def func_fuel(self, x, mass):
mach, h = denormalize(x, self.normfactor)
va = aero.mach2tas(mach, h)
ff = self.fuelflow.enroute(mass, va / aero.kts, h / aero.ft)
ff_m = ff / (va + 1e-3) * 1000
# print("%.03f" % mach, "%d" % (h/aero.ft), "%.05f" % ff_m)
return ff_m
def func_cons_thrust(self, x, mass):
mach, h = denormalize(x, self.normfactor)
va = aero.mach2tas(mach, h)
D = self.drag.clean(mass, va / aero.kts, h / aero.ft)
Tmax = self.thrust.cruise(va / aero.kts, h / aero.ft)
dT = Tmax - D
return dT
def func_cons_lift(self, x, mass):
mach, h = denormalize(x, self.normfactor)
va = aero.mach2tas(mach, h)
Tmax = self.thrust.cruise(va / aero.kts, h / aero.ft)
qS = 0.5 * aero.density(h) * va**2 * self.aircraft['wing']['area']
cd0 = self.drag.polar['clean']['cd0']
k = self.drag.polar['clean']['k']
mach_crit = self.drag.polar['mach_crit']
if mach > mach_crit:
cd0 += 20 * (mach - mach_crit)**4
dL2 = qS**2 * (1 / k * (Tmax /
(qS + 1e-3) - cd0)) - (mass * aero.g0)**2
return dL2
def func_time(self, x, mass):
mach, h = denormalize(x, self.normfactor)
va = aero.mach2tas(mach, h)
va_inv = 1 / (va + 1e-4) * 1000
# print("%.03f" % mach, "%d" % (h/aero.ft), "%.02f" % va)
return va_inv
def climb(self, **kwargs):
"""Generate climb trajectory based on WRAP model.
Args:
**dt (int): Time step in seconds.
**cas_const_cl (int): Constaant CAS for climb (kt).
**mach_const_cl (float): Constaant Mach for climb (-).
**h_cr (int): Target cruise altitude (km).
**random (bool): Generate trajectory with random paramerters.
Returns:
dict: Flight trajectory.
"""
dt = kwargs.get('dt', 1)
random = kwargs.get('random', False)
a_tof = self.wrap.takeoff_acceleration()['default']
v_tof = self.wrap.takeoff_speed()['default']
if random:
cas_const = kwargs.get(
'cas_const_cl',
np.random.uniform(self.wrap.climb_const_vcas()['minimum'],
self.wrap.climb_const_vcas()['maximum']) /
aero.kts)
mach_const = kwargs.get(
'mach_const_cl',
np.random.uniform(self.wrap.climb_const_mach()['minimum'],
self.wrap.climb_const_mach()['maximum']))
h_cr = kwargs.get(
'h_cr',
np.random.uniform(self.wrap.cruise_alt()['minimum'],
self.wrap.cruise_alt()['maximum']) * 1000)
vs_pre_constcas = np.random.uniform(
self.wrap.climb_vs_pre_concas()['minimum'],
self.wrap.climb_vs_pre_concas()['maximum'])
vs_constcas = np.random.uniform(
self.wrap.climb_vs_concas()['minimum'],
self.wrap.climb_vs_concas()['maximum'])
vs_constmach = np.random.uniform(
self.wrap.climb_vs_conmach()['minimum'],
self.wrap.climb_vs_conmach()['maximum'])
else:
cas_const = kwargs.get(
'cas_const_cl',
self.wrap.climb_const_vcas()['default'] / aero.kts)
mach_const = kwargs.get('mach_const_cl',
self.wrap.climb_const_mach()['default'])
h_cr = kwargs.get('h_cr', self.wrap.cruise_alt()['default'] * 1000)
vs_pre_constcas = self.wrap.climb_vs_pre_concas()['default']
vs_constcas = self.wrap.climb_vs_concas()['default']
vs_constmach = self.wrap.climb_vs_conmach()['default']
vcas_const = cas_const * aero.kts
h_cr = np.round(h_cr / aero.ft,
-2) * aero.ft # round cruise altitude to flight level
vs_ic = self.wrap.initclimb_vs()['default']
h_const_cas = self.wrap.climb_cross_alt_concas()['default'] * 1000
h_const_mach = aero.crossover_alt(vcas_const, mach_const)
if h_const_mach > h_cr:
print(
'Warining: const mach crossover altitude higher than cruise altitude, altitude clipped.'
