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test_bada.py
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test_bada.py
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# -*- coding: utf-8 -*-
# %%
import os
import sys
import inspect
from math import *
from dataclasses import dataclass
from importlib import util
import pandas as pd
from traffic.core import Traffic
from mass import FuelEstimator
import numpy as np
import pandas as pd
from flight import (
FlightProfiles,
FlightProfileGenerator,
_to_df,
gen_flight_profile,
FlightPhaseEstimator,
gentraj,
)
import openturns as ot
import openturns.viewer as viewer
ot.RandomGenerator.SetSeed(0)
currentdir = os.path.dirname(os.path.abspath(inspect.getfile(inspect.currentframe())))
parentdir = os.path.dirname(currentdir)
sys.path.insert(0, parentdir)
sys.path.insert(0, parentdir + "/pyBADA")
import pybada.atmosphere as atm
import pybada.conversions as conv
import pybada.TCL as TCL
from pybada.flightTrajectory import FlightTrajectory as FT
# import BADA3, BADA4 and BADAH modules
# handling missing/selective availability of BADA 3/4/H modules
from pybada.bada4 import Bada4Aircraft
# %%
@dataclass
class target:
ROCDtarget: float = None
slopetarget: float = None
acctarget: float = None
ESFtarget: float = None
def bada_calc(
ac_type,
payload,
fuel,
cruising_dist, # NM
Mcl,
Mcr,
Mdes,
Vcl2,
Vdes2,
Hp_CR=33000, # [ft] CRUISing level,
):
# define path to the folder where BADA model can be found (modify if necessary)
aircraft_path_BADA3 = parentdir + "/pybada/aircraft/BADA3/"
aircraft_path_BADA4 = parentdir + "/pybada/aircraft/BADA4/"
output_path = parentdir + "/sensiflow/bada_test"
# initialization of BADA3/4
# uncomment for testing different BADA family if available
AC = Bada4Aircraft(aircraft_path_BADA4, ac_type)
# create a Flight Trajectory object to store the output from TCL segment calculations
ft = FT()
# default parameters
speedType = "CAS" # {M, CAS, TAS}
wS = 0 # [kt] wind speed
ba = 0 # [deg] bank angle
DeltaTau = 0 # [K] delta temperature from ISA
# Initial conditions
m_init = AC.OEW + payload + fuel # [kg] initial mass
Hp_RWY = 0 # [ft] RWY altitude
# take-off conditions
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(Hp_RWY), DeltaTau=DeltaTau
) # atmosphere properties at RWY altitude
[cas_cl1, speedUpdated] = AC.ARPM.climbSpeed(
h=conv.ft2m(Hp_RWY), mass=m_init, theta=theta, delta=delta, DeltaTau=DeltaTau
) # [m/s] take-off CAS
# BADA speed schedule
[Vcl1, _, _] = AC.flightEnvelope.getSpeedSchedule(
phase="Climb"
) # BADA Climb speed schedule
[Vcr1, Vcr2, _] = AC.flightEnvelope.getSpeedSchedule(
phase="Cruise"
) # BADA Cruise speed schedule
[Vdes1, _, _] = AC.flightEnvelope.getSpeedSchedule(
phase="Descent"
) # BADA Descent speed schedule
# ----------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------------
# CLIMB to threshold altitude 1500ft at take-off speed
# ------------------------------------------------
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="CAS",
v=conv.ms2kt(cas_cl1),
Hp_init=Hp_RWY,
Hp_final=1499,
m_init=m_init,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# accelerate according to BADA ARPM for below 3000ft
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(2999), DeltaTau=DeltaTau
)
[cas_cl2, speedUpdated] = AC.ARPM.climbSpeed(
h=conv.ft2m(2999), mass=m_final, theta=theta, delta=delta, DeltaTau=DeltaTau
)
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas_cl2),
Hp_init=Hp,
control=None,
phase="Climb",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# CLIMB to threshold altitude 3000ft
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=2999,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# accelerate according to BADA ARPM for below 4000ft
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(3999), DeltaTau=DeltaTau
)
[cas_cl3, speedUpdated] = AC.ARPM.climbSpeed(
h=conv.ft2m(3999), mass=m_final, theta=theta, delta=delta, DeltaTau=DeltaTau
)
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas_cl3),
Hp_init=Hp,
control=None,
phase="Climb",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# CLIMB to threshold altitude 4000ft
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=3999,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# accelerate according to BADA ARPM for below 5000ft
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(4999), DeltaTau=DeltaTau
