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)