)
data = []
# intitial conditions
t = 0
tcr = 0
h = 0
s = 0
v = 0
vs = 0
a = 0.5 # standard acceleration m/s^2
seg = None
while True:
data.append([t, h, s, v, vs, seg])
t = t + dt
s = s + v * dt
h = h + vs * dt
if v < v_tof:
v = v + a_tof * dt
vs = 0
seg = 'TO'
elif h < 1500 * aero.ft:
v = v + a * dt
vs = vs_ic
seg = 'IC'
elif h < h_const_cas:
v = v + a * dt
if aero.tas2cas(v, h) >= vcas_const:
v = aero.cas2tas(vcas_const, h)
vs = vs_pre_constcas
seg = 'PRE-CAS'
elif h < h_const_mach:
v = aero.cas2tas(vcas_const, h)
vs = vs_constcas
seg = 'CAS'
elif h < h_cr:
v = aero.mach2tas(mach_const, h)
vs = vs_constmach
seg = 'MACH'
else:
v = aero.mach2tas(mach_const, h)
vs = 0
seg = 'CR'
if tcr == 0:
tcr = t
if t - tcr > 60:
break
data = np.array(data)
ndata = len(data)
datadict = {
't': data[:, 0],
'h': data[:, 1] + np.random.normal(0, self.sigma_h, ndata),
's': data[:, 2] + np.random.normal(0, self.sigma_s, ndata),
'v': data[:, 3] + np.random.normal(0, self.sigma_v, ndata),
'vs': data[:, 4] + np.random.normal(0, self.sigma_vs, ndata),
'seg': data[:, 5],
'cas_const_cl': cas_const,
'mach_const_cl': mach_const,
'h_cr': h_cr
}
return datadict
def cruise(self, **kwargs):
"""Generate descent trajectory based on WRAP model.
Args:
**dt (int): Time step in seconds.
**range_cr (int): Cruise range (km).
**h_cr (int): Cruise altitude (km).
**mach_cr (float): Cruise Mach number (-).
**random (bool): Generate trajectory with random paramerters.
Returns:
dict: flight trajectory
"""
dt = kwargs.get('dt', 1)
random = kwargs.get('random', False)
if random:
range = kwargs.get(
'range_cr',
np.random.uniform(self.wrap.cruise_range()['minimum'],
self.wrap.cruise_range()['maximum']) * 1000)
h_cr = kwargs.get(
'h_cr',
np.random.uniform(self.wrap.cruise_alt()['minimum'],
self.wrap.cruise_alt()['maximum']) * 1000)
mach_cr = kwargs.get(
'mach_cr',
np.random.uniform(self.wrap.cruise_mach()['minimum'],
self.wrap.cruise_mach()['maximum']))
else:
range = kwargs.get('range_cr',
self.wrap.cruise_range()['default'] * 1000)
mach_cr = kwargs.get('mach_cr', self.wrap.cruise_mach()['default'])
h_cr = kwargs.get('h_cr', self.wrap.cruise_alt()['default'] * 1000)
h_cr = np.round(h_cr / aero.ft,
-3) * aero.ft # round cruise altitude to flight level
data = []
# intitial conditions
t = 0
s = 0
v = aero.mach2tas(mach_cr, h_cr)
vs = 0
while True:
data.append([t, h_cr, s, v, vs])
t = t + dt
s = s + v * dt
if s > range:
break
data = np.array(data)
ndata = len(data)
datadict = {
't': data[:, 0],
'h': data[:, 1] + np.random.normal(0, self.sigma_h, ndata),
's': data[:, 2] + np.random.normal(0, self.sigma_s, ndata),
'v': data[:, 3] + np.random.normal(0, self.sigma_v, ndata),
'vs': data[:, 4] + np.random.normal(0, self.sigma_vs, ndata),
'h_cr': h_cr,
'mach_cr': mach_cr,
}
return datadict
def descent(self, **kwargs):
"""Generate descent trajectory based on WRAP model.
