def __init__(self):
TrafficArrays.__init__(self)
# [m] Horizontal separation minimum for detection
self.rpz = bs.settings.asas_pzr * nm
# [m] Vertical separation minimum for detection
self.hpz = bs.settings.asas_pzh * ft
# [s] lookahead time
self.dtlookahead = bs.settings.asas_dtlookahead
self.dtnolook = 0.0
# Conflicts and LoS detected in the current timestep (used for resolving)
self.confpairs = list()
self.lospairs = list()
self.qdr = np.array([])
self.dist = np.array([])
self.dcpa = np.array([])
self.tcpa = np.array([])
self.tLOS = np.array([])
# Unique conflicts and LoS in the current timestep (a, b) = (b, a)
self.confpairs_unique = set()
self.lospairs_unique = set()
# All conflicts and LoS since simt=0
self.confpairs_all = list()
self.lospairs_all = list()
# Per-aircraft conflict data
with RegisterElementParameters(self):
self.inconf = np.array([], dtype=bool) # In-conflict flag
self.tcpamax = np.array([]) # Maximum time to CPA for aircraft in conflict
def __init__(self, min_update_dt=1):
super(OpenAP, self).__init__()
self.min_update_dt = min_update_dt # second, minimum update dt
self.current_sim_time = 0 # last update simulation time
self.ac_warning = False # aircraft mdl to default warning
self.eng_warning = False # aircraft engine to default warning
self.coeff = coeff.Coefficient()
with RegisterElementParameters(self):
self.actypes = np.array([], dtype=str)
self.phase = np.array([])
self.lifttype = np.array([]) # lift type, fixwing [1] or rotor [2]
self.engnum = np.array([], dtype=int) # number of engines
self.engthrust = np.array([]) # static engine thrust
self.engbpr = np.array([]) # engine bypass ratio
self.thrustratio = np.array([]) # thrust ratio at current alt spd
self.ff_coeff_a = np.array([]) # icao fuel flows coefficient a
self.ff_coeff_b = np.array([]) # icao fuel flows coefficient b
self.ff_coeff_c = np.array([]) # icao fuel flows coefficient c
self.engpower = np.array([]) # engine power, rotor ac
self.cd0 = np.array([]) # zero drag coefficient
self.cd0_clean = np.array([]) # Cd0, clean configuration
self.cd0_gd = np.array([]) # Cd0, ground mode
self.cd0_to = np.array([]) # Cd0, taking-off
self.cd0_ic = np.array([]) # Cd0, initial climb
self.cd0_ap = np.array([]) # Cd0, landing
self.cd0_ld = np.array([]) # Cd0, landing
self.k = np.array([]) # induced drag coeff
def __init__(self):
super(ActiveWaypoint, self).__init__()
with RegisterElementParameters(self):
self.lat = np.array([]) # [deg] Active WP latitude
self.lon = np.array([]) # [deg] Active WP longitude
self.nextaltco = np.array(
[]) # [m] Altitude to arrive at after distance xtoalt
self.xtoalt = np.array(
[]) # [m] Distance to next altitude constraint
self.nextspd = np.array(
[]) # [CAS[m/s]/Mach] save speed from next wp for next leg
self.spd = np.array(
[]
) # [CAS[m/s]/Mach]Active WP speed (constraint or calculated)
self.spdcon = np.array(
[]) # [CAS[m/s]/Mach]Active WP speed constraint
self.vs = np.array([]) # [m/s] Active vertical speed to use
self.turndist = np.array(
[]) # [m] Distance when to turn to next waypoint
self.flyby = np.array(
[]) # Flyby switch, when False, flyover (turndist=0.0)
self.torta = np.array(
[]) # [s] NExt req Time of Arrival (RTA) (-999. = None)
self.xtorta = np.array([]) # [m] distance ot next RTA
self.next_qdr = np.array([]) # [deg] track angle of next leg
def __init__(self):
super(Autopilot, self).__init__()
# Scheduling of FMS and ASAS
self.t0 = -999. # last time fms was called
self.dt = 1.01 # interval for fms
