def get_weight_estimations(cpacs_path, cpacs_out_path):
"""Function to estimate the all weights for a conventional aircraft.
Function 'get_weight_estimations' ...
Source:
* Reference paper or book, with author and date, see ...
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str):Path to CPACS output file
"""
# TODO: replace that by a general function??? (same for all modules)
start = time.time()
# Removing and recreating the ToolOutput folder.
if os.path.exists('ToolOutput'):
shutil.rmtree('ToolOutput')
os.makedirs('ToolOutput')
else:
os.makedirs('ToolOutput')
# Classes
# TODO: Use only one class or subclasses
ui = weightconvclass.UserInputs()
mw = weightconvclass.MassesWeights()
out = weightconvclass.WeightOutput()
if not os.path.exists(cpacs_path):
raise ValueError('No "ToolInput.xml" file in the ToolInput folder.')
name = aircraft_name(cpacs_path)
shutil.copyfile(cpacs_path, cpacs_out_path) # TODO: shoud not be like that
newpath = 'ToolOutput/' + name
if not os.path.exists(newpath):
os.makedirs(newpath)
ag = geometry.geometry_eval(cpacs_path, name)
fuse_length = round(ag.fuse_length[0], 3)
fuse_width = round(np.amax(ag.fuse_sec_width[:, 0]), 3)
ind = weightconvclass.InsideDimensions(fuse_length, fuse_width)
ind.nose_length = round(ag.fuse_nose_length[0], 3)
ind.tail_length = round(ag.fuse_tail_length[0], 3)
ind.cabin_length = round(ag.fuse_cabin_length[0], 3)
wing_area = round(ag.wing_plt_area_main, 3)
wing_span = round(ag.wing_span[ag.main_wing_index - 1], 3)
wing_area_tot = np.sum(ag.wing_plt_area)
#Has been replace by classes function
# (ind, ui) = getinput.get_user_inputs(ind, ui, ag, cpacs_out_path)
ui.get_user_inputs(cpacs_out_path)
ind.get_inside_dim(cpacs_out_path)
if ui.MAX_FUEL_VOL > 0 and ui.MAX_FUEL_VOL < ag.wing_fuel_vol:
max_fuel_vol = ui.MAX_FUEL_VOL
else:
max_fuel_vol = ag.wing_fuel_vol
out.PILOT_NB = ui.PILOT_NB # Number of pilot [-].
# Massimum payload allowed, set 0 if equal to max passenger mass.
mw.MAX_PAYLOAD = ui.MAX_PAYLOAD
# Adding extra length in case of aircraft with second floor [m].
if ui.IS_DOUBLE_FLOOR == 1:
cabin_length2 = ind.cabin_length * 1.91
elif ui.IS_DOUBLE_FLOOR == 2:
cabin_length2 = ind.cabin_length * 1.20
elif ui.IS_DOUBLE_FLOOR == 0:
cabin_length2 = ind.cabin_length
else:
log.warning('Warning, double floor index can be only 0 (1 floor),\
2 (B747-2nd floor type) or 3 (A380-2nd floor type).\
Set Default value (0)')
### WEIGHT ANALYSIS
log.info('------- Starting the weight analysis --------')
log.info('---------- Aircraft: ' + name + ' -----------')
# Maximum Take Off Mass Evaluation
mw.maximum_take_off_mass = estimate_mtom(fuse_length, fuse_width,
wing_area, wing_span, name)
# Wing loading
out.wing_loading = mw.maximum_take_off_mass / wing_area_tot
# Operating Empty Mass evaluation
mw.operating_empty_mass = estimate_operating_empty_mass(
mw.maximum_take_off_mass, fuse_length, fuse_width, wing_area,
wing_span, ui.TURBOPROP)
# Passengers and Crew mass evaluation
if ((fuse_width / (1 + (ind.fuse_thick / 100))) >
