def summarize(interface):
vehicle = interface.configs.base
results = interface.results
mission_profile = results.missions.base
# merge all segment conditions
def stack_condition(a,b):
if isinstance(a,np.ndarray):
return np.vstack([a,b])
else:
return None
conditions = None
for segment in mission_profile.segments:
if conditions is None:
conditions = segment.conditions
continue
conditions = conditions.do_recursive(stack_condition,segment.conditions)
# pack
summary = SUAVE.Core.Results()
summary.weight_empty = vehicle.mass_properties.operating_empty
summary.fuel_burn = max(conditions.weights.total_mass[:,0]) - min(conditions.weights.total_mass[:,0])
#results.output.max_usable_fuel = vehicle.mass_properties.max_usable_fuel
summary.noise = results.noise
summary.mission_time_min = max(conditions.frames.inertial.time[:,0] / Units.min)
summary.max_altitude_km = max(conditions.freestream.altitude[:,0] / Units.km)
summary.range_nmi = mission_profile.segments[-1].conditions.frames.inertial.position_vector[-1,0] / Units.nmi
summary.field_length = results.field_length
summary.stability = Data()
summary.stability.cm_alpha = max(conditions.stability.static.cm_alpha[:,0])
summary.stability.cn_beta = max(conditions.stability.static.cn_beta[:,0])
#summary.conditions = conditions
#TODO: revisit how this is calculated
summary.second_segment_climb_rate = mission_profile.segments[1].climb_rate
printme = Data()
printme.fuel_burn = summary.fuel_burn
printme.weight_empty = summary.weight_empty
print "RESULTS"
print printme
return summary
def summarize(interface):
# Unpack
vehicle = interface.configs.base
results = interface.results
mission_profile = results.missions.base
short_field_results = results.short_field
takeoff_field_results = results.takeoff_field_length
range_results = results.max_range
# Weights
max_zero_fuel = vehicle.mass_properties.max_zero_fuel
operating_empty = vehicle.mass_properties.operating_empty
payload = vehicle.mass_properties.payload
# pack
summary = SUAVE.Core.Results()
# TOFL for MTOW @ SL, ISA
summary.takeoff_field_length = float(takeoff_field_results.takeoff_field_length[-1])
# Range from a short field
summary.range_short_field_nmi = float(short_field_results.range / Units.nmi)
# Maximum range
summary.range_max_nmi = float(range_results.range / Units.nmi)
# MZFW margin calculation
summary.max_zero_fuel_margin = max_zero_fuel - (operating_empty + payload)
# fuel margin calculation
from SUAVE.Methods.Geometry.Two_Dimensional.Planform import wing_fuel_volume
wing_fuel_volume(vehicle.wings['main_wing'])
fuel_density = vehicle.propulsors['turbo_fan'].combustor.fuel_data.density
fuel_available = 0.97 * vehicle.wings['main_wing'].fuel_volume * fuel_density
summary.available_fuel_margin = fuel_available - range_results.fuel
# Fuel burn
summary.fuel_burn = results.mission_fuel.fuel
## if summary.fuel_burn < 0: # work around for negative fuel results.
## summary.fuel_burn = summary.fuel_burn ** 2.
# Print outs
printme = Data()
printme.fuel_burn = summary.fuel_burn
printme.weight_empty = operating_empty
printme.tofl_MTOW = summary.takeoff_field_length
printme.SF_range = summary.range_short_field_nmi
printme.range_max = summary.range_max_nmi
printme.max_zero_fuel_margin = summary.max_zero_fuel_margin
printme.available_fuel_margin = summary.available_fuel_margin
print "RESULTS"
print printme
inputs = interface.inputs
import datetime
fid = open('Results.dat','a')
fid.write('{:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ; {:18.10f} ;'.format( \
inputs.aspect_ratio,inputs.reference_area,inputs.sweep,inputs.design_thrust,inputs.wing_thickness,inputs.MTOW,inputs.MZFW_ratio,
summary.fuel_burn , operating_empty , summary.takeoff_field_length , summary.range_short_field_nmi , summary.range_max_nmi , summary.max_zero_fuel_margin , summary.available_fuel_margin
))
fid.write(datetime.datetime.now().strftime("%I:%M:%S"))
fid.write('\n')
## print interface.configs.takeoff.maximum_lift_coefficient
return summary