# Standard self.steepness for descent
self.steepness = 3000. * ft / (10. * nm)
# From here, define object arrays
with RegisterElementParameters(self):
# FMS directions
self.trk = np.array([])
self.spd = np.array([])
self.tas = np.array([])
self.alt = np.array([])
self.vs = np.array([])
# VNAV variables
self.dist2vs = np.array([]) # distance from coming waypoint to TOD
self.swvnavvs = np.array([]) # whether to use given VS or not
self.vnavvs = np.array([]) # vertical speed in VNAV
# Traffic navigation information
self.orig = [] # Four letter code of origin airport
self.dest = [] # Four letter code of destination airport
# Route objects
self.route = []
def __init__(self):
TrafficArrays.__init__(self)
# Standard self.steepness for descent
self.steepness = 3000. * ft / (10. * nm)
# From here, define object arrays
with RegisterElementParameters(self):
# FMS directions
self.trk = np.array([])
self.spd = np.array([])
self.tas = np.array([])
self.alt = np.array([])
self.vs = np.array([])
# VNAV variables
self.dist2vs = np.array([]) # distance from coming waypoint to TOD
self.swvnavvs = np.array([]) # whether to use given VS or not
self.vnavvs = np.array([]) # vertical speed in VNAV
# LNAV variables
self.qdr2wp = np.array(
[]
) # Direction to waypoint from the last time passing was checked
# to avoid 180 turns due to updated qdr shortly before passing wp
# Traffic navigation information
self.orig = [] # Four letter code of origin airport
self.dest = [] # Four letter code of destination airport
# Route objects
self.route = []
def __init__(self):
TrafficArrays.__init__(self)
# Standard self.steepness for descent
self.steepness = 3000. * ft / (10. * nm)
# From here, define object arrays
with RegisterElementParameters(self):
# FMS directions
self.trk = np.array([])
self.spd = np.array([])
self.tas = np.array([])
self.alt = np.array([])
self.vs = np.array([])
# VNAV variables
self.dist2vs = np.array([]) # distance from coming waypoint to TOD
self.swvnavvs = np.array([]) # whether to use given VS or not
self.vnavvs = np.array([]) # vertical speed in VNAV
# Traffic navigation information
self.orig = [] # Four letter code of origin airport
self.dest = [] # Four letter code of destination airport
# Route objects
self.route = []
def __init__(self):
# Initialize the groups structure
super(TrafficGroups, self).__init__()
self.groups = dict()
self.allmasks = 0
with RegisterElementParameters(self):
self.ingroup = np.array([], dtype=np.int64)
def __init__(self):
super(Pilot, self).__init__()
with RegisterElementParameters(self):
# Desired aircraft states
self.alt = np.array([]) # desired altitude [m]
self.hdg = np.array([]) # desired heading [deg]
self.trk = np.array([]) # desired track angle [deg]
self.vs = np.array([]) # desired vertical speed [m/s]
self.tas = np.array([]) # desired speed [m/s]
def __init__(self):
super(ActiveWaypoint, self).__init__()
with RegisterElementParameters(self):
self.lat = np.array([]) # [deg] Active WP latitude
self.lon = np.array([]) # [deg] Active WP longitude
self.nextaltco = np.array([]) # [m] Altitude to arrive at after distance xtoalt
self.xtoalt = np.array([]) # [m] Distance to next altitude constraint
self.spd = np.array([]) # [CAS[m/s]/Mach]Active WP speed
self.vs = np.array([]) # [m/s] Active vertical speed to use
self.turndist = np.array([]) # [m] Distance when to turn to next waypoint
self.flyby = np.array([]) # Flyby switch, when False, flyover (turndist=0.0)
self.next_qdr = np.array([]) # [deg] track angle of next leg
def __init__(self):
super(ASAS, self).__init__()
