 1.347, 0.0], [-0.2, 3.2969999999999997, 0.0], [-0.2, -1.347, 0.0], [-0.2, -3.2969999999999997, 0.0],\
[4.938, 1.347, 1.54], [4.938, 3.2969999999999997, 1.54], [4.938, -1.347, 1.54], [4.938, -3.2969999999999997, 1.54]]
for ii in range(8):
rotor = deepcopy(prop)
rotor.tag = 'propeller'
rotor.origin = [origins[ii]]
net.propellers.append(rotor)
# Motor
#------------------------------------------------------------------
# Design Motors
#------------------------------------------------------------------
# Propeller (Thrust) motor
motor = SUAVE.Components.Energy.Converters.Motor()
motor.efficiency = 0.9
motor.nominal_voltage = bat.max_voltage *3/4
motor.propeller_radius = prop.tip_radius
motor.no_load_current = 2.0
motor = size_optimal_motor(motor,prop)
motor.mass_properties.mass = nasa_motor(motor.design_torque)
net.motor = motor
for ii in range(8):
rotor_motor = deepcopy(motor)
rotor_motor.tag = 'motor'
rotor_motor.origin = [origins[ii]]
net.propeller_motors.append(rotor_motor)
# 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
# append motor origin spanwise locations onto wing data structure
motor_origins_front = np.array(origins[:4])
motor_origins_rear = np.array(origins[5:])
vehicle.wings['canard_wing'].motor_spanwise_locations = motor_origins_front[:,1]/ vehicle.wings['canard_wing'].spans.projected
vehicle.wings['canard_wing'].motor_spanwise_locations = motor_origins_front[:,1]/ vehicle.wings['canard_wing'].spans.projected
vehicle.wings['main_wing'].motor_spanwise_locations = motor_origins_rear[:,1]/ vehicle.wings['main_wing'].spans.projected
vehicle.append_component(net)
vehicle.weight_breakdown = empty(vehicle)
compute_component_centers_of_gravity(vehicle)
vehicle.center_of_gravity()
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'X57_Maxwell_Mod2'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 2550. * Units.pounds
vehicle.mass_properties.takeoff = 2550. * Units.pounds
vehicle.mass_properties.max_zero_fuel = 2550. * Units.pounds
vehicle.envelope.ultimate_load = 5.7
vehicle.envelope.limit_load = 3.8
vehicle.reference_area = 14.76
vehicle.passengers = 4
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "commuter"
cruise_speed = 135. * Units['mph']
altitude = 2500. * Units.ft
atmo = SUAVE.Analyses.Atmospheric.US_Standard_1976()
freestream = atmo.compute_values(0.)
freestream0 = atmo.compute_values(altitude)
mach_number = (cruise_speed / freestream.speed_of_sound)[0][0]
vehicle.design_dynamic_pressure = (.5 * freestream0.density *
(cruise_speed * cruise_speed))[0][0]
vehicle.design_mach_number = mach_number
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.sweeps.quarter_chord = 0.0 * Units.deg
wing.thickness_to_chord = 0.12
wing.areas.reference = 14.76
wing.spans.projected = 11.4
wing.chords.root = 1.46
wing.chords.tip = 0.92
wing.chords.mean_aerodynamic = 1.19
wing.taper = wing.chords.root / wing.chords.tip
wing.aspect_ratio = wing.spans.projected**2. / wing.areas.reference
wing.twists.root = 3.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[2.93, 0., 1.01]]
wing.aerodynamic_center = [3., 0., 1.01]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.winglet_fraction = 0.0
wing.dynamic_pressure_ratio = 1.0
airfoil = SUAVE.Components.Airfoils.Airfoil()
airfoil.coordinate_file = '../Vehicles/Airfoils/NACA_63_412.txt'
cg_x = wing.origin[0][0] + 0.25 * wing.chords.mean_aerodynamic
cg_z = wing.origin[0][2] - 0.2 * wing.chords.mean_aerodynamic
vehicle.mass_properties.center_of_gravity = [
[cg_x, 0., cg_z]
] # SOURCE: Design and aerodynamic analysis of a twin-engine commuter aircraft
# Wing Segments
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'inboard'
segment.percent_span_location = 0.0
segment.twist = 3. * Units.degrees
segment.root_chord_percent = 1.
