# Possibility to modify initial values
#------------------------------------------------------------------------------------------------------
study_name = "This airplane"
aircraft.turbofan_engine.reference_thrust = 130000 # Newtons
aircraft.wing.area = 155 # m2
e_power = 1.0e6 # Watts, electric motor power
aircraft.power_elec_chain.mto = e_power
aircraft.power_elec_chain.mcn = e_power
aircraft.power_elec_chain.mcl = e_power
aircraft.power_elec_chain.mcr = e_power
aircraft.battery.energy_cruise = 0. #unit.J_kWh(140) # J, energy stored in the battery dedicated to the cruise
aircraft.battery.energy_density = unit.J_kWh(
0.2) # J/kg, # Battery energy density
aircraft.propulsion.bli_effect = 1 #init.boundary_layer_effect()
aircraft.power_elec_chain.overall_efficiency = 0.90 # 0.90 from init.e_chain_efficiency()
# Solve the geometric coupling between airframe and engines
#------------------------------------------------------------------------------------------------------
run.aircraft_pre_design(aircraft)
# Estimate all mass and CGs
#------------------------------------------------------------------------------------------------------
run.mass_mission_adaptation(aircraft)
#run.mass_estimation(aircraft)
# Calculate all airplane performances
#------------------------------------------------------------------------------------------------------
def elec_price():
#===========================================================================================================
elec_price_i = 0.15 / unit.J_kWh(1) # 0.15 $/kWh Assumed de-carbonated
return elec_price_i
def battery_energy_density():
battery_energy_density_i = unit.J_kWh(0.2) # Battery energy density
return battery_energy_density_i
#------------------------------------------------------------------------------------------------------
run.aircraft_initialize(aircraft, n_pax_ref, design_range, cruise_mach,
propu_config, n_engine)
# Possibility to modify initial values
#------------------------------------------------------------------------------------------------------
study_name = "This airplane"
aircraft.battery.strategy = 2
aircraft.propulsion.bli_effect = 1 # 1: with, 0: without
aircraft.power_elec_chain.overall_efficiency = 0.90 # 0.90 from init.e_chain_efficiency()
aircraft.economics.battery_price = 20 # $/kg
aircraft.economics.elec_price = 0.15 / unit.J_kWh(1) # 0.05 $/kWh
aircraft.economics.fuel_price = 2 / unit.liter_usgal(1) # 2 $/USgal
aircraft.battery.energy_density = unit.J_kWh(
0.2) * 4 # J/kg, # Battery energy density
aircraft.battery.mass = 0 # kg, # Battery mass [0 to 2000 kg]
e_power = 1.0e6 # Watts, electric motor power [0 to 1 MW]
aircraft.power_elec_chain.mto = e_power
aircraft.power_elec_chain.mcn = e_power
aircraft.power_elec_chain.mcl = e_power
aircraft.power_elec_chain.mcr = e_power
#------------------------------------------------------------------------------------------------------
# Automatic optimization of the airplane
#------------------------------------------------------------------------------------------------------
thrust_bnd = (110000, 150000)
area_bnd = (100, 200)
search_domain = (thrust_bnd, area_bnd)
run.optimization(aircraft, search_domain)
# Print relevant output
#------------------------------------------------------------------------------------------------------
print("")
print("Fuel price = ", "%.3f" % (init.fuel_price() * unit.liter_usgal(1)),
" $/USgal")
print("Elec price = ", "%.3f" % (init.elec_price() * unit.J_kWh(1)), " $/kW")
print("")
print("Engine thrust = ",
"%.1f" % (aircraft.propulsion.reference_thrust_effective / 10), " daN")
print("Wing area = ", "%.1f" % aircraft.wing.area, " m2")
print("MTOW = ", "%.0f" % aircraft.weights.mtow, " kg")
print("OWE = ", "%.0f" % aircraft.weights.owe, " kg")
print("")
print("Turbofan nacelle mass = ", "%.1f" % aircraft.turbofan_nacelle.mass,
" kg")
if (aircraft.propulsion.architecture == 2):
print("Electric nacelle mass = ", "%.1f" % aircraft.electric_nacelle.mass,
" kg")
print("Power electric mass = ", "%.1f" % aircraft.power_elec_chain.mass,
#------------------------------------------------------------------------------------------------------
run.aircraft_initialize(aircraft, n_pax_ref, design_range, cruise_mach,
propulsion_architecture, n_engine)
# Possibility to modify initial values
#------------------------------------------------------------------------------------------------------
study_name = "This airplane"
e_power = 1.0e6 # Watts, electric motor power
aircraft.power_elec_chain.mto = e_power
aircraft.power_elec_chain.mcn = e_power
aircraft.power_elec_chain.mcl = e_power
aircraft.power_elec_chain.mcr = e_power
aircraft.battery.energy_cruise = unit.J_kWh(
140) # J, energy stored in the battery dedicated to the cruise
aircraft.battery.energy_density = unit.J_kWh(
0.2) # J/kg, # Battery energy density
aircraft.propulsion.bli_effect = 1 #init.boundary_layer_effect()
aircraft.power_elec_chain.overall_efficiency = 0.90 # 0.90 from init.e_chain_efficiency()
# Solve the geometric coupling between airframe and engines
#------------------------------------------------------------------------------------------------------
run.aircraft_pre_design(aircraft)
# Estimate all mass and CGs
#------------------------------------------------------------------------------------------------------
run.mass_mission_adaptation(aircraft)
# Calculate all airplane performances