Args:
**dt (int): Time step in seconds.
**cas_const_de (int): Constaant CAS for climb (kt).
**mach_const_de (float): Constaant Mach for climb (-).
**h_cr (int): Target cruise altitude (km).
**random (bool): Generate trajectory with random paramerters.
Returns:
dict: Flight trajectory.
"""
dt = kwargs.get('dt', 1)
random = kwargs.get('random', False)
a_lnd = self.wrap.landing_acceleration()['default']
v_app = self.wrap.finalapp_vcas()['default']
if random:
h_cr = kwargs.get(
'h_cr',
np.random.uniform(self.wrap.cruise_alt()['minimum'],
self.wrap.cruise_alt()['maximum']) * 1000)
mach_const = kwargs.get(
'mach_const_de',
np.random.uniform(self.wrap.descent_const_mach()['minimum'],
self.wrap.descent_const_mach()['maximum']))
cas_const = kwargs.get(
'cas_const_de',
np.random.uniform(self.wrap.descent_const_vcas()['minimum'],
self.wrap.descent_const_vcas()['maximum']) /
aero.kts)
vs_constmach = np.random.uniform(
self.wrap.descent_vs_conmach()['minimum'],
self.wrap.descent_vs_conmach()['maximum'])
vs_constcas = np.random.uniform(
self.wrap.descent_vs_concas()['minimum'],
self.wrap.descent_vs_concas()['maximum'])
vs_post_constcas = np.random.uniform(
self.wrap.descent_vs_post_concas()['minimum'],
self.wrap.descent_vs_post_concas()['maximum'])
else:
mach_const = kwargs.get('mach_const_de',
self.wrap.descent_const_mach()['default'])
cas_const = kwargs.get(
'cas_const_de',
self.wrap.descent_const_vcas()['default'] / aero.kts)
h_cr = kwargs.get('h_cr', self.wrap.cruise_alt()['default'] * 1000)
vs_constmach = self.wrap.descent_vs_conmach()['default']
vs_constcas = self.wrap.descent_vs_concas()['default']
vs_post_constcas = self.wrap.descent_vs_post_concas()['default']
vcas_const = cas_const * aero.kts
h_cr = np.round(h_cr / aero.ft,
-2) * aero.ft # round cruise altitude to flight level
vs_fa = self.wrap.finalapp_vs()['default']
h_const_cas = self.wrap.descent_cross_alt_concas()['default'] * 1000
h_const_mach = aero.crossover_alt(vcas_const, mach_const)
if h_const_mach > h_cr:
print(
'Warining: const mach crossover altitude higher than cruise altitude, altitude clipped.'
)
data = []
# intitial conditions
a = -0.5
t = 0
s = 0
h = h_cr
v = aero.mach2tas(mach_const, h_cr)
vs = 0
seg = None
while True:
data.append([t, h, s, v, vs, seg])
t = t + dt
s = s + v * dt
h = h + vs * dt
if t < 60:
v = aero.mach2tas(mach_const, h)
vs = 0
seg = 'CR'
elif h > h_const_mach:
v = aero.mach2tas(mach_const, h)
vs = vs_constmach
seg = 'MACH'
elif h > h_const_cas:
v = aero.cas2tas(vcas_const, h)
vs = vs_constcas
seg = 'CAS'
elif h > 1000 * aero.ft:
v = v + a * dt
if aero.tas2cas(v, h) < v_app:
v = aero.cas2tas(v_app, h)
vs = vs_post_constcas
seg = 'POST-CAS'
elif h > 0:
v = v_app
vs = vs_fa
seg = 'FA'
else:
h = 0
vs = 0
v = v + a_lnd * dt
seg = 'LD'
if v <= 0:
break
data = np.array(data)
ndata = len(data)
datadict = {
't': data[:, 0],
'h': data[:, 1] + np.random.normal(0, self.sigma_h, ndata),
's': data[:, 2] + np.random.normal(0, self.sigma_s, ndata),
'v': data[:, 3] + np.random.normal(0, self.sigma_v, ndata),
'vs': data[:, 4] + np.random.normal(0, self.sigma_vs, ndata),
'seg': data[:, 5],
'cas_const_de': cas_const,
'vcas_const_de': vcas_const,
'mach_const_de': mach_const,
'h_cr': h_cr
}
return datadict
def climb(self, **kwargs):
"""Generate climb trajectory based on WRAP model.