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 0.
segment.thickness_to_chord = 0.12
segment.append_airfoil(airfoil)
wing.append_segment(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'outboard'
segment.percent_span_location = 0.5438
segment.twist = 2. * Units.degrees
segment.root_chord_percent = 1.
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 0.
segment.thickness_to_chord = 0.12
segment.append_airfoil(airfoil)
wing.append_segment(segment)
# Wing Segments
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'winglet'
segment.percent_span_location = 0.98
segment.twist = 1. * Units.degrees
segment.root_chord_percent = 0.630
segment.dihedral_outboard = 75. * Units.degrees
segment.sweeps.quarter_chord = 82. * Units.degrees
segment.thickness_to_chord = 0.12
segment.append_airfoil(airfoil)
wing.append_segment(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'tip'
segment.percent_span_location = 1.
segment.twist = 0. * Units.degrees
segment.root_chord_percent = 0.12
segment.dihedral_outboard = 0.
segment.sweeps.quarter_chord = 0.
segment.thickness_to_chord = 0.12
segment.append_airfoil(airfoil)
wing.append_segment(segment)
# Fill out more segment properties automatically
wing = segment_properties(wing)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.sweeps.quarter_chord = 0.0 * Units.deg
wing.thickness_to_chord = 0.12
wing.areas.reference = 2.540
wing.spans.projected = 3.3 * Units.meter
wing.sweeps.quarter_chord = 0 * Units.deg
wing.chords.root = 0.769 * Units.meter
wing.chords.tip = 0.769 * Units.meter
wing.chords.mean_aerodynamic = 0.769 * Units.meter
wing.taper = 1.
wing.aspect_ratio = wing.spans.projected**2. / wing.areas.reference
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[7.7, 0., 0.25]]
wing.aerodynamic_center = [7.8, 0., 0.25]
wing.vertical = False
wing.winglet_fraction = 0.0
wing.symmetric = True
wing.high_lift = False
wing.dynamic_pressure_ratio = 0.9
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.sweeps.quarter_chord = 25. * Units.deg
wing.thickness_to_chord = 0.12
wing.areas.reference = 2.258 * Units['meters**2']
wing.spans.projected = 1.854 * Units.meter
wing.chords.root = 1.6764 * Units.meter
wing.chords.tip = 0.6858 * Units.meter
wing.chords.mean_aerodynamic = 1.21 * Units.meter
wing.taper = wing.chords.tip / wing.chords.root
wing.aspect_ratio = wing.spans.projected**2. / wing.areas.reference
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[6.75, 0, 0.623]]
wing.aerodynamic_center = [0.508, 0, 0]
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.winglet_fraction = 0.0
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.seats_abreast = 2.
fuselage.fineness.nose = 1.6
fuselage.fineness.tail = 2.
fuselage.lengths.nose = 60. * Units.inches
fuselage.lengths.tail = 161. * Units.inches
fuselage.lengths.cabin = 105. * Units.inches
fuselage.lengths.total = 332.2 * Units.inches
fuselage.lengths.fore_space = 0.
fuselage.lengths.aft_space = 0.
fuselage.width = 42. * Units.inches
fuselage.heights.maximum = 62. * Units.inches
fuselage.heights.at_quarter_length = 62. * Units.inches
fuselage.heights.at_three_quarters_length = 62. * Units.inches
fuselage.heights.at_wing_root_quarter_chord = 23. * Units.inches
fuselage.areas.side_projected = 8000. * Units.inches**2.
fuselage.areas.wetted = 30000. * Units.inches**2.
fuselage.areas.front_projected = 42. * 62. * Units.inches**2.
