def fct_mass(x_in, aircraft):
ac = aircraft
ac.weights.mlw = x_in[0] # Coupling variable
ac.weights.mzfw = x_in[1] # Coupling variable
# Mass
#------------------------------------------------------------------------------------------------------
airframe.eval_cabin_mass(ac)
airframe.eval_fuselage_mass(ac)
airframe.eval_vtp_mass(ac)
airframe.eval_wing_mass(ac)
airframe.eval_htp_mass(ac)
airframe.eval_landing_gear_mass(ac)
propulsion.eval_propulsion_mass(ac)
propulsion.eval_battery_mass(ac)
propulsion.eval_tank_data(ac)
airplane.eval_system_mass(ac)
airplane.eval_payload_mass(ac)
airplane.eval_aircraft_weights(ac)
y_out = np.array([x_in[0] - ac.weights.mlw, \
x_in[1] - ac.weights.mzfw])
return y_out
def fct_mass_mission(x_in, aircraft):
ac = aircraft
ac.weights.mtow = x_in[0] # Coupling variable
ac.weights.mlw = x_in[1] # Coupling variable
ac.weights.mzfw = x_in[2] # Coupling variable
# Mass
#------------------------------------------------------------------------------------------------------
airframe.eval_cabin_mass(ac)
airframe.eval_fuselage_mass(ac)
airframe.eval_vtp_mass(ac)
airframe.eval_wing_mass(ac)
airframe.eval_htp_mass(ac)
airframe.eval_landing_gear_mass(ac)
propulsion.eval_propulsion_mass(ac)
propulsion.eval_battery_mass(ac)
propulsion.eval_tank_data(ac)
airplane.eval_system_mass(ac)
airplane.eval_payload_mass(ac)
airplane.eval_aircraft_weights(ac)
# Mission
#------------------------------------------------------------------------------------------------------
disa = 0
altp = ac.design_driver.ref_cruise_altp
mach = ac.design_driver.cruise_mach
ac.nominal_mission.payload = ac.payload.nominal
ac.nominal_mission.range = ac.design_driver.design_range
ac.nominal_mission.tow = ac.weights.mtow
payload = ac.nominal_mission.payload
range = ac.nominal_mission.range
tow = ac.nominal_mission.tow
block_fuel, block_time, total_fuel = perfo.mission(
ac, range, tow, altp, mach, disa)
ac.nominal_mission.block_fuel = block_fuel
ac.nominal_mission.block_time = block_time
ac.nominal_mission.total_fuel = total_fuel
required_mtow = ac.weights.owe + payload + total_fuel
y_out = np.array([x_in[0] - required_mtow, \
x_in[1] - ac.weights.mlw, \
x_in[2] - ac.weights.mzfw])
return y_out
delta_nacelle_width = ac.turbofan_nacelle.width - nacelle_width_i # Should be driven to zero
delta_nacelle_y_ext = ac.turbofan_nacelle.y_ext - nacelle_y_ext_i # Should be driven to zero
print('Coupling : delta_nacelle_width = ', "%.3f" % delta_nacelle_width,
' (= 0 ?)')
print('Coupling : delta_nacelle_y_ext = ', "%.3f" % delta_nacelle_y_ext,
' (= 0 ?)')
airplane.eval_aerodynamics_design(ac)
print("-------------------------------------------")
print("Pre design : done")
# airplane mass & CG estimation
#------------------------------------------------------------------------------------------------------
airframe.eval_cabin_mass(ac)
airframe.eval_fuselage_mass(ac)
airframe.eval_vtp_mass(ac)
airframe.eval_wing_mass(ac)
airframe.eval_htp_mass(ac)
airframe.eval_landing_gear_mass(ac)
propulsion.eval_propulsion_mass(ac)
propulsion.eval_battery_mass(ac)
propulsion.eval_tank_data(ac)
airplane.eval_system_mass(ac)
airplane.eval_payload_mass(ac)
airplane.eval_aircraft_weights(ac)
airplane.eval_aircraft_cg(ac)
def mass_mission_adaptation(aircraft):
"""
Perform mass - mission adaptation and update mass and CGs
"""
#===========================================================================================================
def fct_mass_mission(x_in, aircraft):
ac = aircraft
ac.weights.mtow = x_in[0] # Coupling variable
ac.weights.mlw = x_in[1] # Coupling variable
ac.weights.mzfw = x_in[2] # Coupling variable
# Mass
#------------------------------------------------------------------------------------------------------
airframe.eval_cabin_mass(ac)
airframe.eval_fuselage_mass(ac)
airframe.eval_vtp_mass(ac)
airframe.eval_wing_mass(ac)
airframe.eval_htp_mass(ac)
airframe.eval_landing_gear_mass(ac)
propulsion.eval_propulsion_mass(ac)
propulsion.eval_battery_mass(ac)
propulsion.eval_tank_data(ac)
airplane.eval_system_mass(ac)
airplane.eval_payload_mass(ac)
airplane.eval_aircraft_weights(ac)
