def main():
# ------------------------------------------------------------------
# Propulsor
# ------------------------------------------------------------------
# build network
net = Solar()
net.number_of_engines = 1.
net.nacelle_dia = 0.2
# 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.area = 100 * Units.m
panel.efficiency = 0.18
panel.mass_properties.mass = panel.area * .600
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
# Propeller design specs
design_altitude = 0.0 * Units.km
Velocity = 10.0 # freestream m/s
RPM = 5887
Blades = 2.0
Radius = .4064
Hub_Radius = 0.05
Design_Cl = 0.7
Thrust = 0.0 #Specify either thrust or power to design for
Power = 7500. #Specify either thrust or power to design for
# Design the Propeller
prop_attributes = Data()
prop_attributes.number_blades = Blades
prop_attributes.freestream_velocity = Velocity
prop_attributes.angular_velocity = RPM * (2. * np.pi / 60.0)
prop_attributes.tip_radius = Radius
prop_attributes.hub_radius = Hub_Radius
prop_attributes.design_Cl = Design_Cl
prop_attributes.design_altitude = design_altitude
prop_attributes.design_thrust = Thrust
prop_attributes.design_power = Power
prop_attributes = propeller_design(prop_attributes)
# Create and attach this propeller
prop = SUAVE.Components.Energy.Converters.Propeller()
prop.prop_attributes = prop_attributes
net.propeller = prop
# Component 4 the Motor
motor = SUAVE.Components.Energy.Converters.Motor()
motor.resistance = 0.01
motor.no_load_current = 8.0
motor.speed_constant = 140. * (2. * np.pi / 60.
) # RPM/volt converted to rad/s
motor.propeller_radius = prop.prop_attributes.tip_radius
motor.propeller_Cp = prop.prop_attributes.Cp
motor.gear_ratio = 1.
motor.gearbox_efficiency = 1.
motor.expected_current = 260.
motor.mass_properties.mass = 2.0
net.motor = motor
# Component 6 the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 0. #Watts
payload.mass_properties.mass = 0. * Units.kg
net.payload = payload
# Component 7 the Avionics
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 0. #Watts
net.avionics = avionics
# Component 8 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion(
)
batterymass = 50. #kg
bat.type = 'Li-Ion'
bat.resistance = 0.0
bat.energy_density = 250.
initialize_from_mass(bat, batterymass)
bat.current_energy = bat.max_energy
net.battery = bat
#Component 9 the system logic controller and MPPT
logic = SUAVE.Components.Energy.Distributors.Solar_Logic()
logic.system_voltage = 50.0
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(
prop_attributes.design_altitude)
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([[design_altitude],
[design_altitude]])
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])
# Run the network and print the results
results = net(state)
F = results.thrust_force_vector
# Truth results
truth_F = [[522.40448791], [522.40448791]]
truth_i = [[314.90485916], [314.90485916]]
truth_rpm = [[6581.17653732], [6581.17653732]]
truth_bat = [[36000000.], [35984254.75704217]]
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 error.items():
assert (np.abs(v) < 0.001)
return
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Solar'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 200. * Units.kg
vehicle.mass_properties.operating_empty = 200. * Units.kg
vehicle.mass_properties.max_takeoff = 200. * Units.kg
# basic parameters
vehicle.reference_area = 80.
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
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.areas.reference = vehicle.reference_area
wing.spans.projected = 40.0 * Units.meter
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.chords.root = wing.areas.reference/wing.spans.projected
wing.chords.tip = 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] # meters
wing.aerodynamic_center = [3.0,0.0,0.0] # meters
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 20.
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] # meters
wing.aerodynamic_center = [0.5,0.0,0.0] # meters
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 20.
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] # meters
wing.aerodynamic_center = [0.5,0.0,0.0] # meters
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()
net.number_of_engines = 1.
net.nacelle_diameter = 0.2 * Units.meters
net.engine_length = 0.01 * Units.meters
net.areas = Data()
net.areas.wetted = 0.01*(2*np.pi*0.01/2.)
