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