# Mission
#------------------------------------------------------------------------------------------------------
disa = 0
altp = ac.design_driver.ref_cruise_altp
mach = ac.design_driver.cruise_mach
ac.nominal_mission.payload = ac.payload.nominal
ac.nominal_mission.range = ac.design_driver.design_range
ac.nominal_mission.tow = ac.weights.mtow
payload = ac.nominal_mission.payload
range = ac.nominal_mission.range
tow = ac.nominal_mission.tow
block_fuel, block_time, total_fuel = perfo.mission(
ac, range, tow, altp, mach, disa)
ac.nominal_mission.block_fuel = block_fuel
ac.nominal_mission.block_time = block_time
ac.nominal_mission.total_fuel = total_fuel
required_mtow = ac.weights.owe + payload + total_fuel
y_out = np.array([x_in[0] - required_mtow, \
x_in[1] - ac.weights.mlw, \
x_in[2] - ac.weights.mzfw])
return y_out
#-----------------------------------------------------------------------------------------------------------
n_pax_ref = aircraft.cabin.n_pax_ref
design_range = aircraft.design_driver.design_range
mtow_i = init.mtow(n_pax_ref, design_range)
mzfw_i = init.mzfw(n_pax_ref, design_range)
mlw_i = init.mlw(mtow_i, mzfw_i)
x_ini = np.array([mtow_i, mlw_i, mzfw_i])
fct_arg = aircraft
output_dict = fsolve(fct_mass_mission,
x0=x_ini,
args=fct_arg,
full_output=True)
aircraft.weights.mtow = output_dict[0][0] # Coupling variable
aircraft.weights.mlw = output_dict[0][1] # Coupling variable
aircraft.weights.mzfw = output_dict[0][2] # Coupling variable
# Update mass
#------------------------------------------------------------------------------------------------------
airframe.eval_cabin_mass(aircraft)
airframe.eval_fuselage_mass(aircraft)
airframe.eval_vtp_mass(aircraft)
airframe.eval_wing_mass(aircraft)
airframe.eval_htp_mass(aircraft)
airframe.eval_landing_gear_mass(aircraft)
propulsion.eval_propulsion_mass(aircraft)
propulsion.eval_battery_mass(aircraft)
propulsion.eval_tank_data(aircraft)
airplane.eval_system_mass(aircraft)
airplane.eval_payload_mass(aircraft)
airplane.eval_aircraft_weights(aircraft)
airplane.eval_aircraft_cg(aircraft)
return
def mass_estimation(aircraft):
"""
Estimate mass and CGs of the airplane
Takes MTOW as input but solves the coupling carried by MZFW and MLW
"""
#===========================================================================================================
def fct_mass(x_in, aircraft):
ac = aircraft
ac.weights.mlw = x_in[0] # Coupling variable
ac.weights.mzfw = x_in[1] # Coupling variable
# Mass
#------------------------------------------------------------------------------------------------------
airframe.eval_cabin_mass(ac)
airframe.eval_fuselage_mass(ac)
airframe.eval_vtp_mass(ac)
airframe.eval_wing_mass(ac)
airframe.eval_htp_mass(ac)
airframe.eval_landing_gear_mass(ac)
propulsion.eval_propulsion_mass(ac)
propulsion.eval_battery_mass(ac)
propulsion.eval_tank_data(ac)
airplane.eval_system_mass(ac)
airplane.eval_payload_mass(ac)
airplane.eval_aircraft_weights(ac)
y_out = np.array([x_in[0] - ac.weights.mlw, \
x_in[1] - ac.weights.mzfw])
return y_out
#-----------------------------------------------------------------------------------------------------------
n_pax_ref = aircraft.cabin.n_pax_ref
design_range = aircraft.design_driver.design_range
mtow_i = aircraft.weights.mtow
mzfw_i = aircraft.weights.mzfw
mlw_i = aircraft.weights.mlw
x_ini = np.array([mlw_i, mzfw_i])
fct_arg = aircraft
output_dict = fsolve(fct_mass, x0=x_ini, args=fct_arg, full_output=True)
aircraft.weights.mlw = output_dict[0][0] # Coupling variable
aircraft.weights.mzfw = output_dict[0][1] # Coupling variable
# Update mass
#------------------------------------------------------------------------------------------------------
airframe.eval_cabin_mass(aircraft)
airframe.eval_fuselage_mass(aircraft)
airframe.eval_vtp_mass(aircraft)
airframe.eval_wing_mass(aircraft)
airframe.eval_htp_mass(aircraft)
airframe.eval_landing_gear_mass(aircraft)
propulsion.eval_propulsion_mass(aircraft)
propulsion.eval_battery_mass(aircraft)
propulsion.eval_tank_data(aircraft)
airplane.eval_system_mass(aircraft)
airplane.eval_payload_mass(aircraft)
airplane.eval_aircraft_weights(aircraft)
airplane.eval_aircraft_cg(aircraft)
return