)
[cas_cl4, speedUpdated] = AC.ARPM.climbSpeed(
h=conv.ft2m(4999), mass=m_final, theta=theta, delta=delta, DeltaTau=DeltaTau
)
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas_cl4),
Hp_init=Hp,
control=None,
phase="Climb",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# CLIMB to threshold altitude 5000ft
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=4999,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# accelerate according to BADA ARPM for below 6000ft
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(5999), DeltaTau=DeltaTau
)
[cas_cl5, speedUpdated] = AC.ARPM.climbSpeed(
h=conv.ft2m(5999), mass=m_final, theta=theta, delta=delta, DeltaTau=DeltaTau
)
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas_cl5),
Hp_init=Hp,
control=None,
phase="Climb",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# CLIMB to threshold altitude 6000ft
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=5999,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# accelerate according to BADA ARPM for below 10000ft
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(9999), DeltaTau=DeltaTau
)
[cas_cl6, speedUpdated] = AC.ARPM.climbSpeed(
h=conv.ft2m(9999), mass=m_final, theta=theta, delta=delta, DeltaTau=DeltaTau
)
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas_cl6),
Hp_init=Hp,
control=None,
phase="Climb",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# CLIMB to threshold altitude 10000ft
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=9999,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# accelerate according to BADA ARPM for above 10000ft and below crossover altitude
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(Vcl2),
Hp_init=Hp,
control=None,
phase="Climb",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# CLIMB to crossover altitude
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
# calculate the crosover altitude for climb phase
crossoverAltitude = conv.m2ft(atm.crossOver(Vcl2, Mcl))
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=crossoverAltitude,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# climb at M from crossover altitude
# ------------------------------------------------
# current values
Hp, m_final = ft.getFinalValue(AC, ["Hp", "mass"])
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="M",
v=Mcl,
Hp_init=Hp,
Hp_final=Hp_CR,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# if not at CR speed -> adapt the speed first (acc/dec)
# ------------------------------------------------
# current values
Hp, m_final, M_final = ft.getFinalValue(AC, ["Hp", "mass", "M"])
if M_final < Mcr:
control = target(acctarget=0.5)
flightTrajectory = TCL.accDec(
AC=AC,
speedType="M",
v_init=M_final,
v_final=Mcr,
Hp_init=Hp,
control=control,
phase="Cruise",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# CRUISE for 200 NM
# ------------------------------------------------
# current values
Hp, m_final = ft.getFinalValue(AC, ["Hp", "mass"])
flightTrajectory = TCL.constantSpeedCruise(
AC=AC,
lengthType="distance",
length=cruising_dist,
speedType="M",
v=Mcr,
Hp_init=Hp,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# # CRUISE for 200 NM
# # ------------------------------------------------
# # current values
# Hp, m_final = ft.getFinalValue(AC, ["Hp", "mass"])
# flightTrajectory = TCL.constantSpeedCruise(
# AC=AC,
# lengthType="distance",
# length=200,
# step_length=50,
# maxRFL=36000,
# speedType="M",
# v=Mcr,
# Hp_init=Hp,
# m_init=m_final,
# stepClimb=True,
# wS=wS,
# bankAngle=ba,
# DeltaTau=DeltaTau,
# )
# ft.append(AC, flightTrajectory)
# acc/dec to DESCENT speed during the descend
# ------------------------------------------------
# current values
Hp, m_final, M_final = ft.getFinalValue(AC, ["Hp", "mass", "M"])
flightTrajectory = TCL.accDec(
AC=AC,
speedType="M",
v_init=M_final,
v_final=Mdes,
Hp_init=Hp,
phase="Descent",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend to crossover altitude
# ------------------------------------------------
# current values
Hp, m_final = ft.getFinalValue(AC, ["Hp", "mass"])
# calculate the crosover altitude for descend phase
crossoverAltitude = conv.m2ft(atm.crossOver(Vdes2, Mdes))
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="M",
v=Mdes,
Hp_init=Hp,
Hp_final=crossoverAltitude,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend to FL100
