eval_landing_performances(aircraft)
eval_payload_range_analysis(aircraft)
return
#-----------------------------------------------------------------------------------------------------------
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)
from marilib.aircraft_model.operations import handling_qualities as h_q
from marilib.earth import environment as earth
from marilib.airplane.propulsion import jet_models as jet
from marilib.aircraft_model.airplane import viewer as show
#======================================================================================================
# Initialization
#======================================================================================================
propulsive_architecture = 2 # 1:turbofan, 2:partial turboelectric
number_of_engine = 2
aircraft = Aircraft(propulsive_architecture)
n_pax_ref = 150
design_range = unit.m_NM(3000)
cruise_mach = 0.78
#------------------------------------------------------------------------------------------------------
run.aircraft_initialize(aircraft, n_pax_ref, design_range, cruise_mach,
propulsive_architecture, number_of_engine)
#======================================================================================================
# Modify initial values here
#======================================================================================================
aircraft.turbofan_engine.reference_thrust = 118482.
aircraft.wing.area = 152.9