Args:
**dt (int): Time step in seconds.
**cas_const_cl (int): Constaant CAS for climb (kt).
**mach_const_cl (float): Constaant Mach for climb (-).
**alt_cr (int): Target cruise altitude (ft).
**random (bool): Generate trajectory with random paramerters.
Returns:
dict: Flight trajectory.
"""
dt = kwargs.get("dt", 1)
random = kwargs.get("random", False)
a_tof = self.wrap.takeoff_acceleration()["default"]
v_tof = self.wrap.takeoff_speed()["default"]
if random:
cas_const = kwargs.get(
"cas_const_cl",
np.random.uniform(
self.wrap.climb_const_vcas()["minimum"],
self.wrap.climb_const_vcas()["maximum"],
) / aero.kts,
)
mach_const = kwargs.get(
"mach_const_cl",
np.random.uniform(
self.wrap.climb_const_mach()["minimum"],
self.wrap.climb_const_mach()["maximum"],
),
)
alt_cr = kwargs.get(
"alt_cr",
np.random.uniform(self.wrap.cruise_alt()["minimum"],
self.wrap.cruise_alt()["maximum"]) * 1000 /
aero.ft,
)
vs_pre_constcas = np.random.uniform(
self.wrap.climb_vs_pre_concas()["minimum"],
self.wrap.climb_vs_pre_concas()["maximum"],
)
vs_constcas = np.random.uniform(
self.wrap.climb_vs_concas()["minimum"],
self.wrap.climb_vs_concas()["maximum"],
)
vs_constmach = np.random.uniform(
self.wrap.climb_vs_conmach()["minimum"],
self.wrap.climb_vs_conmach()["maximum"],
)
else:
cas_const = kwargs.get(
"cas_const_cl",
self.wrap.climb_const_vcas()["default"] / aero.kts)
cas_const = max(
cas_const,
v_tof / aero.kts) # cas can not be smaller then takeoff speed
mach_const = kwargs.get("mach_const_cl",
self.wrap.climb_const_mach()["default"])
alt_cr = kwargs.get(
"alt_cr",
self.wrap.cruise_alt()["default"] * 1000 / aero.ft)
vs_pre_constcas = self.wrap.climb_vs_pre_concas()["default"]
vs_constcas = self.wrap.climb_vs_concas()["default"]
vs_constmach = self.wrap.climb_vs_conmach()["default"]
vcas_const = cas_const * aero.kts
alt_cr = np.round(alt_cr, -2) # round cruise altitude to flight level
h_cr = alt_cr * aero.ft # meters
vs_ic = self.wrap.initclimb_vs()["default"]
h_const_cas = self.wrap.climb_cross_alt_concas()["default"] * 1000
h_const_mach = aero.crossover_alt(vcas_const, mach_const)
if h_const_mach > h_cr:
print(
"Warining: const mach crossover altitude higher than cruise altitude, altitude clipped."
