def __init__(self, ac, eng=None):
"""Intitialize the generator.
Args:
ac (string): Aircraft type.
eng (string): Engine type. Leave empty for default engine type in OpenAP.
Returns:
dict: flight trajectory
"""
super(Generator, self).__init__()
self.ac = ac
self.acdict = prop.aircraft(self.ac)
if eng is None:
self.eng = self.acdict['engine']['default']
else:
self.eng = eng
self.engdict = prop.engine(self.eng)
self.wrap = WRAP(self.ac)
# self.thrust = Thrust(self.ac, self.eng)
# self.drag = Drag(self.ac)
# self.fuelflow = Thrust(self.ac, self.eng)
# for noise generation
self.sigma_v = 0
self.sigma_vs = 0
self.sigma_h = 0
self.sigma_s = 0
def __init__(self, ac, eng=None):
"""Initialize FuelFlow object.
Args:
ac (string): ICAO aircraft type (for example: A320).
eng (string): Engine type (for example: CFM56-5A3).
Leave empty to use the default engine specified
by in the aircraft database.
"""
self.aircraft = prop.aircraft(ac)
if eng is None:
eng = self.aircraft["engine"]["default"]
self.engine = prop.engine(eng)
self.thrust = Thrust(ac, eng)
self.drag = Drag(ac)
c3, c2, c1 = (
self.engine["fuel_c3"],
self.engine["fuel_c2"],
self.engine["fuel_c1"],
)
# print(c3,c2,c1)
self.fuel_flow_model = lambda x: c3 * x**3 + c2 * x**2 + c1 * x
def __init__(self, ac, eng=None, **kwargs):
"""Initialize FuelFlow object.
Args:
ac (string): ICAO aircraft type (for example: A320).
eng (string): Engine type (for example: CFM56-5A3).
Leave empty to use the default engine specified
by in the aircraft database.
"""
if not hasattr(self, "np"):
self.np = importlib.import_module("numpy")
if not hasattr(self, "Thrust"):
self.Thrust = importlib.import_module("openap.thrust").Thrust
if not hasattr(self, "Drag"):
self.Drag = importlib.import_module("openap.drag").Drag
if not hasattr(self, "WRAP"):
self.WRAP = importlib.import_module("openap.kinematic").WRAP
self.aircraft = prop.aircraft(ac, **kwargs)
if eng is None:
eng = self.aircraft["engine"]["default"]
self.engine = prop.engine(eng)
self.thrust = self.Thrust(ac, eng, **kwargs)
self.drag = self.Drag(ac, **kwargs)
self.wrap = self.WRAP(ac, **kwargs)
polydeg = kwargs.get("polydeg", 3)
if polydeg == 2:
a, b = self.engine["fuel_a"], self.engine["fuel_b"]
self.polyfuel = func_fuel2(a, b)
elif polydeg == 3:
c3, c2, c1 = (
self.engine["fuel_c3"],
self.engine["fuel_c2"],
self.engine["fuel_c1"],
)
self.polyfuel = func_fuel3(c3, c2, c1)
else:
raise RuntimeError(f"polydeg must be 2 or 3")
def __init__(self, ac, eng=None):
"""Initialize FuelFlow object.
Args:
ac (string): ICAO aircraft type (for example: A320).
eng (string): Engine type (for example: CFM56-5A3).
Leave empty to use the default engine specified
by in the aircraft database.
"""
self.ac = prop.aircraft(ac)
self.n_eng = self.ac["engine"]["number"]
if eng is None:
eng = self.ac["engine"]["default"]
self.engine = prop.engine(eng)
def __init__(self, ac, eng=None, **kwargs):
"""Initialize Thrust object.
Args:
ac (string): ICAO aircraft type (for example: A320).
eng (string): Engine type (for example: CFM56-5A3).
"""
if not hasattr(self, "np"):
self.np = importlib.import_module("numpy")
if not hasattr(self, "aero"):
self.aero = importlib.import_module("openap").aero
aircraft = prop.aircraft(ac, **kwargs)
if eng is None:
eng = aircraft["engine"]["default"]
engine = prop.engine(eng)
if type(aircraft["engine"]["options"]) == dict:
eng_options = list(aircraft["engine"]["options"].values())
elif type(aircraft["engine"]["options"]) == list:
eng_options = list(aircraft["engine"]["options"])
if engine["name"] not in eng_options:
raise RuntimeError(
f"Engine {eng} and aircraft {ac} mismatch. Available engines for {ac} are {eng_options}"
)
self.cruise_alt = aircraft["cruise"]["height"] / self.aero.ft
# self.cruise_alt = 30000
self.eng_bpr = engine["bpr"]
self.eng_max_thrust = engine["max_thrust"]
self.eng_number = aircraft["engine"]["number"]
if engine["cruise_mach"] > 0:
self.cruise_mach = engine["cruise_mach"]
self.eng_cruise_thrust = engine["cruise_thrust"]
else:
self.cruise_mach = aircraft["cruise"]["mach"]
self.eng_cruise_thrust = 0.2 * self.eng_max_thrust + 890
def __init__(self, ac, eng=None, **kwargs):
"""Initialize FuelFlow object.
