def simple_sizing(nexus):
# Pull out the vehicle
vec = nexus.vehicle_configurations.base
# Change the dynamic pressure based on the, add a factor of safety
vec.envelope.maximum_dynamic_pressure = nexus.missions.mission.segments.cruise.dynamic_pressure * 1.2
# Scale the horizontal and vertical tails based on the main wing area
vec.wings.horizontal_stabilizer.areas.reference = 0.15 * vec.reference_area
vec.wings.vertical_stabilizer.areas.reference = 0.08 * vec.reference_area
# wing spans,areas, and chords
for wing in vec.wings:
# Unpack
AR = wing.aspect_ratio
S = wing.areas.reference
# Set the spans
wing.spans.projected = np.sqrt(AR * S)
# Set all of the areas for the surfaces
wing.areas.wetted = 2.0 * S
wing.areas.exposed = 1.0 * wing.areas.wetted
wing.areas.affected = 1.0 * wing.areas.wetted
# Set all of the chord lengths
chord = wing.areas.reference / wing.spans.projected
wing.chords.mean_aerodynamic = chord
wing.chords.mean_geometric = chord
wing.chords.root = chord
wing.chords.tip = chord
# Size solar panel area
wing_area = vec.reference_area
spanel = vec.propulsors.network.solar_panel
sratio = spanel.ratio
solar_area = wing_area * sratio
spanel.area = solar_area
spanel.mass_properties.mass = solar_area * (0.60 * Units.kg)
# Resize the motor
motor = vec.propulsors.network.motor
kv = motor.speed_constant
motor = size_from_kv(motor, kv)
# diff the new data
vec.store_diff()
return nexus
def simple_sizing(nexus):
# Pull out the vehicle
vec = nexus.vehicle_configurations.base
# Change the dynamic pressure based on the, add a factor of safety
vec.envelope.maximum_dynamic_pressure = nexus.missions.mission.segments.cruise.dynamic_pressure*1.2
# Scale the horizontal and vertical tails based on the main wing area
vec.wings.horizontal_stabilizer.areas.reference = 0.15 * vec.reference_area
vec.wings.vertical_stabilizer.areas.reference = 0.08 * vec.reference_area
# wing spans,areas, and chords
for wing in vec.wings:
# Unpack
AR = wing.aspect_ratio
S = wing.areas.reference
# Set the spans
wing.spans.projected = np.sqrt(AR*S)
# Set all of the areas for the surfaces
wing.areas.wetted = 2.0 * S
wing.areas.exposed = 1.0 * wing.areas.wetted
wing.areas.affected = 1.0 * wing.areas.wetted
# Set all of the chord lengths
chord = wing.areas.reference/wing.spans.projected
wing.chords.mean_aerodynamic = chord
wing.chords.mean_geometric = chord
wing.chords.root = chord
wing.chords.tip = chord
# Size solar panel area
wing_area = vec.reference_area
spanel = vec.propulsors.network.solar_panel
sratio = spanel.ratio
solar_area = wing_area*sratio
spanel.area = solar_area
spanel.mass_properties.mass = solar_area*(0.60 * Units.kg)
# Resize the motor
motor = vec.propulsors.network.motor
kv = motor.speed_constant
motor = size_from_kv(motor, kv)
# diff the new data
vec.store_diff()
return nexus
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Tecnam_P2006TElectric'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 1400 * Units.kilogram
vehicle.mass_properties.takeoff = 1400 * Units.kilogram
vehicle.mass_properties.operating_empty = 1000 * Units.kilogram
vehicle.mass_properties.max_zero_fuel = 1400 * Units.kilogram
vehicle.mass_properties.cargo = 80 * Units.kilogram
# envelope properties
vehicle.envelope.ultimate_load = 5.7
vehicle.envelope.limit_load = 3.8
# basic parameters
vehicle.reference_area = 64.4 * Units['meters**2']
vehicle.passengers = 4
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Landing Gear
# ------------------------------------------------------------------
# used for noise calculations
#landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
#landing_gear.tag = "main_landing_gear"
#landing_gear.main_tire_diameter = 0.423 * Units.m
#landing_gear.nose_tire_diameter = 0.3625 * Units.m
#landing_gear.main_strut_length = 0.4833 * Units.m
#landing_gear.nose_strut_length = 0.3625 * Units.m
#landing_gear.main_units = 2 #number of main landing gear units
#landing_gear.nose_units = 1 #number of nose landing gear
#landing_gear.main_wheels = 1 #number of wheels on the main landing gear
#landing_gear.nose_wheels = 1 #number of wheels on the nose landing gear
#vehicle.landing_gear = landing_gear
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
aux = time.time()
fuselage.time = aux
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 2
fuselage.seat_pitch = 0.995 * Units.meter
fuselage.fineness.nose = 1.27
fuselage.fineness.tail = 1 #3.31
fuselage.lengths.nose = 1.16 * Units.meter
fuselage.lengths.tail = 4.637 * Units.meter
fuselage.lengths.cabin = 2.653 * Units.meter
fuselage.lengths.total = 8.45 * Units.meter
fuselage.lengths.fore_space = 0.0 * Units.meter
fuselage.lengths.aft_space = 0.0 * Units.meter
fuselage.width = 1.1 * Units.meter #1.22
fuselage.heights.maximum = 1.41 * Units.meter
fuselage.effective_diameter = 2 * Units.meter
fuselage.areas.side_projected = 7.46 * Units['meters**2']
fuselage.areas.wetted = 25.0 * Units['meters**2']
fuselage.areas.front_projected = 1.54 * Units['meters**2']
fuselage.differential_pressure = 10**5 * Units.pascal # Maximum differential pressure
fuselage.heights.at_quarter_length = 1.077 * Units.meter
fuselage.heights.at_three_quarters_length = 0.5 * Units.meter #0.621 * Units.meter
fuselage.heights.at_wing_root_quarter_chord = 1.41 * Units.meter
## OpenVSP Design
fuselage.OpenVSP_values = Data() # VSP uses degrees directly
#MidFuselage1 Section
fuselage.OpenVSP_values.midfus1 = Data()
fuselage.OpenVSP_values.midfus1.z_pos = 0.03
#MidFuselage2 Section
fuselage.OpenVSP_values.midfus2 = Data()
fuselage.OpenVSP_values.midfus2.z_pos = 0.06
#MidFuselage3 Section
fuselage.OpenVSP_values.midfus3 = Data()
fuselage.OpenVSP_values.midfus3.z_pos = 0.04
#Tail Section
fuselage.OpenVSP_values.tail = Data()
fuselage.OpenVSP_values.tail.bottom = Data()
fuselage.OpenVSP_values.tail.z_pos = 0.039
fuselage.OpenVSP_values.tail.bottom.angle = -20.0
fuselage.OpenVSP_values.tail.bottom.strength = 1
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.thickness_to_chord = 0.15249979370200092
wing.taper = 0.9014171440917205
wing.spans.projected = 9.342124951930751 * Units.meter
wing.chords.root = 2.0273876759854024 * Units.meter
wing.chords.tip = wing.chords.root * wing.taper
wing.chords.mean_aerodynamic = (wing.chords.root * (2.0 / 3.0) *
((1.0 + wing.taper + wing.taper**2.0) /
(1.0 + wing.taper)))
wing.areas.reference = (wing.chords.root +
wing.chords.tip) * wing.spans.projected / 2
print wing.areas.reference
basearea = wing.areas.reference
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = wing.areas.wetted
wing.areas.affected = wing.areas.wetted
wing.twists.root = 0. * Units.degrees
wing.twists.tip = 0. * Units.degrees
wing.dihedral = 1. * Units.degrees
wing.origin = [2.986, 0, 1.077] # meters
wing.sweeps.leading_edge = 1.9 * Units.deg
wing.aspect_ratio = (wing.spans.projected *
wing.spans.projected) / wing.areas.reference
wing.span_efficiency = 0.95
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
## Wing Segments
# Root Segment
#segment = SUAVE.Components.Wings.Segment()
#segment.tag = 'root'
#segment.percent_span_location = 0.0
#segment.twist = 0. * Units.deg
#segment.root_chord_percent = 1.
