total_fuel = ac.weights.mfw
tow = ac.weights.owe + total_fuel
ac.zero_payload_mission.tow = tow
ac.zero_payload_mission.total_fuel = total_fuel
range, payload, block_fuel, block_time = sub_proc.mission_fuel_limited(
ac, tow, total_fuel, altp, mach, disa)
ac.zero_payload_mission.range = range
ac.zero_payload_mission.block_fuel = block_fuel
ac.zero_payload_mission.block_time = block_time
print("-------------------------------------------")
print("Payload-Range analysis : done")
print("-------------------------------------------")
print("Propeller =", ac.turboprop_engine.propeller_diameter)
# airplane 3D view
#------------------------------------------------------------------------------------------------------
print("-------------------------------------------")
print("3 view drawing : launched")
show.draw_3d_view(ac, "sequence deployed", "This plane")
file_name = "Aircraft.pkl"
output = open(file_name, "wb")
pickle.dump(ac, output)
output.close()
mtow_req = aircraft.weights.owe + aircraft.nominal_mission.payload + aircraft.nominal_mission.total_fuel
# Print relevant data
#------------------------------------------------------------------------------------------------------
delta_mtow = mtow_i - mtow_req # Should be positive or zero
print("")
print("MTOW required = ", "%.0f" % mtow_req, " kg")
print("Delta MTOW = ", "%.2f" % delta_mtow, " kg (Should be positive or zero)")
disa = 0
altp = aircraft.design_driver.ref_cruise_altp
mach = aircraft.design_driver.cruise_mach
vtas = earth.vtas_from_mach(altp, disa, mach)
print("")
print("Wing mass = ", "%.2f" % aircraft.wing.mass, " kg")
print("Wing span = ", "%.2f" % aircraft.wing.span, " m")
print("Wing aspect ratio = ", "%.2f" % aircraft.wing.aspect_ratio, " no_dim")
print("")
print("True air speed = ", "%.2f" % unit.kt_mps(vtas), " kt")
print("Fuel mission = ", "%.2f" % aircraft.nominal_mission.block_fuel, " kg")
print("LoD cruise (LoD max) = ", "%.2f" % aircraft.high_speed.cruise_lod,
" no_dim")
print("SFC cruise = ", "%.3f" % (aircraft.high_speed.cruise_sfc * 36000),
" kg/daN/h")
# airplane 3D view
#------------------------------------------------------------------------------------------------------
show.draw_3d_view(aircraft, "study_n1", "This plane")
print("Vertical speed required with MCR rating = ","%.1f"%unit.ftpmin_mps(aircraft.high_speed.req_vz_cruise)," ft/min")
print("Vertical speed effective with MCR rating = ","%.1f"%unit.ftpmin_mps(aircraft.high_speed.eff_vz_cruise)," ft/min")
print("")
print("Time to climb required = ","%.1f"%unit.min_s(aircraft.high_speed.req_ttc)," min")
print("Time to climb effective = ","%.1f"%unit.min_s(aircraft.high_speed.eff_ttc)," min")
# """
print("")
print("--------------------------------------------------------------")
print("MTOW = ","%.0f"%aircraft.weights.mtow," kg")
print("Cost mission fuel = ","%.1f"%aircraft.cost_mission.block_fuel," kg")
print("Cash Operating Cost = ","%.1f"%aircraft.economics.cash_operating_cost," $/trip")
print("Carbon dioxid emission = ","%.1f"%(aircraft.cost_mission.block_CO2)," kg/trip")
print("Fuel efficiency metric = ","%.4f"%(aircraft.environmental_impact.CO2_metric*1e7)," 10-7kg/km/m0.48")
"""
# airplane 3D view
#------------------------------------------------------------------------------------------------------
show.draw_3d_view(aircraft,"study_n5",study_name)
#aircraft.export_to_ini_file("output_mda3")
# """
e_power = 1.0e6
for i in range(0, 4, 1):
# 100k/200k
#for i in range(160, 200, 1):
# e_power = 100000+i
aircraft.power_elec_chain.overall_efficiency = 0.60+i/10
perform.handling_qualities_analysis(aircraft)
print("-------------------------------------------")
print("Handling qualities analysis : done")
print("")
print("Rayon d'action demandé = ","%.0f"%unit.NM_m(aircraft.design_driver.design_range)," NM")
print(" . . . . . . . effectif = ","%.0f"%unit.NM_m(aircraft.nominal_mission.range)," NM")
print("")
print("Longueur de piste au décollage demandée = "+"%.0f"%aircraft.low_speed.req_tofl+" m")
print(" . . . . . . . . . . . . . . . effective = "+"%.0f"%aircraft.low_speed.eff_tofl+" m")
print("")
print("Vitesse d'approche demandée = "+"%.1f"%unit.kt_mps(aircraft.low_speed.req_app_speed)+" kt")
print(" . . . . . . . . . effective = "+"%.1f"%unit.kt_mps(aircraft.low_speed.eff_app_speed)+" kt")
print("")
print("Vitesse de monté demandé = "+"%.1f"%unit.ftpmin_mps(aircraft.high_speed.req_vz_climb)+" ft/min")
print(" . . . . . . . . effective = "+"%.1f"%unit.ftpmin_mps(aircraft.high_speed.eff_vz_climb)+" ft/min")
print("")
print("Temps de monté demandé = "+"%.1f"%unit.min_s(aircraft.high_speed.req_ttc)+" min")
print(" . . . . . . . effectif = "+"%.1f"%unit.min_s(aircraft.high_speed.eff_ttc)+" min")
print("")
print("Coût d'un voyage = "+"%.0f"%aircraft.economics.direct_operating_cost+" $")
# airplane 3D view
#------------------------------------------------------------------------------------------------------
print("-------------------------------------------")
print("3 view drawing : launched")
show.draw_3d_view(aircraft,"sequence packaged","This plane")
print("Rayon d'action demandé = ",
"%.0f" % unit.NM_m(aircraft.design_driver.design_range), " NM")
print(" . . . . . . effectif = ",
"%.0f" % unit.NM_m(aircraft.nominal_mission.range), " NM")
print("")
print("Longueur de piste au décollage demandée = " +
"%.0f" % aircraft.low_speed.req_tofl + " m")
print(" . . . . . . . . . . . . . . effective = " +
"%.0f" % aircraft.low_speed.eff_tofl + " m")
print("")
print("Vitesse d'approche demandée = " +
"%.1f" % unit.kt_mps(aircraft.low_speed.req_app_speed) + " kt")
print(" . . . . . . . . effective = " +
"%.1f" % unit.kt_mps(aircraft.low_speed.eff_app_speed) + " kt")
print("")
print("Vitesse de monté demandé = " +
"%.1f" % unit.ftpmin_mps(aircraft.high_speed.req_vz_climb) + " ft/min")
print(" . . . . . . . effective = " +
"%.1f" % unit.ftpmin_mps(aircraft.high_speed.eff_vz_climb) + " ft/min")
print("")
print("Temps de monté demandé = " +
"%.1f" % unit.min_s(aircraft.high_speed.req_ttc) + " min")
print(" . . . . . . effectif = " +
"%.1f" % unit.min_s(aircraft.high_speed.eff_ttc) + " min")
print("")
print("Coût d'un voyage = " +
"%.0f" % aircraft.economics.direct_operating_cost + " $")
print("COC = " + "%.0f" % aircraft.economics.cash_operating_cost + " $")
show.draw_3d_view(aircraft, "Test", "My plane")