fuselage.effective_diameter = 50. * Units.inches
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_0'
segment.percent_x_location = 0
segment.percent_z_location = 0
segment.height = 0.01
segment.width = 0.01
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_1'
segment.percent_x_location = 0.007279116466
segment.percent_z_location = 0.002502014453
segment.height = 0.1669064748
segment.width = 0.2780205877
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_2'
segment.percent_x_location = 0.01941097724
segment.percent_z_location = 0.001216095397
segment.height = 0.3129496403
segment.width = 0.4365777215
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_3'
segment.percent_x_location = 0.06308567604
segment.percent_z_location = 0.007395489231
segment.height = 0.5841726619
segment.width = 0.6735119903
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_4'
segment.percent_x_location = 0.1653761217
segment.percent_z_location = 0.02891281352
segment.height = 1.064028777
segment.width = 1.067200529
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_5'
segment.percent_x_location = 0.2426372155
segment.percent_z_location = 0.04214148761
segment.height = 1.293766653
segment.width = 1.183058255
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_6'
segment.percent_x_location = 0.2960174029
segment.percent_z_location = 0.04705241831
segment.height = 1.377026712
segment.width = 1.181540054
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_7'
segment.percent_x_location = 0.3809404284
segment.percent_z_location = 0.05313580461
segment.height = 1.439568345
segment.width = 1.178218989
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_8'
segment.percent_x_location = 0.5046854083
segment.percent_z_location = 0.04655492473
segment.height = 1.29352518
segment.width = 1.054390707
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_9'
segment.percent_x_location = 0.6454149933
segment.percent_z_location = 0.03741966266
segment.height = 0.8971223022
segment.width = 0.8501926505
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_10'
segment.percent_x_location = 0.985107095
segment.percent_z_location = 0.04540283436
segment.height = 0.2920863309
segment.width = 0.2012565415
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_11'
segment.percent_x_location = 1
segment.percent_z_location = 0.04787575562
segment.height = 0.1251798561
segment.width = 0.1206021048
fuselage.Segments.append(segment)
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Nacelles
# ------------------------------------------------------------------
nacelle = SUAVE.Components.Nacelles.Nacelle()
nacelle.tag = 'nacelle_1'
nacelle.length = 2
nacelle.diameter = 42 * Units.inches
nacelle.areas.wetted = 0.01 * (2 * np.pi * 0.01 / 2)
nacelle.origin = [[2.5, 2.5, 1.0]]
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 = 0.0
nac_segment.width = 0.0
nacelle.append_segment(nac_segment)
nac_segment = SUAVE.Components.Lofted_Body_Segment.Segment()
nac_segment.tag = 'segment_2'
nac_segment.percent_x_location = 0.1
nac_segment.height = 0.5
nac_segment.width = 0.65
nacelle.append_segment(nac_segment)
nac_segment = SUAVE.Components.Lofted_Body_Segment.Segment()
nac_segment.tag = 'segment_3'
nac_segment.percent_x_location = 0.3
nac_segment.height = 0.52
nac_segment.width = 0.7
nacelle.append_segment(nac_segment)
nac_segment = SUAVE.Components.Lofted_Body_Segment.Segment()
nac_segment.tag = 'segment_4'
nac_segment.percent_x_location = 0.5
nac_segment.height = 0.5
nac_segment.width = 0.65
nacelle.append_segment(nac_segment)
nac_segment = SUAVE.Components.Lofted_Body_Segment.Segment()
nac_segment.tag = 'segment_5'
nac_segment.percent_x_location = 0.7
nac_segment.height = 0.4
nac_segment.width = 0.6
nacelle.append_segment(nac_segment)
nac_segment = SUAVE.Components.Lofted_Body_Segment.Segment()
nac_segment.tag = 'segment_6'
nac_segment.percent_x_location = 0.9
nac_segment.height = 0.3
nac_segment.width = 0.5
nacelle.append_segment(nac_segment)
nac_segment = SUAVE.Components.Lofted_Body_Segment.Segment()
nac_segment.tag = 'segment_7'
nac_segment.percent_x_location = 1.0
nac_segment.height = 0.0
nac_segment.width = 0.0
nacelle.append_segment(nac_segment)
vehicle.append_component(nacelle)
nacelle_2 = deepcopy(nacelle)
nacelle_2.tag = 'nacelle_2'
nacelle_2.origin = [[2.5, -2.5, 1.0]]
vehicle.append_component(nacelle_2)
#---------------------------------------------------------------------------------------------
# DEFINE PROPELLER
#---------------------------------------------------------------------------------------------
# build network
net = Battery_Propeller()
net.number_of_propeller_engines = 2.