#segment.dihedral_outboard = 1. * Units.degrees
#segment.sweeps.quarter_chord = 0. * Units.degrees
#segment.thickness_to_chord = 0.15
#airfoil = SUAVE.Components.Wings.Airfoils.Airfoil()
#airfoil.coordinate_file = '/Users/Bruno/Documents/Delft/Courses/2016-2017/Thesis/Code/Airfoils/naca642415.dat'
#segment.append_airfoil(airfoil)
#wing.Segments.append(segment)
# Tip Segment
#segment = SUAVE.Components.Wings.Segment()
#segment.tag = 'tip'
#segment.percent_span_location = 1.0
#segment.twist = 0. * Units.deg
#segment.root_chord_percent = 1.
#segment.dihedral_outboard = 1. * Units.degrees
#segment.sweeps.quarter_chord = 0. * Units.degrees
#segment.thickness_to_chord = 0.15
#airfoil = SUAVE.Components.Wings.Airfoils.Airfoil()
#airfoil.coordinate_file = '/Users/Bruno/Documents/Delft/Courses/2016-2017/Thesis/Code/Airfoils/naca642415.dat'
#segment.append_airfoil(airfoil)
#wing.Segments.append(segment)
# ------------------------------------------------------------------
# Flaps
# ------------------------------------------------------------------
wing.flaps.chord = wing.chords.root * 0.15
wing.flaps.span_start = 0.3 * wing.spans.projected
wing.flaps.span_end = 0.8 * wing.spans.projected
wing.flaps.area = wing.flaps.chord * (wing.flaps.span_end -
wing.flaps.span_start)
wing.flaps.type = 'single_slotted'
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 4.193
wing.areas.reference = 0.145 * basearea
wing.sweeps.quarter_chord = 0.0 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.span_efficiency = 0.97
wing.spans.projected = np.sqrt(wing.aspect_ratio * wing.areas.reference)
wing.chords.root = wing.areas.reference / wing.spans.projected
wing.chords.tip = wing.chords.root
wing.chords.mean_aerodynamic = (wing.chords.root * (2.0 / 3.0) *
((1.0 + wing.taper + wing.taper**2.0) /
(1.0 + wing.taper)))
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = wing.areas.wetted
wing.areas.affected = wing.areas.wetted
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [7.789, 0.0, 0.3314] # meters
wing.vertical = False
wing.symmetric = True
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.areas.reference = 0.099 * basearea
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = wing.areas.wetted
wing.areas.affected = wing.areas.wetted
wing.aspect_ratio = 1.407
wing.sweeps.quarter_chord = 38.75 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 0.4142
wing.span_efficiency = 0.97
wing.spans.projected = np.sqrt(wing.aspect_ratio * wing.areas.reference)
wing.chords.root = (2.0 * wing.areas.reference) / (wing.spans.projected *
(1 + wing.taper))
wing.chords.tip = wing.chords.root * wing.taper
wing.chords.mean_aerodynamic = (wing.chords.root * (2.0 / 3.0) *
((1.0 + wing.taper + wing.taper**2.0) /
(1.0 + wing.taper)))
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [7.25, 0, 0.497] # meters
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Propellers Powered By Batteries
# ------------------------------------------------------------------
# build network
net = SUAVE.Components.Energy.Networks.Lift_Forward_Propulsor()
net.nacelle_diameter_lift = 0.08 * Units.meters
net.nacelle_diameter_forward = 0.1732 * Units.meters
net.engine_length_lift = 0.47244 * Units.meters
net.engine_length_forward = 1.2 * Units.meters
net.number_of_engines_lift = 10
print 'Prop Optimization'
print 'Engines Lift Number'
print net.number_of_engines_lift
net.number_of_engines_forward = 2
net.thrust_angle_lift = 0.0 * Units.degrees
net.thrust_angle_forward = 0.0 * Units.degrees
net.voltage = 461. * Units['volt'] #461.
net.areas_forward = Data()
net.areas_forward.wetted = 1.1 * np.pi * net.nacelle_diameter_forward * net.engine_length_forward
net.areas_lift = Data()
net.areas_lift.wetted = 1.1 * np.pi * net.nacelle_diameter_forward * net.engine_length_lift
net.number_of_engines = 1
net.nacelle_diameter = net.nacelle_diameter_forward
net.areas = Data()
net.areas.wetted = net.areas_lift.wetted
net.engine_length = 1.
# Component 1 - Tip ESC
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95 # Gundlach for brushless motors
net.esc_forward = esc
# Component 1 - High Lift ESC
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95 # Gundlach for brushless motors
net.esc_lift = esc
# Component 2 - Tip Propeller
# Design the Propeller
#prop_attributes = Data()
#prop_attributes = propeller_design(prop_attributes)
prop_forward = SUAVE.Components.Energy.Converters.Propeller()
prop_forward.number_blades = 3.0
prop_forward.propulsive_efficiency = 0.85
prop_forward.freestream_velocity = 50.0 * Units['m/s'] # freestream m/s
prop_forward.angular_velocity = 27500. * Units['rpm'] # For 20x10 prop
prop_forward.tip_radius = 0.5 * Units.meter
prop_forward.hub_radius = 0.085 * Units.meter
prop_forward.design_Cl = 0.8
prop_forward.design_altitude = 14.0 * Units.km
prop_forward.design_thrust = 0.0 * Units.newton
prop_forward.design_power = 60000. * Units.watts
prop_forward = propeller_design(prop_forward)
net.propeller_forward = prop_forward
# Component 2 - High Lift Propeller
# Design the Propeller
#prop_attributes = Data()
prop_lift = SUAVE.Components.Energy.Converters.Propeller()
prop_lift.number_blades = 5.0
prop_lift.propulsive_efficiency = 0.85
prop_lift.freestream_velocity = 1. * Units['m/s'] # freestream m/s
prop_lift.angular_velocity = 2750 * Units['rpm'] # For 20x10 prop
prop_lift.tip_radius = 0.26 * Units.meter #0.2880360
prop_lift.hub_radius = 0.07772400 * Units.meter
prop_lift.design_Cl = 0.8
prop_lift.design_altitude = 0.0 * Units.meter
prop_lift.design_thrust = 0.0 * Units.newton
prop_lift.design_power = 10500. * Units.watts
prop_lift = propeller_design(prop_lift)
net.propeller_lift = prop_lift
# Component 3 - Tip Motor
motor = SUAVE.Components.Energy.Converters.Motor_Lo_Fid()
#motor.resistance = 1.
#motor.no_load_current = 7. * Units.ampere
#motor.speed_constant = 11.9999 * Units['rpm/volt'] # RPM/volt converted to (rad/s)/volt
#motor.propeller_radius = prop_forward.tip_radius
#motor.propeller_Cp = prop_forward.Cp[0]
#motor.gear_ratio = 12. # Gear ratio
#motor.gearbox_efficiency = .98 # Gear box efficiency
#motor.expected_current = 160. # Expected current
#motor.mass_properties.mass = 9.0 * Units.kg
#net.motor_forward = motor
motor.speed_constant = 180. * Units['rpm/volt'] # RPM/volt is standard
motor = size_from_kv(motor, motor.speed_constant)
motor.gear_ratio = 1. # Gear ratio, no gearbox
motor.gearbox_efficiency = .98 # Gear box efficiency, no gearbox
motor.motor_efficiency = 0.825
net.motor_forward = motor
# Component 3 - High Lift Motor
motor = SUAVE.Components.Energy.Converters.Motor_Lo_Fid()
#motor.resistance = 0.008
#motor.no_load_current = 4.5 * Units.ampere
#motor.speed_constant = 5800. * Units['rpm/volt'] # RPM/volt converted to (rad/s)/volt
#motor.propeller_radius = prop_lift.tip_radius
#motor.propeller_Cp = prop_lift.Cp[0]
#motor.gear_ratio = 12. # Gear ratio
#motor.gearbox_efficiency = .98 # Gear box efficiency
#motor.expected_current = 25. # Expected current
#motor.mass_properties.mass = 6.0 * Units.kg
#net.motor_lift = motor
motor.speed_constant = 90. * Units['rpm/volt'] # RPM/volt is standard
motor = size_from_kv(motor, motor.speed_constant)
motor.gear_ratio = 1. # Gear ratio, no gearbox
motor.gearbox_efficiency = .98 # Gear box efficiency, no gearbox
motor.motor_efficiency = 0.825
net.motor_lift = motor
# Component 4 - the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 50. * Units.watts
payload.mass_properties.mass = 5.0 * Units.kg
net.payload = payload
# Component 5 - the Avionics
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 50. * Units.watts
net.avionics = avionics
# Component 6 - the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion(
)
bat.mass_properties.mass = 386.0 * Units.kg
bat.specific_energy = 121.8 * Units.Wh / Units.kg #192.84
bat.specific_power = 0.312 * Units.kW / Units.kg #0.837
bat.resistance = 0.32
bat.max_voltage = 538. * Units['volt'] #10000.