# 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.area = vehicle.reference_area * 0.9
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
# Design the Propeller
prop_attributes = Data()
prop_attributes.number_blades = 2.0
prop_attributes.freestream_velocity = 40.0 * Units['m/s']# freestream
prop_attributes.angular_velocity = 150. * Units['rpm']
prop_attributes.tip_radius = 4.25 * Units.meters
prop_attributes.hub_radius = 0.05 * Units.meters
prop_attributes.design_Cl = 0.7
prop_attributes.design_altitude = 14.0 * Units.km
prop_attributes.design_thrust = 0.0
prop_attributes.design_power = 3500.0 * Units.watts
prop_attributes = propeller_design(prop_attributes)
prop = SUAVE.Components.Energy.Converters.Propeller()
prop.prop_attributes = prop_attributes
net.propeller = prop
# Component 4 the Motor
motor = SUAVE.Components.Energy.Converters.Motor()
motor.resistance = 0.008
motor.no_load_current = 4.5 * Units.ampere
motor.speed_constant = 120. * Units['rpm'] # RPM/volt converted to (rad/s)/volt
motor.propeller_radius = prop.prop_attributes.tip_radius
motor.propeller_Cp = prop.prop_attributes.Cp
motor.gear_ratio = 12. # Gear ratio
motor.gearbox_efficiency = .98 # Gear box efficiency
motor.expected_current = 160. # Expected current
motor.mass_properties.mass = 2.0 * Units.kg
net.motor = motor
# Component 6 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 7 the Avionics
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 50. * Units.watts
net.avionics = avionics
# Component 8 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion()
bat.mass_properties.mass = 55.0 * Units.kg
bat.specific_energy = 450. * Units.Wh/Units.kg
bat.resistance = 0.05
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 = 40.0
logic.MPPT_efficiency = 0.95
net.solar_logic = logic
# add the solar network to the vehicle
vehicle.append_component(net)
return vehicle
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'Solar'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 200. * Units.kg
vehicle.mass_properties.operating_empty = 200. * Units.kg
vehicle.mass_properties.max_takeoff = 200. * Units.kg
# basic parameters
vehicle.reference_area = 80.
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
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'main_wing'
wing.areas.reference = vehicle.reference_area
wing.spans.projected = 40.0 * Units.meter
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.chords.root = wing.areas.reference / wing.spans.projected
wing.chords.tip = 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] # meters
wing.aerodynamic_center = [3.0, 0.0, 0.0] # meters
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 20.
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] # meters
wing.aerodynamic_center = [0.5, 0.0, 0.0] # meters
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Wing()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 20.
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] # meters
wing.aerodynamic_center = [0.5, 0.0, 0.0] # meters
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()
net.number_of_engines = 1.
net.nacelle_diameter = 0.2 * Units.meters
net.engine_length = 0.01 * Units.meters
net.areas = Data()
net.areas.wetted = 0.01 * (2 * np.pi * 0.01 / 2.)
# 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.area = vehicle.reference_area * 0.9
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
# Design the Propeller
prop_attributes = Data()
prop_attributes.number_blades = 2.0
prop_attributes.freestream_velocity = 40.0 * Units['m/s'] # freestream
prop_attributes.angular_velocity = 150. * Units['rpm']
prop_attributes.tip_radius = 4.25 * Units.meters
prop_attributes.hub_radius = 0.05 * Units.meters
prop_attributes.design_Cl = 0.7
prop_attributes.design_altitude = 14.0 * Units.km
prop_attributes.design_thrust = 0.0
prop_attributes.design_power = 3500.0 * Units.watts
prop_attributes = propeller_design(prop_attributes)
prop = SUAVE.Components.Energy.Converters.Propeller()
prop.prop_attributes = prop_attributes
net.propeller = prop
# Component 4 the Motor
motor = SUAVE.Components.Energy.Converters.Motor()
motor.resistance = 0.008
motor.no_load_current = 4.5 * Units.ampere
motor.speed_constant = 120. * Units[
'rpm'] # RPM/volt converted to (rad/s)/volt
motor.propeller_radius = prop.prop_attributes.tip_radius
motor.propeller_Cp = prop.prop_attributes.Cp
motor.gear_ratio = 12. # Gear ratio
motor.gearbox_efficiency = .98 # Gear box efficiency
motor.expected_current = 160. # Expected current
motor.mass_properties.mass = 2.0 * Units.kg
net.motor = motor
# Component 6 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 7 the Avionics
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 50. * Units.watts
net.avionics = avionics
# Component 8 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion(
)
bat.mass_properties.mass = 55.0 * Units.kg
bat.specific_energy = 450. * Units.Wh / Units.kg
bat.resistance = 0.05
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 = 40.0
logic.MPPT_efficiency = 0.95
net.solar_logic = logic
# add the solar network to the vehicle
vehicle.append_component(net)
return vehicle
def main():
# ------------------------------------------------------------------
# Propulsor
# ------------------------------------------------------------------
# build network
net = Solar()
net.number_of_engines = 1.