net.identical_propellers = True
# Component 1 the ESC
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95 # Gundlach for brushless motors
net.esc = esc
# Component 2 the Propeller
prop = SUAVE.Components.Energy.Converters.Propeller()
prop.tag = 'propeller_1'
prop.number_of_blades = 2.0
prop.freestream_velocity = 135. * Units['mph']
prop.angular_velocity = 1300. * Units.rpm
prop.tip_radius = 76. / 2. * Units.inches
prop.hub_radius = 8. * Units.inches
prop.design_Cl = 0.8
prop.design_altitude = 12000. * Units.feet
prop.design_altitude = 12000. * Units.feet
prop.design_thrust = 1200.
prop.origin = [[2., 2.5, 0.784]]
prop.rotation = -1
prop.symmetry = True
prop.variable_pitch = True
prop.airfoil_geometry = ['../Vehicles/Airfoils/NACA_4412.txt']
prop.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'
]]
prop.airfoil_polar_stations = [
0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0
]
prop = propeller_design(prop)
prop_left = deepcopy(prop)
prop_left.tag = 'propeller_2'
prop_left.origin = [[2., -2.5, 0.784]]
prop_left.rotation = 1
net.propellers.append(prop)
net.propellers.append(prop_left)
# Component 3 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion_LiNiMnCoO2_18650(
)
bat.mass_properties.mass = 500. * Units.kg
bat.max_voltage = 500.
initialize_from_mass(bat)
net.battery = bat
net.voltage = bat.max_voltage
# Component 4 Miscellaneous Systems
sys = SUAVE.Components.Systems.System()
sys.mass_properties.mass = 5 # kg
# Component 5 the Motor
motor = SUAVE.Components.Energy.Converters.Motor()
motor.efficiency = 0.95
motor.gearbox_efficiency = 1.
motor.origin = [[2., 2.5, 0.784]]
motor.nominal_voltage = bat.max_voltage * 3 / 4
motor.propeller_radius = prop.tip_radius
motor.no_load_current = 4.0
motor = size_optimal_motor(motor, prop)
motor.mass_properties.mass = 10. * Units.kg
# append right motor
net.propeller_motors.append(motor)
# append left motor
motor_left = deepcopy(motor)
motor_left.origin = [[2., -2.5, 0.784]]
net.propeller_motors.append(motor_left)
# Component 6 the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 10. # Watts
payload.mass_properties.mass = 1.0 * Units.kg
net.payload = payload
# Component 7 the Avionics
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 20. # Watts
net.avionics = avionics
# add the solar network to the vehicle
vehicle.append_component(net)
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
return vehicle
def setup_vehicle():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
# Create a vehicle and set level properties
vehicle = SUAVE.Vehicle()
vehicle.tag = 'eVTOL'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 2500. * Units.lb
vehicle.mass_properties.operating_empty = 2150. * Units.lb
vehicle.mass_properties.max_takeoff = 2500. * Units.lb
vehicle.mass_properties.max_payload = 100. * Units.lb
vehicle.mass_properties.center_of_gravity = [[2.0, 0.,
0.]] # I made this up
# basic parameters
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.origin = [[1.5, 0., -0.5]]
wing.spans.projected = 35.0 * Units.feet
wing.chords.root = 3.25 * Units.feet
# Segment
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Root'
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 = 'Tip'
segment.percent_span_location = 1.0
segment.twist = 0.