)
data = []
# intitial conditions
t = 0
tcr = 0
h = 0
s = 0
v = 0
vs = 0
a = 0.5 # standard acceleration m/s^2
seg = None
while True:
data.append([t, h, s, v, vs, seg])
t = t + dt
s = s + v * dt
h = h + vs * dt
if v < v_tof:
v = v + a_tof * dt
vs = 0
seg = "TO"
elif h < 1500 * aero.ft:
v = v + a * dt
if aero.tas2cas(v, h) >= vcas_const:
v = aero.cas2tas(vcas_const, h)
vs = vs_ic
seg = "IC"
elif h < h_const_cas:
v = v + a * dt
if aero.tas2cas(v, h) >= vcas_const:
v = aero.cas2tas(vcas_const, h)
vs = vs_pre_constcas
seg = "PRE-CAS"
elif h < h_const_mach:
v = aero.cas2tas(vcas_const, h)
vs = vs_constcas
seg = "CAS"
elif h < h_cr:
v = aero.mach2tas(mach_const, h)
vs = vs_constmach
seg = "MACH"
else:
v = aero.mach2tas(mach_const, h)
vs = 0
seg = "CR"
if tcr == 0:
tcr = t
if t - tcr > 60:
break
data = np.array(data)
ndata = len(data)
datadict = {
"t": data[:, 0], # t, seconds
"h": data[:, 1] + np.random.normal(0, self.sigma_h, ndata), # h, m
"s": data[:, 2] + np.random.normal(0, self.sigma_s, ndata), # s, m
"v":
data[:, 3] + np.random.normal(0, self.sigma_v, ndata), # v, m/s
"vs":
data[:, 4] + np.random.normal(0, self.sigma_vs, ndata), # VS, m/s
"seg": data[:, 5],
"cas_const_cl": cas_const,
"mach_const_cl": mach_const,
"alt_cr": alt_cr, # alt_cr, ft
}
return datadict
def cruise(self, **kwargs):
"""Generate descent trajectory based on WRAP model.
Args:
**dt (int): Time step in seconds.
**range_cr (int): Cruise range (km).
**alt_cr (int): Cruise altitude (ft).
**mach_cr (float): Cruise Mach number (-).
**random (bool): Generate trajectory with random paramerters.
Returns:
dict: flight trajectory
"""
dt = kwargs.get("dt", 1)
random = kwargs.get("random", False)
if random:
range = kwargs.get(
"range_cr",
np.random.uniform(
self.wrap.cruise_range()["minimum"],
self.wrap.cruise_range()["maximum"],
) * 1000,
)
alt_cr = kwargs.get(
"alt_cr",
np.random.uniform(self.wrap.cruise_alt()["minimum"],
self.wrap.cruise_alt()["maximum"]) * 1000 /
aero.ft,
)
mach_cr = kwargs.get(
"mach_cr",
np.random.uniform(
self.wrap.cruise_mach()["minimum"],
self.wrap.cruise_mach()["maximum"],
),
)
else:
range = kwargs.get("range_cr",
self.wrap.cruise_range()["default"] * 1000)
mach_cr = kwargs.get("mach_cr", self.wrap.cruise_mach()["default"])
alt_cr = kwargs.get(
"alt_cr",
self.wrap.cruise_alt()["default"] * 1000 / aero.ft)
alt_cr = np.round(alt_cr, -2) # round cruise altitude to flight level
h_cr = alt_cr * aero.ft
data = []
# intitial conditions
t = 0
s = 0
v = aero.mach2tas(mach_cr, h_cr)
vs = 0
while True:
data.append([t, h_cr, s, v, vs])
t = t + dt
s = s + v * dt
if s > range:
break
data = np.array(data)
ndata = len(data)
datadict = {
"t": data[:, 0],
"h": data[:, 1] + np.random.normal(0, self.sigma_h, ndata),
"s": data[:, 2] + np.random.normal(0, self.sigma_s, ndata),
"v": data[:, 3] + np.random.normal(0, self.sigma_v, ndata),
"vs": data[:, 4] + np.random.normal(0, self.sigma_vs, ndata),
"alt_cr": alt_cr,
"mach_cr": mach_cr,
}
return datadict
def descent(self, **kwargs):
"""Generate descent trajectory based on WRAP model.
Args:
**dt (int): Time step in seconds.
**cas_const_de (int): Constaant CAS for climb (kt).
**mach_const_de (float): Constaant Mach for climb (-).
**alt_cr (int): Target cruise altitude (ft).
**random (bool): Generate trajectory with random paramerters.
Returns:
dict: Flight trajectory.