with RegisterElementParameters(self):
# ASAS info per aircraft:
self.inconf = np.array([], dtype=bool) # In-conflict flag per aircraft
self.tcpamax = np.array([]) # Maximum time to CPA for aircraft in conflict
self.active = np.array([], dtype=bool) # whether the autopilot follows ASAS or not
self.trk = np.array([]) # heading provided by the ASAS [deg]
self.tas = np.array([]) # speed provided by the ASAS (eas) [m/s]
self.alt = np.array([]) # speed alt by the ASAS [m]
self.vs = np.array([]) # speed vspeed by the ASAS [m/s]
# All ASAS variables are initialized in the reset function
self.reset()
def __init__(self):
super(ASAS, self).__init__()
with RegisterElementParameters(self):
# ASAS info per aircraft:
self.iconf = [] # index in 'conflicting' aircraft database
self.active = np.array([], dtype=bool) # whether the autopilot follows ASAS or not
self.trk = np.array([]) # heading provided by the ASAS [deg]
self.tas = np.array([]) # speed provided by the ASAS (eas) [m/s]
self.alt = np.array([]) # speed alt by the ASAS [m]
self.vs = np.array([]) # speed vspeed by the ASAS [m/s]
# All ASAS variables are initialized in the reset function
self.reset()
def __init__(self):
super(ActiveWaypoint, self).__init__()
with RegisterElementParameters(self):
self.lat = np.array([]) # Active WP latitude
self.lon = np.array([]) # Active WP longitude
self.nextaltco = np.array(
[]) # Altitude to arrive at after distance xtoalt
self.xtoalt = np.array([]) # Distance to next altitude constraint
self.spd = np.array([]) # Active WP speed
self.vs = np.array([]) # Active vertical speed to use
self.turndist = np.array(
[]) # Distance when to turn to next waypoint
self.flyby = np.array([]) # Distance when to turn to next waypoint
self.next_qdr = np.array([]) # bearing next leg
def __init__(self):
TrafficArrays.__init__(self)
# From here, define object arrays
with RegisterElementParameters(self):
# Most recent broadcast data
self.lastupdate = np.array([])
self.lat = np.array([])
self.lon = np.array([])
self.alt = np.array([])
self.trk = np.array([])
self.tas = np.array([])
self.gs = np.array([])
self.vs = np.array([])
self.setnoise(False)
def __init__(self):
super(ADSB, self).__init__()
# From here, define object arrays
with RegisterElementParameters(self):
# Most recent broadcast data
self.lastupdate = np.array([])
self.lat = np.array([])
self.lon = np.array([])
self.alt = np.array([])
self.trk = np.array([])
self.tas = np.array([])
self.gs = np.array([])
self.vs = np.array([])
self.SetNoise(False)
def __init__(self):
super(OpenAP, self).__init__()
self.ac_warning = False # aircraft mdl to default warning
self.eng_warning = False # aircraft engine to default warning
self.coeff = coeff.Coefficient()
with RegisterElementParameters(self):
self.actypes = np.array([], dtype=str)
self.phase = np.array([])
self.lifttype = np.array([]) # lift type, fixwing [1] or rotor [2]
self.mass = np.array([]) # mass of aircraft
self.engnum = np.array([], dtype=int) # number of engines
self.engthrmax = np.array([]) # static engine thrust
self.engbpr = np.array([]) # engine bypass ratio
self.thrust = np.array([]) # thrust ratio at current alt spd
self.max_thrust = np.array([]) # thrust ratio at current alt spd
self.ff_coeff_a = np.array([]) # icao fuel flows coefficient a
self.ff_coeff_b = np.array([]) # icao fuel flows coefficient b
self.ff_coeff_c = np.array([]) # icao fuel flows coefficient c
self.engpower = np.array([]) # engine power, rotor ac
self.cd0 = np.array([]) # zero drag coefficient