(ind.seat_width + ind.aisle_width)):
(out.pass_nb, out.row_nb, out.abreast_nb, out.aisle_nb,\
out.toilet_nb, ind) = estimate_passengers(ui.PASS_PER_TOILET,\
cabin_length2, fuse_width, ind)
get_seat_config(out.pass_nb, out.row_nb, out.abreast_nb, out.aisle_nb,
ui.IS_DOUBLE_FLOOR, out.toilet_nb, ui.PASS_PER_TOILET,
fuse_length, ind, name)
else:
out.pass_nb = 0
raise Exception('The aircraft can not transport passengers, increase'\
+ ' fuselage width.' + '\nCabin Width [m] = '\
+ str((fuse_width/(1 + ind.fuse_thick)))\
+ ' is less than seat width [m]'\
+ ' + aisle width [m] = '\
+ str(ind.seat_width + ind.aisle_width))
(out.crew_nb, out.cabin_crew_nb, mw.mass_crew)\
= estimate_crew(out.pass_nb, ui.MASS_PILOT, ui.MASS_CABIN_CREW,\
mw.maximum_take_off_mass, out.PILOT_NB)
mw.mass_payload = out.pass_nb * ui.MASS_PASS + ui.MASS_CARGO
mw.mass_people = mw.mass_crew + out.pass_nb * ui.MASS_PASS
maxp = False
if (mw.MAX_PAYLOAD > 0 and mw.mass_payload > mw.MAX_PAYLOAD):
mw.mass_payload = mw.MAX_PAYLOAD
maxp = True
log.info('With the fixed payload, passenger nb reduced to: '\
+ str(round(mw.MAX_PAYLOAD / (ui.MASS_PASS),0)))
# Fuel Mass evaluation
# Maximum fuel that can be stored with maximum number of passengers.
if not ui.MAX_FUEL_VOL: # TODO while retesting, redo fitting
if ui.TURBOPROP:
if wing_area > 55.00:
mw.mass_fuel_max = round(mw.maximum_take_off_mass / 4.6, 3)
else:
mw.mass_fuel_max = round(mw.maximum_take_off_mass / 3.6, 3)
elif wing_area < 90.00:
if fuse_length < 60.00:
mw.mass_fuel_max = round(mw.maximum_take_off_mass / 4.3, 3)
else:
mw.mass_fuel_max = round(mw.maximum_take_off_mass / 4.0, 3)
elif wing_area < 300.00:
if fuse_length < 35.00:
mw.mass_fuel_max = round(mw.maximum_take_off_mass / 3.6, 3)
else:
mw.mass_fuel_max = round(mw.maximum_take_off_mass / 3.8, 3)
elif wing_area < 400.00:
mw.mass_fuel_max = round(mw.maximum_take_off_mass / 2.2, 3)
elif wing_area < 600.00:
mw.mass_fuel_max = round(mw.maximum_take_off_mass / 2.35, 3)
else:
mw.mass_fuel_max = round(mw.maximum_take_off_mass / 2.8, 3)
else:
mw.mass_fuel_max = round(max_fuel_vol * ui.FUEL_DENSITY, 3)
mw.mass_fuel_maxpass = round(mw.maximum_take_off_mass \
- mw.operating_empty_mass \
- mw.mass_payload, 3)
if (mw.MAX_FUEL_MASS > 0 and mw.mass_fuel_maxpass > mw.MAX_FUEL_MASS):
mw.mass_fuel_maxpass = mw.MAX_FUEL_MASS
log.info('Maximum fuel ammount allowed reached [kg]: ' +
str(mw.mass_fuel_maxpass))
if (mw.maximum_take_off_mass > (mw.mass_fuel_maxpass\
+ mw.operating_empty_mass + mw.mass_payload)):
mw.mass_cargo = mw.maximum_take_off_mass - (mw.mass_fuel_maxpass\
+ mw.operating_empty_mass + mw.mass_payload)
if not maxp:
log.info('Adding extra payload mass [kg]: '\
+ str(mw.mass_cargo))
mw.mass_payload = mw.mass_payload + mw.mass_cargo
else:
maximum_take_off_mass = maximum_take_off_mass - mw.mass_cargo
log.info('With all the constrains on the fuel and payload, '\
+ 'the maximum take off mass is not reached.'\
+ '\n Maximum take off mass [kg]: '\
+ str(maximum_take_off_mass))
else:
log.info('Fuel mass with maximum passengers [kg]: '\
+ str(mw.mass_fuel_maxpass))
if (mw.MAX_FUEL_MASS > 0 and mw.mass_fuel_max > mw.MAX_FUEL_MASS):
mw.mass_fuel_max = mw.MAX_FUEL_MASS
# Zero Fuel Mass evaluation
mw.zero_fuel_mass = mw.maximum_take_off_mass - mw.mass_fuel_maxpass\
+ (ui.RES_FUEL_PERC)*mw.mass_fuel_max
# Log writting (TODO: maybe create a separate function)
log.info('---- Geometry evaluation from CPACS file ----')
log.info('Fuselage length [m]: ' + str(round(fuse_length, 3)))
log.info('Fuselage width [m]: ' + str(round(fuse_width, 3)))
log.info('Fuselage mean width [m]: ' + str(round(ag.fuse_mean_width, 3)))
log.info('Wing Span [m]: ' + str(round(wing_span, 3)))
log.info('--------- Masses evaluated: -----------')
log.info('Maximum Take Off Mass [kg]: '\
+ str(int(round(mw.maximum_take_off_mass))))
log.info('Operating Empty Mass [kg]: '\
+ str(int(round(mw.operating_empty_mass))))
log.info('Zero Fuel Mass [kg]: '\
+ str(int(round(mw.zero_fuel_mass))))
log.info('Wing loading [kg/m^2]: '\
+ str(int(round(out.wing_loading))))
log.info('Maximum ammount of fuel allowed with no passengers [kg]: '\
+ str(int(round(mw.mass_fuel_max))))
log.info('Maximum ammount of fuel allowed with no passengers [l]: '\
+ str(int(round(mw.mass_fuel_max/ui.FUEL_DENSITY))))
log.info('--------- Passegers evaluated: ---------')
log.info('Passengers: ' + str(out.pass_nb))
log.info('Lavatory: ' + str(out.toilet_nb))
log.info('Payload mass [kg]: ' + str(mw.mass_payload))
log.info('------- Crew members evaluated: --------')
log.info('Pilots: ' + str(out.PILOT_NB))
log.info('Cabin crew members: ' + str(out.cabin_crew_nb))
end = time.time()
log.info('---------------------------------------')
log.info('Elapsed time [s]: ' + str(round((end - start), 3)))
log.info('---------------------------------------')
log.info('############### Weight estimation completed ###############')
# Outptu writting
log.info('-------- Generating output text file --------')
outputweightgen.output_txt(out, mw, ind, ui, name)
# CPACS writting
cpacsweightupdate.cpacs_update(mw, out, cpacs_path, cpacs_out_path)
##=============================== PREPROCESSING ============================##
start = time.time()
# Removing and recreating the ToolOutput folder.
if os.path.exists('ToolOutput'):
shutil.rmtree('ToolOutput')
os.makedirs('ToolOutput')
else:
os.makedirs('ToolOutput')
# Class Definition from the ceasiompy.Input_classes/Conventional folder
ui = weightconvclass.UserInputs()
# Class Definition from the classes folder
mw = weightconvclass.MassesWeights()
out = weightconvclass.WeightOutput()
# Set True for option B or False for option A
cpacs = True
if not cpacs:
### Option 1: GEOMETRY FROM INPUT
name = str(input('Name of the aircraft: '))
wing_area = float(input('Wing plantform area [m^2]: '))
wing_span = float(input('Wing span [m]: '))
fuse_length = float(input('Fuselage length [m]: '))
fuse_width = float(input('Fuselage width [m]: '))
wing_area_tot = wing_area
start = time.time()
ind = weightconvclass.InsideDimensions(fuse_length,\