initialize_from_mass(bat, bat.mass_properties.mass)
print bat.max_energy
net.battery = bat
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
# add the energy network to the vehicle
vehicle.append_component(net)
#now add weights objects
vehicle.landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
vehicle.control_systems = SUAVE.Components.Physical_Component()
vehicle.electrical_systems = SUAVE.Components.Physical_Component()
vehicle.avionics = SUAVE.Components.Energy.Peripherals.Avionics()
vehicle.passenger_weights = SUAVE.Components.Physical_Component()
#vehicle.furnishings = SUAVE.Components.Physical_Component()
#vehicle.apu = SUAVE.Components.Physical_Component()
#vehicle.hydraulics = SUAVE.Components.Physical_Component()
vehicle.optionals = SUAVE.Components.Physical_Component()
vehicle.wings[
'vertical_stabilizer'].rudder = SUAVE.Components.Physical_Component()
#print vehicle
return vehicle
def simple_sizing(nexus):
configs = nexus.vehicle_configurations
base = configs.base
#find conditions
air_speed = nexus.missions.mission.segments['cruise'].air_speed
altitude = nexus.missions.mission.segments['climb_2'].altitude_end
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
freestream = atmosphere.compute_values(altitude)
freestream0 = atmosphere.compute_values(6000. * Units.ft) #cabin altitude
diff_pressure = np.max(freestream0.pressure - freestream.pressure, 0)
fuselage = base.fuselages['fuselage']
fuselage.differential_pressure = diff_pressure
#now size engine
mach_number = air_speed / freestream.speed_of_sound
#now add to freestream data object
freestream.velocity = air_speed
freestream.mach_number = mach_number
freestream.gravity = 9.81
conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics(
) #assign conditions in form for propulsor sizing
conditions.freestream = freestream
for config in configs:
# fuselage
fuselage = config.fuselages['fuselage']
fuselage.differential_pressure = diff_pressure
# Main Wing
main_wing_span = config.wings.main_wing.spans.projected
main_wing_root_chord = config.wings.main_wing.chords.root
config.wings.main_wing.chords.tip = config.wings.main_wing.chords.root * config.wings.main_wing.taper
config.wings.main_wing.chords.mean_aerodynamic = (
main_wing_root_chord * (2.0 / 3.0) *
((1.0 + config.wings.main_wing.taper +
config.wings.main_wing.taper**2.0) /
(1.0 + config.wings.main_wing.taper)))
config.wings.main_wing.areas.reference = (
main_wing_root_chord +
config.wings.main_wing.chords.tip) * main_wing_span / 2.0
config.wings.main_wing.areas.wetted = 2.0 * config.wings.main_wing.areas.reference
config.wings.main_wing.areas.exposed = config.wings.main_wing.areas.wetted
config.wings.main_wing.areas.affected = config.wings.main_wing.areas.wetted
config.wings.main_wing.aspect_ratio = (
main_wing_span *
main_wing_span) / config.wings.main_wing.areas.reference
config.wings.main_wing.flaps.chord = main_wing_root_chord * 0.15
config.wings.main_wing.flaps.span_start = 0.3 * main_wing_span
config.wings.main_wing.flaps.span_end = 0.8 * main_wing_span
config.wings.main_wing.flaps.area = config.wings.main_wing.flaps.chord * (
config.wings.main_wing.flaps.span_end -
config.wings.main_wing.flaps.span_start)
# Horizontal Stabilizer
config.wings.horizontal_stabilizer.areas.reference = 0.145 * config.wings.main_wing.areas.reference
config.wings.horizontal_stabilizer.spans.projected = np.sqrt(
config.wings.horizontal_stabilizer.aspect_ratio *
config.wings.horizontal_stabilizer.areas.reference)
config.wings.horizontal_stabilizer.chords.root = config.wings.horizontal_stabilizer.areas.reference / config.wings.horizontal_stabilizer.spans.projected
config.wings.horizontal_stabilizer.chords.tip = config.wings.horizontal_stabilizer.chords.root
config.wings.horizontal_stabilizer.chords.mean_aerodynamic = (
config.wings.horizontal_stabilizer.chords.root * (2.0 / 3.0) *
((1.0 + config.wings.horizontal_stabilizer.taper +
config.wings.horizontal_stabilizer.taper**2.0) /
(1.0 + config.wings.horizontal_stabilizer.taper)))
config.wings.horizontal_stabilizer.areas.wetted = 2.0 * config.wings.horizontal_stabilizer.areas.reference
config.wings.horizontal_stabilizer.areas.exposed = config.wings.horizontal_stabilizer.areas.wetted
config.wings.horizontal_stabilizer.areas.affected = config.wings.horizontal_stabilizer.areas.wetted
# Vertical Stabilizer
config.wings.vertical_stabilizer.areas.reference = 0.099 * config.wings.main_wing.areas.reference
config.wings.vertical_stabilizer.areas.wetted = 2.0 * config.wings.vertical_stabilizer.areas.reference
config.wings.vertical_stabilizer.areas.exposed = config.wings.vertical_stabilizer.areas.wetted
config.wings.vertical_stabilizer.areas.affected = config.wings.vertical_stabilizer.areas.wetted
config.wings.vertical_stabilizer.spans.projected = np.sqrt(
config.wings.vertical_stabilizer.aspect_ratio *
config.wings.vertical_stabilizer.areas.reference)
config.wings.vertical_stabilizer.chords.root = (
2.0 * config.wings.vertical_stabilizer.areas.reference) / (
config.wings.vertical_stabilizer.spans.projected *
(1 + config.wings.vertical_stabilizer.taper))
config.wings.vertical_stabilizer.chords.tip = config.wings.vertical_stabilizer.chords.root * config.wings.vertical_stabilizer.taper
config.wings.vertical_stabilizer.chords.mean_aerodynamic = (
config.wings.vertical_stabilizer.chords.root * (2.0 / 3.0) *
((1.0 + config.wings.vertical_stabilizer.taper +
config.wings.vertical_stabilizer.taper**2.0) /
(1.0 + config.wings.vertical_stabilizer.taper)))
# Resize the motor
kv = config.propulsors.propulsor.motor_forward.speed_constant
config.propulsors.propulsor.motor_forward = size_from_kv(
config.propulsors.propulsor.motor_forward, kv)
kv = config.propulsors.propulsor.motor_lift.speed_constant
config.propulsors.propulsor.motor_lift = size_from_kv(
config.propulsors.propulsor.motor_lift, kv)
# diff the new data
config.store_diff()
#turbofan_sizing(config.propulsors['turbofan'], mach_number = mach_number, altitude = altitude)
#compute_turbofan_geometry(config.propulsors['turbofan'], conditions)
# ------------------------------------------------------------------
# Landing Configuration
# ------------------------------------------------------------------
landing = nexus.vehicle_configurations.landing
landing_conditions = Data()
landing_conditions.freestream = Data()
# landing weight
landing.mass_properties.landing = 1.0 * config.mass_properties.takeoff
# Landing CL_max
altitude = nexus.missions.mission.segments[-1].altitude_end
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
freestream_landing = atmosphere.compute_values(0.)
landing_conditions.freestream.velocity = nexus.missions.mission.segments[
'descent_2'].air_speed
landing_conditions.freestream.density = freestream_landing.density
landing_conditions.freestream.dynamic_viscosity = freestream_landing.dynamic_viscosity
CL_max_landing, CDi = compute_max_lift_coeff(landing, landing_conditions)
landing.maximum_lift_coefficient = CL_max_landing
#Takeoff CL_max
takeoff = nexus.vehicle_configurations.takeoff
takeoff_conditions = Data()
takeoff_conditions.freestream = Data()
altitude = nexus.missions.mission.airport.altitude
freestream_takeoff = atmosphere.compute_values(altitude)
takeoff_conditions.freestream.velocity = nexus.missions.mission.segments.climb_1.air_speed
takeoff_conditions.freestream.density = freestream_takeoff.density
takeoff_conditions.freestream.dynamic_viscosity = freestream_takeoff.dynamic_viscosity
max_CL_takeoff, CDi = compute_max_lift_coeff(takeoff, takeoff_conditions)
takeoff.maximum_lift_coefficient = max_CL_takeoff
#Base config CL_max
base = nexus.vehicle_configurations.base
base_conditions = Data()
base_conditions.freestream = takeoff_conditions.freestream
max_CL_base, CDi = compute_max_lift_coeff(base, base_conditions)
base.maximum_lift_coefficient = max_CL_base
return nexus
def main():
#------------------------------------------------------------------
# Network
#------------------------------------------------------------------
# build network
net = Solar_Low_Fidelity()
net.number_of_engines = 1.
