def m_pax_max(design_range):
if(design_range <= unit.m_NM(3500)):
m_pax_max_i = 120
elif(design_range <= unit.m_NM(5500)):
m_pax_max_i = 135
else:
m_pax_max_i = 150
return m_pax_max_i
def req_tofl(design_range):
if(design_range <= unit.m_NM(3500)):
req_tofl_i = 2000
elif(design_range <= unit.m_NM(5500)):
req_tofl_i = 2500
else:
req_tofl_i = 3000
return req_tofl_i
def m_pax_nominal(design_range):
if(design_range <= unit.m_NM(3500)):
m_pax_nominal_i = 100
elif(design_range <= unit.m_NM(5500)):
m_pax_nominal_i = 105
else:
m_pax_nominal_i = 110
return m_pax_nominal_i
#-----------------------------------------------------------------------------------------------------------
def criteria(aircraft):
eval_co2_metric(aircraft)
eval_cost_mission(aircraft)
eval_economics(aircraft)
return
# Initialize aircraft data structure
#---------------------------------------------------------------------------
aircraft = Aircraft()
n_pax_ref = 150 # Reference number of passengers
design_range = unit.m_NM(3000) # Design range
cruise_mach = 0.78 # Nominal cruise mach number
propu_config = 1 # 1: turbofan, 2: partial turbo electric
n_engine = 2 # Number of engine
aircraft_initialization(aircraft, n_pax_ref, design_range, cruise_mach,
propu_config, n_engine)
fuselage_design(aircraft)
predesign_initialization(aircraft)
lifting_plane_design(aircraft)
propulsion(aircraft)
from marilib.aircraft_model.airplane import viewer as show
from marilib.aircraft_data.aircraft_description import Aircraft
from marilib.processes import assembly as run, initialization as init
#======================================================================================================
# Initialization
#======================================================================================================
propulsive_architecture = 1 # 1:turbofan, 2:partial turboelectric
aircraft = Aircraft(propulsive_architecture)
n_pax_ref = 300
design_range = unit.m_NM(8000)
cruise_mach = 0.85
number_of_engine = init.n_engine()
#------------------------------------------------------------------------------------------------------
run.aircraft_initialize(aircraft, n_pax_ref, design_range, cruise_mach,
propulsive_architecture, number_of_engine)
print("-------------------------------------------")
print("Initialization : done")
#======================================================================================================
# Modify initial values here
#======================================================================================================
def reserve_fuel_ratio(design_range):
if (design_range < unit.m_NM(6500)):
reserve_fuel_ratio = 0.05
else:
reserve_fuel_ratio = 0.03
return reserve_fuel_ratio
def diversion_range():
diversion_range = unit.m_NM(200)
return diversion_range
from marilib.aircraft_model.airplane import viewer as show
from marilib.aircraft_data.aircraft_description import Aircraft
from marilib.processes import assembly as run, initialization as init
#======================================================================================================
# Initialization
#======================================================================================================
propulsive_architecture = 1 # 1:turbofan, 2:partial turboelectric
aircraft = Aircraft(propulsive_architecture)
n_pax_ref = 280
design_range = unit.m_NM(6100)
cruise_mach = 0.82
number_of_engine = init.n_engine()
#------------------------------------------------------------------------------------------------------
run.aircraft_initialize(aircraft, n_pax_ref, design_range, cruise_mach, propulsive_architecture, number_of_engine)
print("-------------------------------------------")
print("Initialization : done")
#======================================================================================================
# Design process
#======================================================================================================
#------------------------------------------------------------------------------------------------------
def utilisation(design_range):
if(design_range <= unit.m_NM(3500)): utilisation_i = 1600
else: utilisation_i = 600
return utilisation_i
def cost_mission_range(design_range):
if(design_range < unit.m_NM(4500)): cost_mission_range_i = unit.m_NM(800)
elif(design_range < unit.m_NM(6500)): cost_mission_range_i = unit.m_NM(2000)
else: cost_mission_range_i = unit.m_NM(4000)
return cost_mission_range_i
from marilib.aircraft_model.airplane import viewer as show
from marilib.aircraft_data.aircraft_description import Aircraft
from marilib.processes import assembly as run
#======================================================================================================
# Initialization
#======================================================================================================
propulsive_architecture = 1 # 1:turbofan, 2:partial turboelectric
aircraft = Aircraft(propulsive_architecture)
n_pax_ref = 290
design_range = unit.m_NM(7400)
cruise_mach = 0.82
number_of_engine = 4
#------------------------------------------------------------------------------------------------------
run.aircraft_initialize(aircraft, n_pax_ref, design_range, cruise_mach, propulsive_architecture, number_of_engine)
print("-------------------------------------------")
print("Initialization : done")
#======================================================================================================
# Design process
#======================================================================================================
#------------------------------------------------------------------------------------------------------
from marilib.aircraft_model.airplane import viewer as show
from marilib.aircraft_data.aircraft_description import Aircraft
from marilib.processes import assembly as run, initialization as init
#======================================================================================================
# Initialization
#======================================================================================================
propulsive_architecture = 1 # 1:turbofan, 2:partial turboelectric
aircraft = Aircraft(propulsive_architecture)
n_pax_ref = 8
design_range = unit.m_NM(3300)
cruise_mach = 0.79
number_of_engine = init.n_engine()
#------------------------------------------------------------------------------------------------------
run.aircraft_initialize(aircraft, n_pax_ref, design_range, cruise_mach,
propulsive_architecture, number_of_engine)
print("-------------------------------------------")
print("Initialization : done")
#======================================================================================================
# Design process
#======================================================================================================
from marilib.aircraft_model.airplane import viewer as show
from marilib.aircraft_data.aircraft_description import Aircraft
from marilib.processes import assembly as run, initialization as init
#======================================================================================================
# Initialization
#======================================================================================================
propulsive_architecture = 1 # 1:turbofan, 2:partial turboelectric
aircraft = Aircraft(propulsive_architecture)
n_pax_ref = 110
design_range = unit.m_NM(3100)
cruise_mach = 0.78
number_of_engine = init.n_engine()
#------------------------------------------------------------------------------------------------------
run.aircraft_initialize(aircraft, n_pax_ref, design_range, cruise_mach, propulsive_architecture, number_of_engine)
print("-------------------------------------------")
print("Initialization : done")
#======================================================================================================
# Design process
#======================================================================================================
#------------------------------------------------------------------------------------------------------