Args:
ac (string): ICAO aircraft type (for example: A320).
eng (string): Engine type (for example: CFM56-5A3).
Leave empty to use the default engine specified
by in the aircraft database.
"""
if not hasattr(self, "np"):
self.np = importlib.import_module("numpy")
if not hasattr(self, "Thrust"):
self.Thrust = importlib.import_module("openap.thrust").Thrust
if not hasattr(self, "Drag"):
self.Drag = importlib.import_module("openap.drag").Drag
if not hasattr(self, "WRAP"):
self.WRAP = importlib.import_module("openap.kinematic").WRAP
self.aircraft = prop.aircraft(ac, **kwargs)
if eng is None:
eng = self.aircraft["engine"]["default"]
self.engine = prop.engine(eng)
self.thrust = self.Thrust(ac, eng, **kwargs)
self.drag = self.Drag(ac, **kwargs)
self.wrap = self.WRAP(ac, **kwargs)
c3, c2, c1 = (
self.engine["fuel_c3"],
self.engine["fuel_c2"],
self.engine["fuel_c1"],
)
# print(c3,c2,c1)
self.func_fuel = prop.func_fuel(c3, c2, c1)
def __init__(self, ac, eng=None):
"""Initialize Thrust object.
Args:
ac (string): ICAO aircraft type (for example: A320).
eng (string): Engine type (for example: CFM56-5A3).
"""
super(Thrust, self).__init__()
aircraft = prop.aircraft(ac)
if eng is None:
eng = aircraft['engine']['default']
engine = prop.engine(eng)
if type(aircraft['engine']['options']) == dict:
eng_options = list(aircraft['engine']['options'].values())
elif type(aircraft['engine']['options']) == list:
eng_options = list(aircraft['engine']['options'])
if engine['name'] not in eng_options:
raise RuntimeError(
'Engine {eng} and aircraft {ac} mismatch. Available engines for {ac} are {eng_options}'
)
self.cruise_alt = aircraft['cruise']['height'] / aero.ft
# self.cruise_alt = 30000
self.eng_bpr = engine['bpr']
self.eng_max_thrust = engine['max_thrust']
self.eng_number = aircraft['engine']['number']
if engine['cruise_mach'] > 0:
self.cruise_mach = engine['cruise_mach']
self.eng_cruise_thrust = engine['cruise_thrust']
else:
self.cruise_mach = aircraft['cruise']['mach']
self.eng_cruise_thrust = 0.2 * self.eng_max_thrust + 890
def __init__(self, ac, eng=None, **kwargs):
"""Initialize Emission object.
Args:
ac (string): ICAO aircraft type (for example: A320).
eng (string): Engine type (for example: CFM56-5A3).
Leave empty to use the default engine specified
by in the aircraft database.
"""
if not hasattr(self, "np"):
self.np = importlib.import_module("numpy")
if not hasattr(self, "aero"):
self.aero = importlib.import_module("openap").aero
self.ac = prop.aircraft(ac, **kwargs)
self.n_eng = self.ac["engine"]["number"]
if eng is None:
eng = self.ac["engine"]["default"]
self.engine = prop.engine(eng)
import numpy as np
from openap import prop
from pprint import pprint as print
import matplotlib.pyplot as plt
acs = prop.available_aircraft()
for ac in acs:
engs = prop.aircraft_engine_options(ac)
for eng in engs:
try:
e = prop.engine(eng)
print(e)
except:
print(f"{eng} from {ac} cannot be found.")
continue
c3, c2, c1 = (
e["fuel_c3"],
e["fuel_c2"],
e["fuel_c1"],
)
x = np.array([0.07, 0.3, 0.85, 1.0])
xx = np.linspace(0.07, 1, 100)
plt.suptitle(f"{ac} / {eng}")
plt.subplot(221)
plt.scatter(x, [e["ff_idl"], e["ff_app"], e["ff_co"], e["ff_to"]])
from pprint import pprint
from openap import prop
ac = prop.aircraft("A320")
pprint(ac)
eng = prop.engine("CFM56-5B4")
pprint(eng)