net.nacelle_diameter = 0.05
net.areas = Data()
net.areas.wetted = 0.01 * (2 * np.pi * 0.01 / 2)
net.engine_length = 0.01
# Component 1 the Sun
sun = SUAVE.Components.Energy.Processes.Solar_Radiation()
net.solar_flux = sun
# Component 2 the solar panels
panel = SUAVE.Components.Energy.Converters.Solar_Panel()
panel.ratio = 0.9
panel.area = 1.0 * panel.ratio
panel.efficiency = 0.25
panel.mass_properties.mass = panel.area * (0.60 * Units.kg)
net.solar_panel = panel
# Component 3 the ESC
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95 # Gundlach for brushless motors
net.esc = esc
# Component 5 the Propeller
prop = SUAVE.Components.Energy.Converters.Propeller_Lo_Fid()
prop.propulsive_efficiency = 0.825
net.propeller = prop
# Component 4 the Motor
motor = SUAVE.Components.Energy.Converters.Motor_Lo_Fid()
motor.speed_constant = 800. * Units['rpm/volt'] # RPM/volt is standard
motor = size_from_kv(motor)
motor.gear_ratio = 1. # Gear ratio, no gearbox
motor.gearbox_efficiency = 1. # Gear box efficiency, no gearbox
motor.motor_efficiency = 0.825
net.motor = motor
# Component 6 the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 0. #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 = 10. #Watts
net.avionics = avionics
# Component 8 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion(
)
bat.mass_properties.mass = 5.0 * Units.kg
bat.specific_energy = 250. * Units.Wh / Units.kg
bat.resistance = 0.003
bat.iters = 0
initialize_from_mass(bat)
net.battery = bat
#Component 9 the system logic controller and MPPT
logic = SUAVE.Components.Energy.Distributors.Solar_Logic()
logic.system_voltage = 18.5
logic.MPPT_efficiency = 0.95
net.solar_logic = logic
# Setup the conditions to run the network
state = Data()
state.conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics(
)
state.numerics = SUAVE.Analyses.Mission.Segments.Conditions.Numerics()
conditions = state.conditions
numerics = state.numerics
# Calculate atmospheric properties
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmosphere_conditions = atmosphere.compute_values(1000. * Units.ft)
rho = atmosphere_conditions.density[0, :]
a = atmosphere_conditions.speed_of_sound[0, :]
mu = atmosphere_conditions.dynamic_viscosity[0, :]
T = atmosphere_conditions.temperature[0, :]
conditions.propulsion.throttle = np.array([[1.0], [1.0]])
conditions.freestream.velocity = np.array([[1.0], [1.0]])
conditions.freestream.density = np.array([rho, rho])
conditions.freestream.dynamic_viscosity = np.array([mu, mu])
conditions.freestream.speed_of_sound = np.array([a, a])
conditions.freestream.altitude = np.array([[1000.0], [1000.0]])
conditions.propulsion.battery_energy = bat.max_energy * np.ones_like(
conditions.freestream.altitude)
conditions.frames.body.inertial_rotations = np.zeros([2, 3])
conditions.frames.inertial.time = np.array([[0.0], [1.0]])
numerics.time.integrate = np.array([[0, 0], [0, 1]])
numerics.time.differentiate = np.array([[0, 0], [0, 1]])
numerics.time.control_points = np.array([[0, 0], [0, 1]])
conditions.frames.planet.start_time = time.strptime(
"Sat, Jun 21 06:00:00 2014",
"%a, %b %d %H:%M:%S %Y",
)
conditions.frames.planet.latitude = np.array([[0.0], [0.0]])
conditions.frames.planet.longitude = np.array([[0.0], [0.0]])
conditions.freestream.temperature = np.array([T, T])
conditions.frames.body.transform_to_inertial = np.array([[[1., 0., 0.],
[0., 1., 0.],
[0., 0., 1.]],
[[1., 0., 0.],
[0., 1., 0.],
[0., 0., 1.]]])
# Run the network and print the results
results = net(state)
F = results.thrust_force_vector
# Truth results
truth_F = [[68.78277813], [68.78277813]]
truth_i = [[5.75011436], [5.75011436]]
truth_rpm = [[14390.30435183], [14390.30435183]]
truth_bat = [[3169014.08450704], [3168897.35916947]]
error = Data()
error.Thrust = np.max(np.abs(F[:, 0] - truth_F))
error.RPM = np.max(np.abs(conditions.propulsion.propeller_rpm - truth_rpm))
error.Current = np.max(
np.abs(conditions.propulsion.battery_current - truth_i))
error.Battery = np.max(np.abs(bat.current_energy - truth_bat))
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1e-6)
return
def base_setup(nexus):
aerofoil = nexus.surrogate_data.vec.aerofoil
results = generate_vehicle(nexus)
s, rootChord, rcp, psl, sqc, do, tw, ttc, aero_geom, A_ref, span_vals, totmass = results
c_bar, ca, cg = aero_geom
A_ref_wet, A_ref_pln = A_ref
wing_taper, wing_sweep = span_vals
# print '===== RESULTS'
# print results
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'ModBWB'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = totmass * Units.kg
# vehicle.mass_properties.operating_empty = totmass * Units.kg
# vehicle.mass_properties.max_takeoff = totmass * Units.kg
# basic parameters
vehicle.reference_area = A_ref_pln * Units.m**2
vehicle.envelope.ultimate_load = 2.0
vehicle.envelope.limit_load = 1.5
vehicle.envelope.maximum_dynamic_pressure = 0.5 * 1.225 * (40.**2.) #Max q
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
for i in range(0, len(psl) + 1):
airfoil = SUAVE.Components.Wings.Airfoils.Airfoil()
airfoil.coordinate_file = './marske1.dat'
if i == 0:
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.aspect_ratio = s**2 / vehicle.reference_area
wing.thickness_to_chord = ttc[0]
wing.taper = wing_taper
wing.span_efficiency = 0.95
wing.spans.projected = s * Units.m
# print 'ROOT CHORD : ' + str(rootChord)
wing.chords.root = rootChord * Units.m
wing.chords.tip = wing.taper * wing.chords.root
wing.chords.mean_aerodynamic = c_bar * Units.m
wing.areas.reference = A_ref_pln * Units.m**2
wing.areas.wetted = A_ref_wet * Units.m**2
wing.sweeps.quarter_chord = wing_sweep * Units.deg
wing.twists.root = tw[0] * Units.deg
wing.twists.tip = tw[-1] * Units.deg
# wing.dihedral = do[0] * Units.deg
wing.origin = [0., 0., 0]
wing.aerodynamic_center = [ca, 0, 0] #[ca,0,0]
wing.center_of_gravity = [cg, 0., 0.] #[cg,0.,0.]
