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 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 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 diversion_range():
diversion_range = unit.m_NM(200)
return diversion_range
"""
from MARILib.tools import units as unit
from MARILib.earth import environment as earth
from MARILib.airplane.propulsion import propulsion_models as propu
from MARILib.aircraft_data.aircraft_description import Aircraft
from MARILib.processes import design as run
from MARILib.aircraft_model.airplane import viewer as show
# Initialize aircraft data structure
#------------------------------------------------------------------------------------------------------
aircraft = Aircraft()
design_range = unit.m_NM(3000)
cruise_mach = 0.78
n_pax_ref = 150
propulsion_architecture = 3
n_engine = 2
# Initialize all input data
#------------------------------------------------------------------------------------------------------
run.aircraft_initialize(aircraft, n_pax_ref, design_range, cruise_mach,
propulsion_architecture, n_engine)
# Possibility to modify initial values
#------------------------------------------------------------------------------------------------------
study_name = "This airplane"
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(500)
else: cost_mission_range_i = unit.m_NM(4000)
return cost_mission_range_i
"""
Created on Thu Jan 24 23:22:21 2019
@author: DRUOT Thierry
"""
from MARILib.tools import units as unit
from MARILib.aircraft_data.aircraft_description import Aircraft
from MARILib.processes import design as perform
from MARILib.aircraft_model.operations.handling_qualities import vertical_tail_sizing
from MARILib.aircraft_model.airplane import viewer as show
# Initialize aircraft data structure
#---------------------------------------------------------------------------
aircraft = Aircraft()
design_range = unit.m_NM(3000)
cruise_mach = 0.78
n_pax_ref = 150
propu_config = 1
n_engine = 2
perform.aircraft_initialize(aircraft, n_pax_ref, design_range, cruise_mach,
propu_config, n_engine)
aircraft.turbofan_engine.reference_thrust = 130000 # Newtons
aircraft.wing.area = 155 # m2
aircraft.wing.aspect_ratio = 9 # m2
aircraft.weights.mtow = 77000 # kg
aircraft.cost_mission.range = unit.m_NM(500)