"""
dt = kwargs.get("dt", 1)
random = kwargs.get("random", False)
a_lnd = self.wrap.landing_acceleration()["default"]
v_app = self.wrap.finalapp_vcas()["default"]
if random:
alt_cr = kwargs.get(
"alt_cr",
np.random.uniform(self.wrap.cruise_alt()["minimum"],
self.wrap.cruise_alt()["maximum"]) * 1000 /
aero.ft,
)
mach_const = kwargs.get(
"mach_const_de",
np.random.uniform(
self.wrap.descent_const_mach()["minimum"],
self.wrap.descent_const_mach()["maximum"],
),
)
cas_const = kwargs.get(
"cas_const_de",
np.random.uniform(
self.wrap.descent_const_vcas()["minimum"],
self.wrap.descent_const_vcas()["maximum"],
) / aero.kts,
)
vs_constmach = np.random.uniform(
self.wrap.descent_vs_conmach()["minimum"],
self.wrap.descent_vs_conmach()["maximum"],
)
vs_constcas = np.random.uniform(
self.wrap.descent_vs_concas()["minimum"],
self.wrap.descent_vs_concas()["maximum"],
)
vs_post_constcas = np.random.uniform(
self.wrap.descent_vs_post_concas()["minimum"],
self.wrap.descent_vs_post_concas()["maximum"],
)
else:
mach_const = kwargs.get("mach_const_de",
self.wrap.descent_const_mach()["default"])
cas_const = kwargs.get(
"cas_const_de",
self.wrap.descent_const_vcas()["default"] / aero.kts)
alt_cr = kwargs.get(
"alt_cr",
self.wrap.cruise_alt()["default"] * 1000 / aero.ft)
vs_constmach = self.wrap.descent_vs_conmach()["default"]
vs_constcas = self.wrap.descent_vs_concas()["default"]
vs_post_constcas = self.wrap.descent_vs_post_concas()["default"]
vcas_const = cas_const * aero.kts
alt_cr = np.round(alt_cr, -2) # round cruise altitude to flight level
h_cr = alt_cr * aero.ft
vs_fa = self.wrap.finalapp_vs()["default"]
h_const_cas = self.wrap.descent_cross_alt_concas()["default"] * 1000
h_const_mach = aero.crossover_alt(vcas_const, mach_const)
if h_const_mach > h_cr:
print(
"Warining: const mach crossover altitude higher than cruise altitude, altitude clipped."
)
data = []
# intitial conditions
a = -0.5
t = 0
s = 0
h = h_cr
v = aero.mach2tas(mach_const, h_cr)
vs = 0
seg = None
while True:
data.append([t, h, s, v, vs, seg])
t = t + dt
s = s + v * dt
h = h + vs * dt
if t < 60:
v = aero.mach2tas(mach_const, h)
vs = 0
seg = "CR"
elif h > h_const_mach:
v = aero.mach2tas(mach_const, h)
vs = vs_constmach
seg = "MACH"
elif h > h_const_cas:
v = aero.cas2tas(vcas_const, h)
vs = vs_constcas
seg = "CAS"
elif h > 1000 * aero.ft:
v = v + a * dt
if aero.tas2cas(v, h) < v_app:
v = aero.cas2tas(v_app, h)
vs = vs_post_constcas
seg = "POST-CAS"
elif h > 0:
v = v_app
vs = vs_fa
seg = "FA"
else:
h = 0
vs = 0
v = v + a_lnd * dt
seg = "LD"
if v <= 0:
break
data = np.array(data)
ndata = len(data)
datadict = {
"t": data[:, 0],
"h": data[:, 1] + np.random.normal(0, self.sigma_h, ndata),
"s": data[:, 2] + np.random.normal(0, self.sigma_s, ndata),
"v": data[:, 3] + np.random.normal(0, self.sigma_v, ndata),
"vs": data[:, 4] + np.random.normal(0, self.sigma_vs, ndata),
"seg": data[:, 5],
"cas_const_de": cas_const,
"vcas_const_de": vcas_const,
"mach_const_de": mach_const,
"alt_cr": alt_cr,
}
return datadict