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
if len(psl) == 1:
wing.dihedral = do[i] * Units.deg
wing.sweeps.quarter_chord = sqc[i] * Units.deg
# wing segments
elif i > 0 and len(psl) > 1:
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'section_' + str(i - 1)
segment.percent_span_location = psl[i - 1]
segment.root_chord_percent = rcp[i - 1]
segment.dihedral_outboard = do[i - 1] * Units.deg
segment.sweeps.quarter_chord = sqc[i - 1] * Units.deg
segment.thickness_to_chord = ttc[i - 1]
wing.Segments.append(segment)
wing.Segments.append(segment)
# add to vehicle
vehicle.append_component(wing)
#------------------------------------------------------------------
# Propulsor
#------------------------------------------------------------------
# build network
net = Solar_Low_Fidelity()
net.number_of_engines = 0. #1.
net.nacelle_diameter = 0.05
net.areas = Data()
net.areas.wetted = 0.01 * (2 * np.pi * 0.01 / 2)
net.engine_length = 0.01
# Component 1 the Sun
sun = SUAVE.Components.Energy.Processes.Solar_Radiation()
net.solar_flux = sun
# Component 2 the solar panels
panel = SUAVE.Components.Energy.Converters.Solar_Panel()
panel.ratio = 0.9
panel.area = vehicle.reference_area * panel.ratio
panel.efficiency = 0.25
panel.mass_properties.mass = panel.area * (0.60 * Units.kg)
net.solar_panel = panel
# Component 3 the ESC
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95 # Gundlach for brushless motors
net.esc = esc
# Component 5 the Propeller
prop = SUAVE.Components.Energy.Converters.Propeller_Lo_Fid()
prop.propulsive_efficiency = 0.825
net.propeller = prop
# Component 4 the Motor
motor = SUAVE.Components.Energy.Converters.Motor_Lo_Fid()
kv = 800. * Units['rpm/volt'] # RPM/volt is standard
motor = size_from_kv(motor, kv)
motor.gear_ratio = 1. # Gear ratio, no gearbox
motor.gearbox_efficiency = 1. # Gear box efficiency, no gearbox
motor.motor_efficiency = 0.825
net.motor = motor
# Component 6 the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 0. #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 = 10. #Watts
net.avionics = avionics
# Component 8 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion(
)
bat.mass_properties.mass = 5.0 * Units.kg
bat.specific_energy = 250. * Units.Wh / Units.kg
bat.resistance = 0.003
bat.iters = 0
initialize_from_mass(bat, bat.mass_properties.mass)
net.battery = bat
#Component 9 the system logic controller and MPPT
logic = SUAVE.Components.Energy.Distributors.Solar_Logic()
logic.system_voltage = 18.5
logic.MPPT_efficiency = 0.95
net.solar_logic = logic
# add the solar network to the vehicle
vehicle.append_component(net)
return vehicle
def base_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Solar'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 4.00 * Units.kg
vehicle.mass_properties.operating_empty = 4.00 * Units.kg
vehicle.mass_properties.max_takeoff = 4.00 * Units.kg
# basic parameters
vehicle.reference_area = 1.0
vehicle.envelope.ultimate_load = 2.0
vehicle.envelope.limit_load = 1.5
vehicle.envelope.maximum_dynamic_pressure = 115. * 1.25 * Units.pascals #Max q
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.areas.reference = vehicle.reference_area
wing.spans.projected = 40.0 * Units.meters
wing.aspect_ratio = (wing.spans.projected**2) / wing.areas.reference
wing.sweeps.quarter_chord = 0.0 * Units.deg
wing.symmetric = True
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.vertical = False
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
wing.chords.mean_aerodynamic = wing.areas.reference / wing.spans.projected
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.highlift = False
wing.vertical = False
wing.number_ribs = 26.
wing.number_end_ribs = 2.
wing.transition_x_upper = 0.6
wing.transition_x_lower = 1.0
wing.origin = [[3.0, 0.0, 0.0]]
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Horizontal_Tail()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 10.
wing.sweeps.quarter_chord = 0 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.areas.reference = vehicle.reference_area * .15
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.spans.projected = np.sqrt(wing.aspect_ratio * wing.areas.reference)
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
wing.number_ribs = 5.0
wing.chords.root = wing.areas.reference / wing.spans.projected
wing.chords.tip = wing.areas.reference / wing.spans.projected
wing.chords.mean_aerodynamic = wing.areas.reference / wing.spans.projected
wing.origin = [[10., 0.0, 0.0]]
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Vertical_Tail()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 10.
wing.sweeps.quarter_chord = 0 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.areas.reference = vehicle.reference_area * 0.1
wing.spans.projected = np.sqrt(wing.aspect_ratio * wing.areas.reference)
wing.chords.root = wing.areas.reference / wing.spans.projected
wing.chords.tip = wing.areas.reference / wing.spans.projected
wing.chords.mean_aerodynamic = wing.areas.reference / wing.spans.projected
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[10., 0.0, 0.0]]
wing.symmetric = True
wing.vertical = True
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
wing.number_ribs = 5.
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Nacelle
# ------------------------------------------------------------------
nacelle = SUAVE.Components.Nacelles.Nacelle()
nacelle.diameter = 0.05 * Units.meters
nacelle.length = 0.01 * Units.meters
nacelle.tag = 'nacelle'
nacelle.areas.wetted = nacelle.length * (2 * np.pi * nacelle.diameter / 2.)
vehicle.append_component(nacelle)
#------------------------------------------------------------------
# Propulsor
#------------------------------------------------------------------
# build network
net = Solar_Low_Fidelity()
net.number_of_engines = 1.
# Component 1 the Sun
sun = SUAVE.Components.Energy.Processes.Solar_Radiation()
net.solar_flux = sun
# Component 2 the solar panels
panel = SUAVE.Components.Energy.Converters.Solar_Panel()
panel.ratio = 0.9
panel.area = vehicle.reference_area * panel.ratio
panel.efficiency = 0.25
panel.mass_properties.mass = panel.area * (0.60 * Units.kg)
net.solar_panel = panel
# Component 3 the ESC
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95 # Gundlach for brushless motors
net.esc = esc
# Component 4 the Propeller
prop = SUAVE.Components.Energy.Converters.Propeller_Lo_Fid()
prop.propulsive_efficiency = 0.825
net.propeller = prop
# Component 5 the Motor
motor = SUAVE.Components.Energy.Converters.Motor_Lo_Fid()
motor.speed_constant = 900. * Units['rpm/volt'] # RPM/volt is standard
motor = size_from_kv(motor)
motor.gear_ratio = 1. # Gear ratio, no gearbox
motor.gearbox_efficiency = 1. # Gear box efficiency, no gearbox
motor.motor_efficiency = 0.8
net.motor = motor
# Component 6 the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 0. #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 = 10. #Watts
net.avionics = avionics
# Component 8 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion(
)
bat.mass_properties.mass = 3.0 * Units.kg
bat.specific_energy = 400. * Units.Wh / Units.kg
bat.resistance = 0.003
initialize_from_mass(bat, bat.mass_properties.mass)
net.battery = bat
#Component 9 the system logic controller and MPPT
logic = SUAVE.Components.Energy.Distributors.Solar_Logic()
logic.system_voltage = 18.5
logic.MPPT_efficiency = 0.95
net.solar_logic = logic
# add the solar network to the vehicle
vehicle.append_component(net)
return vehicle
def simple_sizing(nexus):
# Pull out the vehicle
vec = nexus.vehicle_configurations.base
num_seg = nexus.surrogate_data.vec.init_vec.num_seg
# Change the dynamic pressure based on the mission, add a factor of safety
vec.envelope.maximum_dynamic_pressure = nexus.missions.mission.segments.cruise.dynamic_pressure * 1.2
# print vec.wings.main_wing
# pull out variables that are being optimized
new_vec = Data()
new_vec.span = vec.wings.main_wing.spans.projected
new_vec.root_chord = vec.wings.main_wing.chords.root
new_vec.sqc = []
new_vec.rcp = []
new_vec.psl = []
new_vec.do = []
new_vec.tw = []
new_vec.ttc = []
print '================'
in_segs = False
for item in vec.wings.main_wing:
if type(item) == type(
vec.wings.main_wing.Segments): # check if item is wing segment
try:
for i in range(0, num_seg):
key = 'section_' + str(i)
section = getattr(item, key)
# print 'section_'+str(i) + '\n'+str(section)
new_vec.sqc.append(np.rad2deg(
section.sweeps.quarter_chord))
new_vec.rcp.append(section.root_chord_percent)
new_vec.psl.append(section.percent_span_location)
new_vec.do.append(np.rad2deg(section.dihedral_outboard))
new_vec.ttc.append(section.thickness_to_chord)
in_segs = True
except Exception as err:
print err
print 'Not a wing segment, implied whole wing'
if new_vec.psl == []:
new_vec.sqc.append(np.rad2deg(
vec.wings.main_wing.sweeps.quarter_chord))
new_vec.rcp.append(1.)
new_vec.rcp.append(vec.wings.main_wing.taper)
new_vec.psl.append(0.)