# ------------------------------------------------
# current values
Hp, m_final = ft.getFinalValue(AC, ["Hp", "mass"])
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="CAS",
v=conv.ms2kt(Vdes2),
Hp_init=Hp,
Hp_final=10000,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# decelerate according to BADA ARPM for below FL100
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
# get BADA target speed from BADA ARPM procedure for the altitude bracket below
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(9999), DeltaTau=DeltaTau
)
[cas, speedUpdated] = AC.ARPM.descentSpeed(
h=conv.ft2m(9999), mass=m_final, theta=theta, delta=delta, DeltaTau=DeltaTau
)
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas),
Hp_init=Hp,
phase="Descent",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend to 6000ft
# ------------------------------------------------
# current values
Hp, m_final = ft.getFinalValue(AC, ["Hp", "mass"])
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="CAS",
v=conv.ms2kt(cas),
Hp_init=Hp,
Hp_final=6000,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# decelerate according to BADA ARPM for below 6000
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
# get BADA target speed from BADA ARPM procedure for the altitude bracket below
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(5999), DeltaTau=DeltaTau
)
[cas, speedUpdated] = AC.ARPM.descentSpeed(
h=conv.ft2m(5999), mass=m_final, theta=theta, delta=delta, DeltaTau=DeltaTau
)
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas),
Hp_init=Hp,
phase="Descent",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend to 5000ft
# ------------------------------------------------
# current values
Hp, m_final = ft.getFinalValue(AC, ["Hp", "mass"])
flightTrajectory = TCL.constantSpeedRating(
AC=AC,
speedType="CAS",
v=conv.ms2kt(cas),
Hp_init=Hp,
Hp_final=5000,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend on ILS with 3deg glideslope to next altitude threshold
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
if AC.BADAFamily.BADA3:
flightTrajectory = TCL.constantSpeedSlope(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=3700,
slopetarget=-3.0,
config="AP",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
elif AC.BADAFamily.BADA4:
flightTrajectory = TCL.constantSpeedSlope(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=3000,
slopetarget=-3.0,
config=None,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend on ILS with 3deg glideslope while decelerating
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
# get BADA target speed from BADA ARPM procedure for the altitude bracket below
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(2999), DeltaTau=DeltaTau
)
[cas, speedUpdated] = AC.ARPM.descentSpeed(
h=conv.ft2m(2999), mass=m_final, theta=theta, delta=delta, DeltaTau=DeltaTau
)
control = target(slopetarget=-3.0)
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas),
Hp_init=Hp,
control=control,
phase="Descent",
config="AP",
speedBrakes=True,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend on ILS with 3deg glideslope to next altitude threshold
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
if Hp > 2000:
flightTrajectory = TCL.constantSpeedSlope(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=2000,
slopetarget=-3.0,
config=None,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend on ILS with 3deg glideslope while decelerating
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
# get BADA target speed from BADA ARPM procedure for the altitude bracket below
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(1999), DeltaTau=DeltaTau
)
[cas, speedUpdated] = AC.ARPM.descentSpeed(
h=conv.ft2m(1999), mass=m_final, theta=theta, delta=delta, DeltaTau=DeltaTau
)
control = target(slopetarget=-3.0)
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas),
Hp_init=Hp,
control=control,
phase="Descent",
config="LD",
speedBrakes=True,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend on ILS with 3deg glideslope to next altitude threshold
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
if Hp > 1500:
flightTrajectory = TCL.constantSpeedSlope(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=1500,
slopetarget=-3.0,
config="LD",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend on ILS with 3deg glideslope while decelerating
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
