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 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 main():
# vehicle data
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# vehicle analyses
configs_analyses = analyses_setup(configs)
# mission analyses
mission = mission_setup(configs_analyses, vehicle)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
configs.finalize()
analyses.finalize()
# weight analysis
weights = analyses.configs.base.weights
# mission analysis
mission = analyses.missions.base
results = mission.evaluate()
# load older results
#save_results(results)
old_results = load_results()
## plt the old results
plot_mission(results)
plot_mission(old_results, 'k-')
# Check Results
F = results.segments.cruise1.conditions.frames.body.thrust_force_vector[1,
0]
rpm = results.segments.cruise1.conditions.propulsion.propeller_rpm[1, 0]
current = results.segments.cruise1.conditions.propulsion.battery_current[1,
0]
energy = results.segments.cruise1.conditions.propulsion.battery_energy[8,
0]
# Truth results
truth_F = 105.36115293829462
truth_rpm = 218.18739964349612
truth_i = 130.17994767726535
truth_bat = 136584698.345862
print('battery energy')
print(energy)
print('\n')
error = Data()
error.Thrust = np.max(np.abs((F - truth_F) / truth_F))
error.RPM = np.max(np.abs((rpm - truth_rpm) / truth_rpm))
error.Current = np.max(np.abs((current - truth_i) / truth_i))
error.Battery = np.max(np.abs((energy - truth_bat) / truth_bat))
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1e-6)
# Plot vehicle
plot_vehicle(configs.cruise, save_figure=False, plot_control_points=True)
return
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 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
def main():
# vehicle data
vehicle = vehicle_setup()
configs = configs_setup(vehicle)
# vehicle analyses
configs_analyses = analyses_setup(configs)
# mission analyses
mission = mission_setup(configs_analyses, vehicle)
missions_analyses = missions_setup(mission)
analyses = SUAVE.Analyses.Analysis.Container()
analyses.configs = configs_analyses
analyses.missions = missions_analyses
configs.finalize()
analyses.finalize()
# weight analysis
weights = analyses.configs.base.weights
# mission analysis
mission = analyses.missions.base
results = mission.evaluate()
# load older results
#save_results(results)
old_results = load_results()
# plt the old results
plot_mission(results)
plot_mission(old_results, 'k-')
# Check Results
F = results.segments.cruise1.conditions.frames.body.thrust_force_vector[1,
0]
rpm = results.segments.cruise1.conditions.propulsion.rpm[1, 0]
current = results.segments.cruise1.conditions.propulsion.current[1, 0]
energy = results.segments.cruise1.conditions.propulsion.battery_energy[8,
0]
# Truth results
truth_F = 105.9739169506257
truth_rpm = 214.27179253741863
truth_i = 178.88932733145853
truth_bat = 187815498.6290547
print('battery energy')
print(energy)
print('\n')
error = Data()
error.Thrust = np.max(np.abs((F - truth_F) / truth_F))
error.RPM = np.max(np.abs((rpm - truth_rpm) / truth_rpm))
error.Current = np.max(np.abs((current - truth_i) / truth_i))
error.Battery = np.max(np.abs((energy - truth_bat) / truth_bat))
print(error)
for k, v in list(error.items()):
assert (np.abs(v) < 1e-6)
return