new_vec.do.append(np.rad2deg(vec.wings.main_wing.dihedral))
new_vec.ttc.append(vec.wings.main_wing.thickness_to_chord)
new_vec.tw.append(np.rad2deg(vec.wings.main_wing.twists.root))
new_vec.tw.append(np.rad2deg(vec.wings.main_wing.twists.tip))
if in_segs:
new_vec.rcp.append(vec.wings.main_wing.taper)
# logic checks
# span 2* chord at min
if new_vec.span < 2 * new_vec.root_chord:
new_vec.span = 2 * new_vec.root_chord
# no inboard psl less than psl outboard
if len(new_vec.psl) > 1:
for i in range(1, len(new_vec.psl)):
if new_vec.psl[i] < new_vec.psl[i - 1]:
new_vec.psl[i] = new_vec.psl[i -
1] + (1 - new_vec.psl[i - 1]) / 2
# should find intermediate location
# no outboard chord section larger than inboard (wing tear)
for i in range(1, len(new_vec.rcp)):
if new_vec.rcp[i] > new_vec.rcp[i - 1]:
new_vec.rcp[i] = new_vec.rcp[i - 1]
# assign new iteration of vehicle to surrog data vehicle store
nexus.surrogate_data.vec.make_vec = new_vec
results = None
results = generate_vehicle(nexus)
s, rootChord, rcp, psl, sqc, do, tw, ttc, aero_geom, A_ref, span_vals, totmass = results
c_bar, ca, cg = aero_geom
A_ref_wet, A_ref_pln = A_ref
wing_taper, wing_sweep = span_vals
"""
UPDATE ALL NECESSARY THINGS (:
"""
# update all wing structure values
vec.mass_properties.takeoff = totmass * Units.kg
# vec.mass_properties.operating_empty = totmass * Units.kg
# vec.mass_properties.max_takeoff = totmass * Units.kg
vec.reference_area = A_ref_pln * Units.m**2
vw = vec.wings.main_wing
vw.spans.projected = s * Units.m
vw.taper = wing_taper
vw.chords.root = rootChord * Units.m
vw.chords.tip = wing_taper * vw.chords.root
vw.chords.mean_aerodynamic = c_bar * Units.m
vw.areas.reference = A_ref_pln * Units.m**2
vw.areas.wetted = A_ref_wet * Units.m**2
vw.aspect_ratio = s**2 / (A_ref_pln)
vw.sweeps.quarter_chord = wing_sweep * Units.deg
vw.twists.root = new_vec.tw[0] * Units.deg
vw.twists.tip = new_vec.tw[-1] * Units.deg
if len(psl) == 1:
vw.dihedral = do[0] * Units.deg
vw.sweeps.quarter_chord = sqc[0] * Units.deg
# update all segment values
if len(psl) > 1:
for item in vec.wings.main_wing:
if type(item) == type(vec.wings.main_wing.Segments
): # check if item is wing segment
for i in range(0, num_seg):
key = 'section_' + str(i)
# print item
segment = getattr(item, key)
# print segment.tag
segment.percent_span_location = psl[i]
segment.root_chord_percent = rcp[i]
segment.dihedral_outboard = do[i] * Units.deg
segment.sweeps.quarter_chord = sqc[i] * Units.deg
segment.thickness_to_chord = ttc[i]
# print 'section'+str(i) + '\n'+str(segment)
# Size solar panel area
wing_area = vec.reference_area
spanel = vec.propulsors.network.solar_panel
sratio = spanel.ratio
solar_area = wing_area * sratio
spanel.area = solar_area
spanel.mass_properties.mass = solar_area * (0.60 * Units.kg)
# Resize the motor
motor = vec.propulsors.network.motor
kv = motor.speed_constant
motor = size_from_kv(motor, kv)
# diff the new data
vec.store_diff()
return nexus
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Tecnam_P2006TElectric'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.max_takeoff = 1400 * Units.kilogram
vehicle.mass_properties.takeoff = 1400 * Units.kilogram
vehicle.mass_properties.operating_empty = 1000 * Units.kilogram
vehicle.mass_properties.max_zero_fuel = 1400 * Units.kilogram
vehicle.mass_properties.cargo = 80 * Units.kilogram
# envelope properties
vehicle.envelope.ultimate_load = 5.7
vehicle.envelope.limit_load = 3.8
# basic parameters
vehicle.reference_area = 64.4 * Units['meters**2']
vehicle.passengers = 4
vehicle.systems.control = "fully powered"
vehicle.systems.accessories = "medium range"
# ------------------------------------------------------------------
# Landing Gear
# ------------------------------------------------------------------
# used for noise calculations
landing_gear = SUAVE.Components.Landing_Gear.Landing_Gear()
landing_gear.tag = "main_landing_gear"
landing_gear.main_tire_diameter = 0.423 * Units.m
landing_gear.nose_tire_diameter = 0.3625 * Units.m
landing_gear.main_strut_length = 0.4833 * Units.m
landing_gear.nose_strut_length = 0.3625 * Units.m
landing_gear.main_units = 2 #number of main landing gear units
landing_gear.nose_units = 1 #number of nose landing gear
landing_gear.main_wheels = 1 #number of wheels on the main landing gear
landing_gear.nose_wheels = 1 #number of wheels on the nose landing gear
vehicle.landing_gear = landing_gear
# ------------------------------------------------------------------
# Fuselage
# ------------------------------------------------------------------
fuselage = SUAVE.Components.Fuselages.Fuselage()
fuselage.tag = 'fuselage'
fuselage.number_coach_seats = vehicle.passengers
fuselage.seats_abreast = 2
fuselage.seat_pitch = 0.995 * Units.meter
fuselage.fineness.nose = 1.27
fuselage.fineness.tail = 1 #3.31
fuselage.lengths.nose = 1.16 * Units.meter
fuselage.lengths.tail = 4.637 * Units.meter
fuselage.lengths.cabin = 2.653 * Units.meter
fuselage.lengths.total = 8.45 * Units.meter
fuselage.lengths.fore_space = 0.0 * Units.meter
fuselage.lengths.aft_space = 0.0 * Units.meter
fuselage.width = 1.22 * Units.meter
fuselage.heights.maximum = 1.41 * Units.meter
fuselage.effective_diameter = 2 * Units.meter
fuselage.areas.side_projected = 7.46 * Units['meters**2']
fuselage.areas.wetted = 25.0 * Units['meters**2']
fuselage.areas.front_projected = 1.54 * Units['meters**2']
fuselage.differential_pressure = 0.0 * Units.pascal # Maximum differential pressure
fuselage.heights.at_quarter_length = 1.077 * Units.meter
fuselage.heights.at_three_quarters_length = 0.5 * Units.meter #0.621 * Units.meter
fuselage.heights.at_wing_root_quarter_chord = 1.41 * Units.meter
# add to vehicle
vehicle.append_component(fuselage)
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.thickness_to_chord = 0.15
wing.taper = 0.7016
wing.spans.projected = 9.631680 * Units.meter
wing.chords.root = 0.7559040 * Units.meter
wing.chords.tip = wing.chords.root * wing.taper
wing.chords.mean_aerodynamic = 0.6 * Units.meter
wing.areas.reference = (wing.chords.root +
wing.chords.tip) * wing.spans.projected / 2
wing.twists.root = 0. * Units.degrees
wing.twists.tip = 0. * Units.degrees
wing.dihedral = 1. * Units.degrees
wing.origin = [2.986, 0, 1.077] # meters
wing.sweeps.leading_edge = 1.9 * Units.deg
wing.aspect_ratio = (wing.spans.projected *
wing.spans.projected) / wing.areas.reference
wing.span_efficiency = 0.99 * (
1 - 0.0407 * (fuselage.width / wing.spans.projected) - 1.792 *
((fuselage.width / wing.spans.projected)**2))
wing.vertical = False
wing.symmetric = True
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
# ------------------------------------------------------------------
# Flaps
# ------------------------------------------------------------------
wing.flaps.chord = 0.20
wing.flaps.span_start = 0.1053
wing.flaps.span_end = 0.6842
wing.flaps.type = 'single_slotted'
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 4.193
wing.sweeps.quarter_chord = 0.0 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.span_efficiency = 0.733
wing.spans.projected = 3.3 * Units.meter
wing.chords.root = 0.787 * Units.meter
wing.chords.tip = 0.787 * Units.meter
wing.chords.mean_aerodynamic = (wing.chords.root * (2.0 / 3.0) *
((1.0 + wing.taper + wing.taper**2.0) /
(1.0 + wing.taper))) * Units.meter
wing.areas.reference = 2.5971 * Units['meters**2']
wing.areas.exposed = 4.0 * Units['meters**2']
wing.areas.wetted = 4.0 * Units['meters**2']
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [7.789, 0.0, 0.3314] # meters
wing.vertical = False
wing.symmetric = True
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.aspect_ratio = 1.407
wing.sweeps.quarter_chord = 38.75 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.span_efficiency = -0.107
wing.spans.projected = 1.574 * Units.meter
wing.chords.root = 1.2 * Units.meter
wing.chords.tip = 0.497 * Units.meter
wing.chords.mean_aerodynamic = (wing.chords.root * (2.0 / 3.0) *
((1.0 + wing.taper + wing.taper**2.0) /
(1.0 + wing.taper))) * Units.meter
wing.areas.reference = 1.761 * Units['meters**2']
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [7.25, 0, 0.497] # meters
wing.vertical = True
wing.symmetric = False
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Propellers Powered By Batteries
# ------------------------------------------------------------------
# build network
net = SUAVE.Components.Energy.Networks.Lift_Forward_Propulsor_Network_Lo_Fi(
)
net.nacelle_diameter_lift = 0.08 * Units.meters
net.nacelle_diameter_forward = 0.1732 * Units.meters
net.engine_length_lift = 0.47244 * Units.meters
net.engine_length_forward = 1.2 * Units.meters
net.number_of_engines_lift = 12
net.number_of_engines_forward = 2
net.thrust_angle_lift = 0.0 * Units.degrees
net.thrust_angle_forward = 0.0 * Units.degrees
net.voltage = 461.