# get BADA target speed from BADA ARPM procedure for the altitude bracket below
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(1499), DeltaTau=DeltaTau
)
[cas, speedUpdated] = AC.ARPM.descentSpeed(
h=conv.ft2m(1499), mass=m_final, theta=theta, delta=delta, DeltaTau=DeltaTau
)
control = target(slopetarget=-3.0)
if AC.BADAFamily.BADA3:
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas),
Hp_init=Hp,
control=control,
phase="Descent",
config="LD",
speedBrakes=True,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
elif AC.BADAFamily.BADA4:
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas),
Hp_init=Hp,
control=control,
phase="Descent",
config="LD",
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend on ILS with 3deg glideslope to next altitude threshold
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
if Hp > 1000:
flightTrajectory = TCL.constantSpeedSlope(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=1000,
slopetarget=-3.0,
config=None,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend on ILS with 3deg glideslope while decelerating
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
# get BADA target speed from BADA ARPM procedure for the altitude bracket below
[theta, delta, sigma] = atm.atmosphereProperties(
h=conv.ft2m(999), DeltaTau=DeltaTau
)
[cas, speedUpdated] = AC.ARPM.descentSpeed(
h=conv.ft2m(999), mass=m_final, theta=theta, delta=delta, DeltaTau=DeltaTau
)
control = target(slopetarget=-3.0)
if AC.BADAFamily.BADA3:
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas),
Hp_init=Hp,
control=control,
phase="Descent",
config=None,
speedBrakes=True,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
elif AC.BADAFamily.BADA4:
flightTrajectory = TCL.accDec(
AC=AC,
speedType="CAS",
v_init=CAS_final,
v_final=conv.ms2kt(cas),
Hp_init=Hp,
control=control,
phase="Descent",
config=None,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# descend on ILS with 3deg glideslope to next altitude threshold
# ------------------------------------------------
# current values
Hp, m_final, CAS_final = ft.getFinalValue(AC, ["Hp", "mass", "CAS"])
flightTrajectory = TCL.constantSpeedSlope(
AC=AC,
speedType="CAS",
v=CAS_final,
Hp_init=Hp,
Hp_final=Hp_RWY,
slopetarget=-3.0,
config=None,
m_init=m_final,
wS=wS,
bankAngle=ba,
DeltaTau=DeltaTau,
)
ft.append(AC, flightTrajectory)
# save the output to a CSV file
# ------------------------------------------------
return pd.DataFrame.from_dict(next(iter(ft.FT.items()))[1], orient="index").T
# %%
ac_type = "B744"
ac_type_bada = "B744GE"
mission_size = 800
def test_openturns(X):
# Transforming the input into np array
# Xarray = np.array(X, copy=False)
# Getting data from X
# age = Xarray[:, 2]
# Fuel Calculation with PDFs
def fuel_estimate():
load_factor = X[0][0]
weight_person = X[0][1]
cas_const_cl = X[0][2]
mach_const_cl = X[0][3]
cas_const_de = X[0][4]
mach_const_de = X[0][5]
range_cr = X[0][6]
alt_cr = X[0][7]
mach_cr = X[0][8]
traj = gentraj(
ac_type,
cas_const_cl=cas_const_cl,
mach_const_cl=mach_const_cl,
cas_const_de=cas_const_de,
mach_const_de=mach_const_de,
range_cr=range_cr,
alt_cr=alt_cr,
mach_cr=mach_cr,
dt=20,
)
fe = FuelEstimator(
ac_type=ac_type,
passenger_mass=weight_person,
load_factor=load_factor,
)
df = FlightPhaseEstimator()(_to_df(traj))
fp = FlightProfiles.from_df(df)
return fe(fp).to_df().fc.iloc[-1]
fuel = fuel_estimate()
seats = pd.read_csv("data/seats.csv")
seats = int(seats.query("ac_type == @ac_type").nb_seats)
cumul = []
for sample in X:
load_factor = sample[0]
weight_person = sample[1]
cas_const_cl = sample[2]
mach_const_cl = sample[3]
cas_const_de = sample[4]
mach_const_de = sample[5]
range_cr = sample[6]
alt_cr = sample[7]
mach_cr = sample[8]
traj = bada_calc(
ac_type_bada,
(int(load_factor * seats) * weight_person),
fuel,
range_cr * 0.539957, # NM
mach_const_cl,
mach_cr,
mach_const_de,
cas_const_cl,
cas_const_de,
alt_cr, # [ft] CRUISing level,
)
traj["ff"] = (traj["time"] - traj["time"].shift(1)) * traj["FUEL"]
cumul.append([traj.ff.sum()])
return cumul
# test_openturns([[100, 0.8, 0.07]])
# %%
def get_dist(var):
if var["statmodel"] == "beta":
return ot.Beta(
var["statmodel_params"][0],
var["statmodel_params"][1],
var["minimum"],
var["maximum"],
)
elif var["statmodel"] == "norm":
return ot.TruncatedDistribution(
ot.Normal(*var["statmodel_params"]),
var["minimum"],
var["maximum"],