コード例 #1
0
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
コード例 #2
0
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
コード例 #3
0
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
コード例 #4
0

#-----------------------------------------------------------------------------------------------------------
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)
コード例 #5
0
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
#======================================================================================================
コード例 #6
0
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
コード例 #7
0
def diversion_range():
    diversion_range = unit.m_NM(200)
    return diversion_range
コード例 #8
0
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
#======================================================================================================

#------------------------------------------------------------------------------------------------------
コード例 #9
0
def utilisation(design_range):
    if(design_range <= unit.m_NM(3500)): utilisation_i = 1600
    else:                                utilisation_i = 600
    return utilisation_i
コード例 #10
0
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
コード例 #11
0
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
#======================================================================================================

#------------------------------------------------------------------------------------------------------
コード例 #12
0
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
#======================================================================================================
コード例 #13
0
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
#======================================================================================================

#------------------------------------------------------------------------------------------------------