segment.root_chord_percent = 1.0
segment.dihedral_outboard = 0.0 * 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 = segment_properties(wing)
wing = wing_segmented_planform(wing)
## ALSO SET THE VEHICLE REFERENCE AREA
vehicle.reference_area = wing.areas.reference
# add to vehicle
vehicle.append_component(wing)
# Add a horizontal tail
# WING PROPERTIES
wing = SUAVE.Components.Wings.Horizontal_Tail()
wing.tag = 'horizontal_tail'
wing.areas.reference = 2.0
wing.taper = 0.5
wing.sweeps.quarter_chord = 20. * Units.degrees
wing.aspect_ratio = 5.0
wing.thickness_to_chord = 0.12
wing.dihedral = 5. * Units.degrees
wing.origin = [[5.5, 0.0, 0.65]]
# Fill out more segment properties automatically
wing = wing_planform(wing)
# add to vehicle
vehicle.append_component(wing)
# Add a vertical tail
wing = SUAVE.Components.Wings.Vertical_Tail()
wing.tag = 'vertical_tail'
wing.areas.reference = 1.0
wing.taper = 0.5
wing.sweeps.quarter_chord = 30 * Units.degrees
wing.aspect_ratio = 2.5
wing.thickness_to_chord = 0.12
wing.origin = [[5.5, 0.0, 0.65]]
# Fill out more segment properties automatically
wing = wing_planform(wing)
# add to vehicle
vehicle.append_component(wing)
# Add a fuseelage
# ---------------------------------------------------------------
# FUSELAGE
# ---------------------------------------------------------------
# FUSELAGE PROPERTIES
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.seats_abreast = 2.
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 = 6.0
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 = -0.05
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 = 0.06
segment.percent_z_location = -0.05
segment.height = 0.52
segment.width = 0.75
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_2'
segment.percent_x_location = 0.25
segment.percent_z_location = -.01
segment.height = 1.2
segment.width = 1.43
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_3'
segment.percent_x_location = 0.475
segment.percent_z_location = 0
segment.height = 1.4
segment.width = 1.4
fuselage.Segments.append(segment)
# Segment
segment = SUAVE.Components.Lofted_Body_Segment.Segment()
segment.tag = 'segment_4'
segment.percent_x_location = 0.75
segment.percent_z_location = 0.06
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 = 0.1
segment.height = 0.05
segment.width = 0.05
fuselage.Segments.append(segment)
# add to vehicle
vehicle.append_component(fuselage)
#-------------------------------------------------------------------
# Booms
#-------------------------------------------------------------------
# Add booms for the motors
boom = SUAVE.Components.Fuselages.Fuselage()
boom.tag = 'boom_R'
boom.origin = [[0.525, 3.0, -0.35]]
boom.lengths.nose = 0.2
boom.lengths.tail = 0.2
boom.lengths.total = 4
boom.width = 0.15
boom.heights.maximum = 0.15
boom.heights.at_quarter_length = 0.15
boom.heights.at_three_quarters_length = 0.15
boom.heights.at_wing_root_quarter_chord = 0.15
boom.effective_diameter = 0.15
boom.areas.wetted = 2 * np.pi * (0.075) * 3.5
boom.areas.front_projected = np.pi * 0.15
boom.fineness.nose = 0.15 / 0.2
boom.fineness.tail = 0.15 / 0.2
vehicle.append_component(boom)
# Now attach the mirrored boom
other_boom = deepcopy(boom)
other_boom.origin[0][1] = -boom.origin[0][1]
other_boom.tag = 'boom_L'
vehicle.append_component(other_boom)
#------------------------------------------------------------------
# Network
#------------------------------------------------------------------
net = SUAVE.Components.Energy.Networks.Lift_Cruise()
net.number_of_lift_rotor_engines = 4
net.number_of_propeller_engines = 1
net.identical_propellers = True
net.identical_lift_rotors = True
net.voltage = 400.
#------------------------------------------------------------------
# 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
#------------------------------------------------------------------
# Payload
#------------------------------------------------------------------
payload = SUAVE.Components.Energy.Peripherals.Avionics()
payload.power_draw = 0.