self.cd0_clean = np.array([]) # Cd0, clean configuration
self.k_clean = np.array([]) # k, clean configuration
self.cd0_to = np.array([]) # Cd0, takeoff configuration
self.k_to = np.array([]) # k, takeoff configuration
self.cd0_ld = np.array([]) # Cd0, landing configuration
self.k_ld = np.array([]) # k, landing configuration
self.delta_cd_gear = np.array([]) # landing gear
self.vmin = np.array([])
self.vmax = np.array([])
self.vminic = np.array([])
self.vminer = np.array([])
self.vminap = np.array([])
self.vmaxic = np.array([])
self.vmaxer = np.array([])
self.vmaxap = np.array([])
self.vsmin = np.array([])
self.vsmax = np.array([])
self.hmax = np.array([])
self.axmax = np.array([])
self.vminto = np.array([])
self.hcross = np.array([])
self.mmo = np.array([])
def __init__(self, min_update_dt=1):
super(PerfNAP, self).__init__()
self.min_update_dt = min_update_dt # second, minimum update dt
self.current_sim_time = 0 # last update simulation time
self.ac_warning = False # aircraft mdl to default warning
self.eng_warning = False # aircraft engine to default warning
self.coeff = coeff.Coefficient()
with RegisterElementParameters(self):
self.engnum = np.array([]) # number of engines
self.engthrust = np.array([]) # static engine thrust
self.engbpr = np.array([]) # engine bypass ratio
self.thrustratio = np.array([]) # thrust ratio at current alt spd
self.fficao = np.array(
[]) # list of icao fuel flows from emission data bank
def __init__(self):
super(PerfBase, self).__init__()
with RegisterElementParameters(self):
# --- fixed parameters ---
self.actype = np.array([], dtype=str) # aircraft type
self.Sref = np.array([]) # wing reference surface area [m^2]
self.engtype = np.array([]) # integer, aircraft.ENG_TF...
# --- dynamic parameters ---
self.mass = np.array([]) # effective mass [kg]
self.phase = np.array([])
self.cd0 = np.array([])
self.k = np.array([])
self.bank = np.array([])
self.thrust = np.array([]) # thrust
self.drag = np.array([]) # drag
self.fuelflow = np.array([]) # fuel flow
def __init__(self, dttrail=10.):
super(Trails, self).__init__()
self.active = False # Wether or not to show trails
self.dt = dttrail # Resolution of trail pieces in time
self.tcol0 = 60. # After how many seconds old colour
# This list contains some standard colors
self.colorList = {
'BLUE': np.array([0, 0, 255]),
'CYAN': np.array([0, 255, 255]),
'RED': np.array([255, 0, 0]),
'YELLOW': np.array([255, 255, 0])
}
# Set default color to Blue
self.defcolor = self.colorList['CYAN']
# Foreground data on line pieces
self.lat0 = np.array([])
self.lon0 = np.array([])
self.lat1 = np.array([])
self.lon1 = np.array([])
self.time = np.array([])
self.col = []
self.fcol = np.array([])
# background copy of data
self.bglat0 = np.array([])
self.bglon0 = np.array([])
self.bglat1 = np.array([])
self.bglon1 = np.array([])
self.bgtime = np.array([])
self.bgcol = []
with RegisterElementParameters(self):
self.accolor = []
self.lastlat = np.array([])
self.lastlon = np.array([])
self.lasttim = np.array([])
self.clearnew()
return
def __init__(self):
TrafficArrays.__init__(self)
with RegisterElementParameters(self):
self.lat = np.array([]) # [deg] Active WP latitude
self.lon = np.array([]) # [deg] Active WP longitude
self.nextaltco = np.array(
[]) # [m] Altitude to arrive at after distance xtoalt
self.xtoalt = np.array(
[]) # [m] Distance to next altitude constraint
self.nextspd = np.array(
[]) # [CAS[m/s]/Mach] save speed from next wp for next leg
self.spd = np.array(
[]
) # [CAS[m/s]/Mach]Active WP speed (constraint or calculated)
