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manx.py
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manx.py
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# manx_test_1.py
#
# Created: Feb 2024, O.N Afify
# Modified: ------
#----------------------------------------------------------------------
# Imports
# ----------------------------------------------------------------------
import SUAVE
from SUAVE.Core import Units
import sys,os
import pylab as plt
import time
from SUAVE.Plots.Performance.Mission_Plots import *
from SUAVE.Components.Energy.Networks.Battery_Propeller import Battery_Propeller
from SUAVE.Methods.Propulsion import propeller_design
from SUAVE.Methods.Geometry.Two_Dimensional.Planform import segment_properties
from SUAVE.Methods.Power.Battery.Sizing import initialize_from_mass
from SUAVE.Methods.Propulsion.electric_motor_sizing import size_from_kv
# ----------------------------------------------------------------------
# Main
# ----------------------------------------------------------------------
def main():
# build the vehicle, configs, and analyses
configs, analyses = full_setup()
configs.finalize()
analyses.finalize()
# weight analysis
weights = analyses.configs.base.weights
breakdown = weights.evaluate()
# mission analysis
mission = analyses.missions.base
results = mission.evaluate()
# plot results
plot_mission(results)
return
# ----------------------------------------------------------------------
# Analysis Setup
# ----------------------------------------------------------------------
def full_setup():
# 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
return configs, analyses
# ----------------------------------------------------------------------
# Build the Vehicle
# ----------------------------------------------------------------------
def vehicle_setup():
# ------------------------------------------------------------------
# Initialize the Vehicle
# ------------------------------------------------------------------
vehicle = SUAVE.Vehicle()
vehicle.tag = 'manx'
# ------------------------------------------------------------------
# Vehicle-level Properties
# ------------------------------------------------------------------
# mass properties
vehicle.mass_properties.takeoff = 3.23 * Units.kg
vehicle.mass_properties.operating_empty = 3.23 * Units.kg
vehicle.mass_properties.max_takeoff = 3.23 * Units.kg
# basic parameters
vehicle.reference_area = 0.594 * Units.meter**2
vehicle.envelope.maximum_dynamic_pressure = 0.5*1.225*(12**2.) #Max q
# ------------------------------------------------------------------
# Main Wing
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Main_Wing()
wing.tag = 'main_wing'
wing.areas.reference = vehicle.reference_area
wing.spans.projected = 3. * Units.meter
wing.aspect_ratio = (wing.spans.projected**2)/wing.areas.reference
wing.sweeps.quarter_chord = 0.0 * Units.deg
wing.thickness_to_chord = 0.014
wing.taper = 0.48 # 0.6
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.twists.root = 0. * Units.degrees
wing.twists.tip = -1.5 * Units.degrees
wing.number_ribs = 32.
wing.number_end_ribs = 2.
wing.high_lift = False
wing.highlift = False
wing.vertical = False
wing.symmetric = True
wing.origin = [[0.12,0.0,0.0]] # meters from nose
wing.aerodynamic_center = [0.075,0.0,0.0] # meters from nose
print('Croot, Ctip: ',wing.chords.root,wing.chords.tip)
# Wing Segments
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Root'
segment.percent_span_location = 0.0
segment.twist = 1.5 * Units.degrees
segment.root_chord_percent = 1.
segment.thickness_to_chord = 0.014
segment.sweeps.quarter_chord = 0.
wing.append_segment(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Break1'
segment.percent_span_location = 0.083
segment.twist = 0. * Units.degrees
segment.root_chord_percent = 1.
segment.thickness_to_chord = 0.014
segment.sweeps.quarter_chord = 0.
wing.append_segment(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Break2'
segment.percent_span_location = 0.43
segment.twist = 0. * Units.degrees
segment.root_chord_percent = 0.94
segment.thickness_to_chord = 0.015
segment.sweeps.quarter_chord = 0.
wing.append_segment(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Break3'
segment.percent_span_location = 0.8
segment.twist = 0. * Units.degrees
segment.root_chord_percent = 0.65
segment.thickness_to_chord = 0.021
segment.sweeps.quarter_chord = 0.
wing.append_segment(segment)
segment = SUAVE.Components.Wings.Segment()
segment.tag = 'Tip'
segment.percent_span_location = 1.
segment.twist = -1.5 * Units.degrees
segment.root_chord_percent = 0.48
segment.thickness_to_chord = 0.029
segment.sweeps.quarter_chord = 0.