net.areas_forward = Data()
net.areas_forward.wetted = 1.1 * np.pi * net.nacelle_diameter_forward * net.engine_length_forward
net.areas_lift = Data()
net.areas_lift.wetted = 1.1 * np.pi * net.nacelle_diameter_forward * net.engine_length_lift
# Component 1 - Tip ESC
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95 # Gundlach for brushless motors
net.esc_forward = esc
# Component 1 - High Lift ESC
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95 # Gundlach for brushless motors
net.esc_lift = esc
# Component 2 Tip Propeller
prop = SUAVE.Components.Energy.Converters.Propeller_Lo_Fid()
prop.propulsive_efficiency = 0.95
prop.tip_radius = 0.762 * Units.meter
net.propeller_forward = prop
# Component 2 High Lift Propeller
prop = SUAVE.Components.Energy.Converters.Propeller_Lo_Fid()
prop.propulsive_efficiency = 0.95
prop.tip_radius = 0.2880360 * Units.meter
net.propeller_lift = prop
# Component 3 Tip Motor
motor = SUAVE.Components.Energy.Converters.Motor_Lo_Fid()
kv = 300. * Units['rpm/volt'] # RPM/volt is standard
motor.expected_current = 1000.0
motor = size_from_kv(motor, kv)
motor.gear_ratio = 1. # Gear ratio, no gearbox
motor.gearbox_efficiency = 1. # Gear box efficiency, no gearbox
motor.motor_efficiency = 0.95
net.motor_forward = motor
# Component 3 High Lift Motor
motor = SUAVE.Components.Energy.Converters.Motor_Lo_Fid()
kv = 3691. * Units['rpm/volt'] # RPM/volt is standard
motor.expected_current = 1000.0
motor = size_from_kv(motor, kv)
motor.gear_ratio = 1. # Gear ratio, no gearbox
motor.gearbox_efficiency = 1. # Gear box efficiency, no gearbox
motor.motor_efficiency = 0.95
net.motor_lift = motor
# Component 4 - the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 50. * Units.watts
payload.mass_properties.mass = 5.0 * Units.kg
net.payload = payload
# Component 5 - the Avionics
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 50. * Units.watts
net.avionics = avionics
# Component 6 - the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion(
)
bat.mass_properties.mass = 358.33 * Units.kg
bat.specific_energy = 192.84 * Units.Wh / Units.kg
bat.specific_power = 0.837 * Units.kW / Units.kg
bat.resistance = 0.0153
bat.max_voltage = 11.078
initialize_from_mass(bat, bat.mass_properties.mass)
net.battery = bat
# ------------------------------------------------------------------
# Vehicle Definition Complete
# ------------------------------------------------------------------
# add the energy network to the vehicle
vehicle.append_component(net)
#print vehicle
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'tail_sitter'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 0.82 * Units.kg
vehicle.mass_properties.operating_empty = 0.82 * Units.kg
vehicle.mass_properties.max_takeoff = 0.82 * Units.kg
# basic parameters
vehicle.reference_area = 0.1668
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.areas.reference = vehicle.reference_area
wing.spans.projected = 1.03 * Units.m
wing.aspect_ratio = (wing.spans.projected**2)/wing.areas.reference
wing.sweeps.quarter_chord = 5.0 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.dynamic_pressure_ratio = 1.0
wing.chords.mean_aerodynamic = 0.162 * Units.m
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.high_lift = False
wing.vertical = False
wing.symmetric = True
# add to vehicle
vehicle.append_component(wing)
#------------------------------------------------------------------
# Propulsor
#------------------------------------------------------------------
# build network
net = SUAVE.Components.Energy.Networks.Battery_Propeller()
net.number_of_propeller_engines = 4.
net.voltage = 12.3
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
# Design the Propeller
prop = SUAVE.Components.Energy.Converters.Propeller()
prop.number_of_blades = 2.0
prop.freestream_velocity = 15.0 # freestream m/s
prop.angular_velocity = 7500. * Units['rpm']
prop.tip_radius = 4. * Units.inch
prop.hub_radius = 0.125 * Units.inch
prop.design_Cl = 0.7
prop.design_altitude = 0.1 * Units.km
prop.design_power = 200. * Units.watts
prop = propeller_design(prop)
origins = [[0., 0.15, -0.05], [0., -0.15, -0.05], [0., .35, 0.05], [0., 0.35, 0.05]]
for ii in range(4):
rotor = deepcopy(prop)
rotor.tag = 'propeller'
rotor.origin = [origins[ii]]
net.propellers.append(rotor)
# Component 3 the Motor
motor = SUAVE.Components.Energy.Converters.Motor()
motor.speed_constant = 1500. * Units['rpm'] # RPM/volt converted to (rad/s)/volt
motor = size_from_kv(motor)
motor.gear_ratio = 1. # Gear ratio
motor.gearbox_efficiency = 1. # Gear box efficiency
motor.expected_current = 10. # Expected current
motor.propeller_radius = prop.tip_radius
for ii in range(4):
rotor_motor = deepcopy(motor)
rotor_motor.tag = 'motor'
rotor_motor.origin = [origins[ii]]
net.propeller_motors.append(rotor_motor)
# Component 4 the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 0. #Watts
payload.mass_properties.mass = 0.0 * Units.kg
net.payload = payload
# Component 5 the Avionics
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 2. #Watts
net.avionics = avionics
# Component 6 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion()
bat.mass_properties.mass = 0.17 * Units.kg
bat.specific_energy = 175.*Units.Wh/Units.kg
bat.resistance = 0.003
bat.max_voltage = 11.1
initialize_from_mass(bat)
net.battery = bat
# add the solar network to the vehicle
vehicle.append_component(net)
return vehicle
def main():
#------------------------------------------------------------------
# Propulsor
#------------------------------------------------------------------
# build network
net = Solar_Low_Fidelity()
net.number_of_engines = 1.