net.nacelle_dia = 0.2
# 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.area = 100 * Units.m
panel.efficiency = 0.18
panel.mass_properties.mass = panel.area*.600
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
# Propeller design specs
design_altitude = 0.0 * Units.km
Velocity = 10.0 # freestream m/s
RPM = 5887
Blades = 2.0
Radius = .4064
Hub_Radius = 0.05
Design_Cl = 0.7
Thrust = 0.0 #Specify either thrust or power to design for
Power = 7500. #Specify either thrust or power to design for
# Design the Propeller
prop_attributes = Data()
prop_attributes.number_blades = Blades
prop_attributes.freestream_velocity = Velocity
prop_attributes.angular_velocity = RPM*(2.*np.pi/60.0)
prop_attributes.tip_radius = Radius
prop_attributes.hub_radius = Hub_Radius
prop_attributes.design_Cl = Design_Cl
prop_attributes.design_altitude = design_altitude
prop_attributes.design_thrust = Thrust
prop_attributes.design_power = Power
prop_attributes = propeller_design(prop_attributes)
# Create and attach this propeller
prop = SUAVE.Components.Energy.Converters.Propeller()
prop.prop_attributes = prop_attributes
net.propeller = prop
# Component 4 the Motor
motor = SUAVE.Components.Energy.Converters.Motor()
motor.resistance = 0.01
motor.no_load_current = 8.0
motor.speed_constant = 140.*(2.*np.pi/60.) # RPM/volt converted to rad/s
motor.propeller_radius = prop.prop_attributes.tip_radius
#motor.propeller_Cp = prop.prop_attributes.Cp
motor.gear_ratio = 1.
motor.gearbox_efficiency = 1.
motor.expected_current = 260.
motor.mass_properties.mass = 2.0
net.motor = motor
# Component 6 the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 0. #Watts
payload.mass_properties.mass = 0. * Units.kg
net.payload = payload
# Component 7 the Avionics
avionics = SUAVE.Components.Energy.Peripherals.Avionics()
avionics.power_draw = 0. #Watts
net.avionics = avionics
# Component 8 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion()
batterymass = 50. #kg
bat.type = 'Li-Ion'
bat.resistance = 0.0
bat.energy_density = 250.
initialize_from_mass(bat,batterymass)
bat.current_energy = bat.max_energy
net.battery = bat
#Component 9 the system logic controller and MPPT
logic = SUAVE.Components.Energy.Distributors.Solar_Logic()
logic.system_voltage = 50.0
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(prop_attributes.design_altitude)
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([[design_altitude], [design_altitude]])
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.]]])
conditions.propulsion.propeller_power_coefficient = np.array([[1.], [1.]]) * prop.prop_attributes.Cp
# Run the network and print the results
results = net(state)
F = results.thrust_force_vector
# Truth results
truth_F = [[ 545.35952329, 545.35952329]]
truth_i = [[ 249.31622624], [ 249.31622624]]
truth_rpm = [[ 6668.4094191], [ 6668.4094191]]
truth_bat = [[ 36000000. ], [ 35987534.18868808]]
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