self.spdcon = np.array(
[]) # [CAS[m/s]/Mach]Active WP speed constraint
self.vs = np.array([]) # [m/s] Active vertical speed to use
self.turndist = np.array(
[]) # [m] Distance when to turn to next waypoint
self.flyby = np.array(
[]) # Flyby switch, when False, flyover (turndist=0.0)
self.flyturn = np.array(
[]
) # Flyturn switch, when False, when Fkase, use flyby/flyover
self.turnrad = np.array(
[]) # Flyturn turn radius (<0 => not specified)
self.turnspd = np.array(
[]
) # [m/s, CAS] Flyturn turn speed for next turn (<=0 => not specified)
self.oldturnspd = np.array(
[]
) # [TAS, m/s] Flyturn turn speed for previous turn (<=0 => not specified)
self.turnfromlastwp = np.array(
[]
) # Currently in flyturn-mode from last waypoint (old turn, beginning of leg)
self.turntonextwp = np.array(
[]
) # Currently in flyturn-mode to next waypoint (new flyturn mode, end of leg)
self.torta = np.array(
[]) # [s] NExt req Time of Arrival (RTA) (-999. = None)
self.xtorta = np.array([]) # [m] distance ot next RTA
self.next_qdr = np.array([]) # [deg] track angle of next leg
def __init__(self):
super(Afms, self).__init__()
# Parameters of afms
self.dt = 60.0 # [s] frequency of afms update (simtime)
self.skip2next_rta_time_s = 300.0 # Time when skipping to the RTA beyond the active RTA
self.rta_standard_window_size = 60. # [s] standard time window size for rta in seconds
self._patch_route(self.rta_standard_window_size)
self._fms_modes = ['OFF', 'CONTINUE', 'OWN', 'RTA', 'TW']
traf.resultstosave2 = pd.DataFrame()
traf.resultstosave3 = pd.DataFrame()
traf.index = 0
# Adaptations by Johannes
with RegisterElementParameters(self):
# Set required for multiple fms-mode runs
self.interval_counter = np.array([0])
self.currentwp = np.array([])
self.lat = np.array([])
self.lon = np.array([])
self.index = np.array([])
def __init__(self):
TrafficArrays.__init__(self)
# [-] switch to activate priority rules for conflict resolution
self.swprio = False # switch priority on/off
self.priocode = '' # select priority mode
self.resopairs = set() # Resolved conflicts that are still before CPA
# Resolution factors:
# set < 1 to maneuver only a fraction of the resolution
# set > 1 to add a margin to separation values
self.resofach = bs.settings.asas_mar
self.resofacv = bs.settings.asas_mar
with RegisterElementParameters(self):
self.resooffac = np.array([], dtype=np.bool)
self.noresoac = np.array([], dtype=np.bool)
# whether the autopilot follows ASAS or not
self.active = np.array([], dtype=bool)
self.trk = np.array([]) # heading provided by the ASAS [deg]
self.tas = np.array([]) # speed provided by the ASAS (eas) [m/s]
self.alt = np.array([]) # alt provided by the ASAS [m]
self.vs = np.array([]) # vspeed provided by the ASAS [m/s]
def __init__(self, min_update_dt=1):
super(OpenAP, self).__init__()
self.min_update_dt = min_update_dt # second, minimum update dt
self.current_sim_time = 0 # last update simulation time
self.ac_warning = False # aircraft mdl to default warning
self.eng_warning = False # aircraft engine to default warning
self.coeff = coeff.Coefficient()
self.n_ac = 0
with RegisterElementParameters(self):
self.actypes = np.array([], dtype=str)
self.lifttype = np.array([]) # lift type, fixwing [1] or rotor [2]
self.engnum = np.array([], dtype=int) # number of engines
self.engthrust = np.array([]) # static engine thrust
self.engbpr = np.array([]) # engine bypass ratio
self.thrustratio = np.array([]) # thrust ratio at current alt spd