wing.append_segment(segment)
# Fills out more segment properties automatically
wing = segment_properties(wing)
wing = SUAVE.Methods.Geometry.Two_Dimensional.Planform.wing_planform(wing)
# add to vehicle
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Horizontal Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Horizontal_Tail()
wing.tag = 'horizontal_stabilizer'
wing.aspect_ratio = 4.87
wing.sweeps.quarter_chord = 0 * Units.deg
wing.thickness_to_chord = 0.027
wing.taper = 1.0
wing.areas.reference = 0.095 * Units.meter
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 = 11
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 = [[1.6,0.0,0.02]] # meters from nose
wing.aerodynamic_center = [0.05,0.0,0.0] # meters from nose
print('Croot, Ctip: ',wing.chords.root,wing.chords.tip)
#sys.exit()
# add to vehicle
wing = SUAVE.Methods.Geometry.Two_Dimensional.Planform.wing_planform(wing)
vehicle.append_component(wing)
# ------------------------------------------------------------------
# Vertical Stabilizer
# ------------------------------------------------------------------
wing = SUAVE.Components.Wings.Vertical_Tail()
wing.tag = 'vertical_stabilizer'
wing.aspect_ratio = 1.458
wing.sweeps.quarter_chord = 0 * Units.deg
wing.thickness_to_chord = 0.038
wing.taper = 1.0
wing.areas.reference = 0.032 * Units.meter
wing.spans.projected = np.sqrt(wing.aspect_ratio*wing.areas.reference)
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.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.twists.root = 0.0 * Units.degrees
wing.twists.tip = 0.0 * Units.degrees
wing.origin = [[1.45,0.01,0.0]] # meters from nose
wing.aerodynamic_center = [0.0325,0.0,0.0] # meters from nose
wing.symmetric = True
wing.vertical = True
wing.t_tail = False
wing.dynamic_pressure_ratio = 1.0
wing.number_ribs = 7.
# add to vehicle
wing = SUAVE.Methods.Geometry.Two_Dimensional.Planform.wing_planform(wing)
vehicle.append_component(wing)
#------------------------------------------------------------------
# Propulsor - Battery_Propeller
#------------------------------------------------------------------
# build network
net = SUAVE.Components.Energy.Networks.Battery_Propeller()
net.number_of_propeller_engines = 2.
net.voltage = 11.1
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 = 12. * Units['m/s']# freestream 10.12
prop.angular_velocity = 5000 * Units['rpm'] # 9X6 APC Prop ;1984.45, 548.63, 2553
prop.tip_radius = 4.5 * Units.inches
prop.hub_radius = 0.4 * Units.inches
prop.design_Cl = 0.7
prop.design_altitude = 0.12 * Units.km
prop.design_power = None
prop.design_thrust = 2. # CHECK CHANGED 12
prop = propeller_design(prop)
origins = [[0.12, 0.45, 0.], [0.12, -0.45, 0.]] # From the nose
#for ii in range(2):
#rotor = deepcopy(prop)
#rotor.tag = 'propeller'
#rotor.origin = [origins[ii]]
#net.propellers.append(rotor)
net.propellers.append(prop) # Check if propeller polars are necessary
# Component 3 the Motor
motor = SUAVE.Components.Energy.Converters.Motor()
motor.resistance = 0.0075
motor.no_load_current = 0.85 * Units.ampere
motor.speed_constant = 1150 * Units['rpm/volt'] # RPM/volt converted to (rad/s)/volt change to 41.26 , 82.2
motor = size_from_kv(motor)
motor.propeller_radius = prop.tip_radius
motor.propeller_Cp = prop.design_power_coefficient
motor.gear_ratio = 1. # Gear ratio
motor.gearbox_efficiency = 1. # Gear box efficiency
motor.expected_current = 25. * Units.ampere # Expected current
motor.mass_properties.mass = 0.06 * Units.kg
net.propeller_motors.append(motor)
# Component 4 the Payload
payload = SUAVE.Components.Energy.Peripherals.Payload()
payload.power_draw = 0. * Units.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 = 1. #Watts
net.avionics = avionics
# Component 8 the Battery
bat = SUAVE.Components.Energy.Storages.Batteries.Constant_Mass.Lithium_Ion()
bat.mass_properties.mass = 1.186 * Units.kg #
bat.specific_energy = 187.18 * Units.Wh/Units.kg
bat.max_voltage = 11.1
initialize_from_mass(bat,bat.mass_properties.mass)
net.battery = bat
# add the battery network to the vehicle
vehicle.append_component(net)
return vehicle
# ----------------------------------------------------------------------
# Define the Configurations
# ---------------------------------------------------------------------
def configs_setup(vehicle):
# ------------------------------------------------------------------
# Initialize Configurations
# ------------------------------------------------------------------
configs = SUAVE.Components.Configs.Config.Container()
base_config = SUAVE.Components.Configs.Config(vehicle)
base_config.tag = 'base'
configs.append(base_config)
# ------------------------------------------------------------------
# Cruise Configuration
# ------------------------------------------------------------------
config = SUAVE.Components.Configs.Config(base_config)
config.tag = 'cruise'
configs.append(config)
return configs