net.nacelle_diameter = 0.05
net.areas = Data()
net.areas.wetted = 0.01*(2*np.pi*0.01/2)
net.engine_length = 0.01
# Component 1 the Sun
sun = SUAVE.Components.Energy.Processes.Solar_Radiation()
net.solar_flux = sun
# Component 2 the solar panels
panel = SUAVE.Components.Energy.Converters.Solar_Panel()
panel.ratio = 0.9
panel.area = 1.0 * panel.ratio
panel.efficiency = 0.25
panel.mass_properties.mass = panel.area*(0.60 * Units.kg)
net.solar_panel = panel
# Component 3 the ESC
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95 # Gundlach for brushless motors
net.esc = esc
# Component 5 the Propeller
prop = SUAVE.Components.Energy.Converters.Propeller_Lo_Fid()
prop.propulsive_efficiency = 0.825
net.propeller = prop
# Component 4 the Motor
motor = SUAVE.Components.Energy.Converters.Motor_Lo_Fid()
kv = 800. * Units['rpm/volt'] # RPM/volt is standard
motor = size_from_kv(motor, kv)
motor.gear_ratio = 1. # Gear ratio, no gearbox
motor.gearbox_efficiency = 1. # Gear box efficiency, no gearbox
motor.motor_efficiency = 0.825;
net.motor = motor
# Component 6 the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 0. #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 = 10. #Watts
net.avionics = avionics
# Component 8 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion()
bat.mass_properties.mass = 5.0 * Units.kg
bat.specific_energy = 250. *Units.Wh/Units.kg
bat.resistance = 0.003
bat.iters = 0
initialize_from_mass(bat,bat.mass_properties.mass)
net.battery = bat
#Component 9 the system logic controller and MPPT
logic = SUAVE.Components.Energy.Distributors.Solar_Logic()
logic.system_voltage = 18.5
logic.MPPT_efficiency = 0.95
net.solar_logic = logic
# Setup the conditions to run the network
state = Data()
state.conditions = SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics()
state.numerics = SUAVE.Analyses.Mission.Segments.Conditions.Numerics()
conditions = state.conditions
numerics = state.numerics
# Calculate atmospheric properties
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmosphere_conditions = atmosphere.compute_values(1000.*Units.ft)
rho = atmosphere_conditions.density[0,:]
a = atmosphere_conditions.speed_of_sound[0,:]
mu = atmosphere_conditions.dynamic_viscosity[0,:]
T = atmosphere_conditions.temperature[0,:]
conditions.propulsion.throttle = np.array([[1.0],[1.0]])
conditions.freestream.velocity = np.array([[1.0],[1.0]])
conditions.freestream.density = np.array([rho,rho])
conditions.freestream.dynamic_viscosity = np.array([mu, mu])
conditions.freestream.speed_of_sound = np.array([a, a])
conditions.freestream.altitude = np.array([[1000.0],[1000.0]])
conditions.propulsion.battery_energy = bat.max_energy*np.ones_like(conditions.freestream.altitude)
conditions.frames.body.inertial_rotations = np.zeros([2,3])
conditions.frames.inertial.time = np.array([[0.0],[1.0]])
numerics.time.integrate = np.array([[0, 0],[0, 1]])
numerics.time.differentiate = np.array([[0, 0],[0, 1]])
conditions.frames.planet.start_time = time.strptime("Sat, Jun 21 06:00:00 2014", "%a, %b %d %H:%M:%S %Y",)
conditions.frames.planet.latitude = np.array([[0.0],[0.0]])
conditions.frames.planet.longitude = np.array([[0.0],[0.0]])
conditions.freestream.temperature = np.array([T, T])
conditions.frames.body.transform_to_inertial = np.array([[[ 1., 0., 0.],
[ 0., 1., 0.],
[ 0., 0., 1.]],
[[ 1., 0., 0.],
[ 0., 1., 0.],
[ 0., 0., 1.]]])
# Run the network and print the results
results = net(state)
F = results.thrust_force_vector
# Truth results
truth_F = [[ 68.78277813 ], [ 68.78277813 ]]
truth_i = [[ 5.75011436 ], [ 5.75011436 ]]
truth_rpm = [[ 14390.30435183], [ 14390.30435183 ]]
truth_bat = [[ 4500000. ], [ 4499883.5041616 ]]
error = Data()
error.Thrust = np.max(np.abs(F[:,0]-truth_F))
error.RPM = np.max(np.abs(conditions.propulsion.rpm-truth_rpm))
error.Current = np.max(np.abs(conditions.propulsion.current-truth_i))
error.Battery = np.max(np.abs(bat.current_energy-truth_bat))
print(error)
for k,v in list(error.items()):
assert(np.abs(v)<1e-6)
return
def base_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Solar'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 6.75 * Units.kg
vehicle.mass_properties.operating_empty = 6.75 * Units.kg
vehicle.mass_properties.max_takeoff = 6.75 * Units.kg
# basic parameters
vehicle.reference_area = 1.0
vehicle.envelope.ultimate_load = 2.0
vehicle.envelope.limit_load = 1.5
vehicle.envelope.maximum_dynamic_pressure = 115.*1.25 * Units.pascals #Max q
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.areas.reference = vehicle.reference_area
wing.spans.projected = 40.0 * Units.meters
wing.aspect_ratio = (wing.spans.projected**2)/wing.areas.reference
wing.sweeps.quarter_chord = 0.0 * Units.deg
wing.symmetric = True
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.vertical = False
wing.high_lift = True
wing.dynamic_pressure_ratio = 1.0
wing.chords.mean_aerodynamic = wing.areas.reference/wing.spans.projected
wing.span_efficiency = 0.98
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.highlift = False
wing.vertical = False
wing.number_ribs = 26.
wing.number_end_ribs = 2.
wing.transition_x_upper = 0.6
wing.transition_x_lower = 1.0
wing.origin = [3.0,0.0,0.0]
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 10.
wing.sweeps.quarter_chord = 0 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.span_efficiency = 0.95
wing.areas.reference = vehicle.reference_area * .15
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.spans.projected = np.sqrt(wing.aspect_ratio*wing.areas.reference)
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.vertical = False
wing.symmetric = True
wing.dynamic_pressure_ratio = 0.9
wing.number_ribs = 5.0
wing.chords.root = wing.areas.reference/wing.spans.projected
wing.chords.tip = wing.areas.reference/wing.spans.projected
wing.chords.mean_aerodynamic = wing.areas.reference/wing.spans.projected
wing.origin = [10.,0.0,0.0]
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 10.
wing.sweeps.quarter_chord = 0 * Units.deg
wing.thickness_to_chord = 0.12
wing.taper = 1.0
wing.span_efficiency = 0.97
wing.areas.reference = vehicle.reference_area * 0.1
wing.spans.projected = np.sqrt(wing.aspect_ratio*wing.areas.reference)
wing.chords.root = wing.areas.reference/wing.spans.projected
wing.chords.tip = wing.areas.reference/wing.spans.projected
wing.chords.mean_aerodynamic = wing.areas.reference/wing.spans.projected
wing.areas.wetted = 2.0 * wing.areas.reference
wing.areas.exposed = 0.8 * wing.areas.wetted
wing.areas.affected = 0.6 * wing.areas.wetted
wing.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [10.,0.0,0.0]
wing.symmetric = True
wing.vertical = True
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
wing.number_ribs = 5.
# add to vehicle
vehicle.append_component(wing)
#------------------------------------------------------------------
# Propulsor
#------------------------------------------------------------------
# build network
net = Solar_Low_Fidelity()
net.number_of_engines = 1.
net.nacelle_diameter = 0.05
net.areas = Data()
net.areas.wetted = 0.01*(2*np.pi*0.01/2)
net.engine_length = 0.01
# Component 1 the Sun
sun = SUAVE.Components.Energy.Processes.Solar_Radiation()
net.solar_flux = sun
# Component 2 the solar panels
panel = SUAVE.Components.Energy.Converters.Solar_Panel()
panel.ratio = 0.9
panel.area = vehicle.reference_area * panel.ratio
panel.efficiency = 0.25
panel.mass_properties.mass = panel.area*(0.60 * Units.kg)
net.solar_panel = panel
# Component 3 the ESC
esc = SUAVE.Components.Energy.Distributors.Electronic_Speed_Controller()
esc.efficiency = 0.95 # Gundlach for brushless motors
net.esc = esc
# Component 5 the Propeller
prop = SUAVE.Components.Energy.Converters.Propeller_Lo_Fid()
prop.propulsive_efficiency = 0.825
net.propeller = prop
# Component 4 the Motor
motor = SUAVE.Components.Energy.Converters.Motor_Lo_Fid()
kv = 800. * Units['rpm/volt'] # RPM/volt is standard
motor = size_from_kv(motor, kv)
motor.gear_ratio = 1. # Gear ratio, no gearbox
motor.gearbox_efficiency = 1. # Gear box efficiency, no gearbox
motor.motor_efficiency = 0.825;
net.motor = motor
# Component 6 the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 0. #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 = 10. #Watts
net.avionics = avionics
# Component 8 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion()
bat.mass_properties.mass = 5.0 * Units.kg
bat.specific_energy = 250. *Units.Wh/Units.kg
bat.resistance = 0.003
bat.iters = 0
initialize_from_mass(bat,bat.mass_properties.mass)
net.battery = bat
#Component 9 the system logic controller and MPPT
logic = SUAVE.Components.Energy.Distributors.Solar_Logic()
logic.system_voltage = 18.5
logic.MPPT_efficiency = 0.95
net.solar_logic = logic
# add the solar network to the vehicle
vehicle.append_component(net)
return vehicle