net.payload = payload
#------------------------------------------------------------------
# Avionics
#------------------------------------------------------------------
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 300. * Units.watts
net.avionics = avionics
#------------------------------------------------------------------
# Design Battery
#------------------------------------------------------------------
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion_LiNiMnCoO2_18650(
)
bat.mass_properties.mass = 1000. * Units.lb
bat.max_voltage = net.voltage
initialize_from_mass(bat)
net.battery = bat
#------------------------------------------------------------------
# Design Rotors and Propellers
#------------------------------------------------------------------
# The tractor propeller
propeller = SUAVE.Components.Energy.Converters.Propeller()
propeller.origin = [[0, 0, -0.325]]
propeller.number_of_blades = 3
propeller.tip_radius = 0.9
propeller.hub_radius = 0.1
propeller.angular_velocity = 2200 * Units.rpm
propeller.freestream_velocity = 100. * Units.knots
propeller.design_Cl = 0.7
propeller.design_altitude = 5000. * Units.feet
propeller.design_thrust = 500. * Units.lbf
propeller.airfoil_geometry = ['./Airfoils/NACA_4412.txt']
propeller.airfoil_polars = [[
'./Airfoils/Polars/NACA_4412_polar_Re_50000.txt',
'./Airfoils/Polars/NACA_4412_polar_Re_100000.txt',
'./Airfoils/Polars/NACA_4412_polar_Re_200000.txt',
'./Airfoils/Polars/NACA_4412_polar_Re_500000.txt',
'./Airfoils/Polars/NACA_4412_polar_Re_1000000.txt'
]]
propeller.airfoil_polar_stations = np.zeros((20), dtype=np.int8).tolist()
propeller = propeller_design(propeller)
net.propellers.append(propeller)
# The lift rotors
lift_rotor = SUAVE.Components.Energy.Converters.Lift_Rotor()
lift_rotor.tip_radius = 1.5
lift_rotor.hub_radius = 0.15
lift_rotor.number_of_blades = 4
lift_rotor.design_tip_mach = 0.65
lift_rotor.freestream_velocity = 500. * Units['ft/min']
lift_rotor.angular_velocity = lift_rotor.design_tip_mach * Air(
).compute_speed_of_sound() / lift_rotor.tip_radius
lift_rotor.design_Cl = 0.7
lift_rotor.design_altitude = 3000. * Units.feet
lift_rotor.design_thrust = 2500 * Units.lbf / 4
lift_rotor.variable_pitch = False
lift_rotor.airfoil_geometry = ['./Airfoils/NACA_4412.txt']
lift_rotor.airfoil_polars = [[
'./Airfoils/Polars/NACA_4412_polar_Re_50000.txt',
'./Airfoils/Polars/NACA_4412_polar_Re_100000.txt',
'./Airfoils/Polars/NACA_4412_polar_Re_200000.txt',
'./Airfoils/Polars/NACA_4412_polar_Re_500000.txt',
'./Airfoils/Polars/NACA_4412_polar_Re_1000000.txt'
]]
lift_rotor.airfoil_polar_stations = np.zeros((20), dtype=np.int8).tolist()
lift_rotor = propeller_design(lift_rotor)
# Appending rotors with different origins
rotations = [1, -1, -1, 1]
origins = [[0.6, 3., -0.125], [4.5, 3., -0.125], [0.6, -3., -0.125],
[4.5, -3., -0.125]]
for ii in range(4):
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)
#------------------------------------------------------------------
# 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)
for _ in range(4):
lift_rotor_motor = deepcopy(lift_rotor_motor)
lift_rotor_motor.tag = 'motor'
net.lift_rotor_motors.append(lift_rotor_motor)
vehicle.append_component(net)
# Now account for things that have been overlooked for now:
vehicle.excrescence_area = 0.1
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.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.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.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.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.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_rotor_engines = 12
net.number_of_propeller_engines = 1
net.rotor_thrust_angle = 90. * Units.degrees
net.propeller_thrust_angle = 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
#------------------------------------------------------------------
rotor_esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
rotor_esc.efficiency = 0.95
net.rotor_esc = 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()
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_propeller_engines
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 = 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_rotor_engines
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_rotor_engines))
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_rotor_engines
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_rotor_engines = len(rotor.origin)
# append propellers to vehicle
net.rotor = 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_motor = propeller_motor
# Rotor (Lift) Motor
rotor_motor = SUAVE.Components.Energy.Converters.Motor()
rotor_motor.efficiency = 0.95
rotor_motor.nominal_voltage = bat.max_voltage
rotor_motor.mass_properties.mass = 3. * Units.kg
rotor_motor.origin = rotor.origin
rotor_motor.propeller_radius = rotor.tip_radius
rotor_motor.gearbox_efficiency = 1.0
rotor_motor.no_load_current = 4.0
rotor_motor = size_optimal_motor(rotor_motor,rotor)
net.rotor_motor = 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
return vehicle