# ----------------------------------------------------------------------
# Define the Vehicle Analyses
# ----------------------------------------------------------------------
def analyses_setup(configs):
analyses = SUAVE.Analyses.Analysis.Container()
# build a base analysis for each config
for tag,config in configs.items():
analysis = base_analysis(config)
analyses[tag] = analysis
return analyses
def base_analysis(vehicle):
# ------------------------------------------------------------------
# Initialize the Analyses
# ------------------------------------------------------------------
analyses = SUAVE.Analyses.Vehicle()
# ------------------------------------------------------------------
# Basic Geometry Relations
sizing = SUAVE.Analyses.Sizing.Sizing()
analyses.append(sizing)
# ------------------------------------------------------------------
# Weights
weights = SUAVE.Analyses.Weights.Weights_UAV()
weights.settings.empty = \
SUAVE.Methods.Weights.Correlations.Human_Powered.empty
weights.vehicle = vehicle
analyses.append(weights)
# ------------------------------------------------------------------
# Aerodynamics Analysis
aerodynamics = SUAVE.Analyses.Aerodynamics.Fidelity_Zero()
aerodynamics.geometry = vehicle
aerodynamics.settings.drag_coefficient_increment = 0.0000
analyses.append(aerodynamics)
# ------------------------------------------------------------------
# Energy
energy = SUAVE.Analyses.Energy.Energy()
energy.network = vehicle.networks #what is called throughout the mission (at every time step))
analyses.append(energy)
# ------------------------------------------------------------------
# Planet Analysis
planet = SUAVE.Analyses.Planets.Planet()
analyses.append(planet)
# ------------------------------------------------------------------
# Atmosphere Analysis
atmosphere = SUAVE.Analyses.Atmospheric.US_Standard_1976()
atmosphere.features.planet = planet.features
analyses.append(atmosphere)
# done!
return analyses
# ----------------------------------------------------------------------
# Define the Mission
# ----------------------------------------------------------------------
def mission_setup(analyses,vehicle):
# ------------------------------------------------------------------
# Initialize the Mission
# ------------------------------------------------------------------
mission = SUAVE.Analyses.Mission.Sequential_Segments()
mission.tag = 'The Test Mission'
mission.atmosphere = SUAVE.Attributes.Atmospheres.Earth.US_Standard_1976()
mission.planet = SUAVE.Attributes.Planets.Earth()
# unpack Segments module
Segments = SUAVE.Analyses.Mission.Segments
# base segment
base_segment = Segments.Segment()
base_segment.process.iterate.initials.initialize_battery = SUAVE.Methods.Missions.Segments.Common.Energy.initialize_battery
# ------------------------------------------------------------------
# Cruise Segment: constant speed, constant altitude
# ------------------------------------------------------------------
segment = SUAVE.Analyses.Mission.Segments.Cruise.Constant_Mach_Constant_Altitude(base_segment)
segment.tag = "Cruise"
# connect vehicle configuration
segment.analyses.extend(analyses.cruise)
# segment attributes
segment.state.numerics.number_control_points = 32 # 4, 8 or 16.
segment.start_time = time.strptime("Tue, May 02 11:30:00 2023", "%a, %b %d %H:%M:%S %Y",) # Manx first flight.
segment.battery_energy = vehicle.networks.battery_propeller.battery.max_energy*0.3
segment.mach = 0.03
segment.distance = 3. * Units.km
segment.air_speed = 12. * Units['m/s']
segment.altitude = 0.12 * Units.km
segment.latitude = 51. # do not use Units.degrees
segment.longitude = 0. # this defaults to degrees
segment = vehicle.networks.battery_propeller.add_unknowns_and_residuals_to_segment(segment,\
initial_power_coefficient = 0.08)
mission.append_segment(segment)
# ------------------------------------------------------------------
# Mission definition complete
# ------------------------------------------------------------------
return mission
def missions_setup(base_mission):
# the mission container
missions = SUAVE.Analyses.Mission.Mission.Container()
# ------------------------------------------------------------------
# Base Mission
# ------------------------------------------------------------------
missions.base = base_mission
# done!
return missions
# ----------------------------------------------------------------------
# Plot Results
# ----------------------------------------------------------------------
def plot_mission(results):
# Plot Flight Conditions
plot_flight_conditions(results)
# Plot Aerodynamic Coefficients
plot_aerodynamic_coefficients(results)
# Drag Components
plot_drag_components(results)
# Plot Aircraft Flight Speed
plot_aircraft_velocities(results)
# Plot Aircraft Electronics
plot_battery_pack_conditions(results)
plot_battery_cell_conditions(results)
# Plot Propeller Conditions
plot_propeller_conditions(results)
# Plot Electric Motor and Propeller Efficiencies
plot_eMotor_Prop_efficiencies(results)
return
if __name__ == '__main__':
main()
plt.show()