self.ff_coeff_a = np.array([]) # icao fuel flows coefficient a
self.ff_coeff_b = np.array([]) # icao fuel flows coefficient b
self.ff_coeff_c = np.array([]) # icao fuel flows coefficient c
self.engpower = np.array([]) # engine power, rotor ac
def __init__(self):
super(Traffic, self).__init__()
# Traffic is the toplevel trafficarrays object
TrafficArrays.SetRoot(self)
self.ntraf = 0
self.cond = Condition() # Conditional commands list
self.wind = WindSim()
self.turbulence = Turbulence()
self.translvl = 5000. * ft # [m] Default transition level
with RegisterElementParameters(self):
# Aircraft Info
self.id = [] # identifier (string)
self.type = [] # aircaft type (string)
# Positions
self.lat = np.array([]) # latitude [deg]
self.lon = np.array([]) # longitude [deg]
self.distflown = np.array([]) # distance travelled [m]
self.alt = np.array([]) # altitude [m]
self.hdg = np.array([]) # traffic heading [deg]
self.trk = np.array([]) # track angle [deg]
# Velocities
self.tas = np.array([]) # true airspeed [m/s]
self.gs = np.array([]) # ground speed [m/s]
self.gsnorth = np.array([]) # ground speed [m/s]
self.gseast = np.array([]) # ground speed [m/s]
self.cas = np.array([]) # calibrated airspeed [m/s]
self.M = np.array([]) # mach number
self.vs = np.array([]) # vertical speed [m/s]
# Atmosphere
self.p = np.array([]) # air pressure [N/m2]
self.rho = np.array([]) # air density [kg/m3]
self.Temp = np.array([]) # air temperature [K]
self.dtemp = np.array([]) # delta t for non-ISA conditions
# Wind speeds
self.windnorth = np.array(
[]) # wind speed north component a/c pos [m/s]
self.windeast = np.array(
[]) # wind speed east component a/c pos [m/s]
# Traffic autopilot settings
self.selspd = np.array([]) # selected spd(CAS or Mach) [m/s or -]
self.aptas = np.array([]) # just for initializing
self.selalt = np.array([]) # selected alt[m]
self.selvs = np.array([]) # selected vertical speed [m/s]
# Whether to perform LNAV and VNAV
self.swlnav = np.array([], dtype=np.bool)
self.swvnav = np.array([], dtype=np.bool)
self.swvnavspd = np.array([], dtype=np.bool)
# Flight Models
self.asas = ASAS()
self.ap = Autopilot()
self.pilot = Pilot()
self.adsb = ADSB()
self.trails = Trails()
self.actwp = ActiveWaypoint()
self.perf = Perf()
# Group Logic
self.groups = TrafficGroups()
# Traffic performance data
self.apvsdef = np.array(
[]) # [m/s]default vertical speed of autopilot
self.aphi = np.array([]) # [rad] bank angle setting of autopilot
self.ax = np.array(
[]) # [m/s2] absolute value of longitudinal accelleration
self.bank = np.array([]) # nominal bank angle, [radian]
self.swhdgsel = np.array(
[], dtype=np.bool) # determines whether aircraft is turning
# limit settings
self.limspd = np.array([]) # limit speed
self.limspd_flag = np.array(
[], dtype=np.bool
) # flag for limit spd - we have to test for max and min
self.limalt = np.array([]) # limit altitude
self.limalt_flag = np.array(
[]) # A need to limit altitude has been detected
self.limvs = np.array(
[]) # limit vertical speed due to thrust limitation
self.limvs_flag = np.array([]) # A need to limit V/S detected
# Display information on label
self.label = [] # Text and bitmap of traffic label
# Miscallaneous
self.coslat = np.array([]) # Cosine of latitude for computations
self.eps = np.array([]) # Small nonzero numbers
# Default bank angles per flight phase
self.bphase = np.deg2rad(np.array([15, 35, 35, 35, 15, 45]))
self.reset()
def __init__(self):
super(Traffic, self).__init__()
# Traffic is the toplevel trafficarrays object
TrafficArrays.SetRoot(self)
self.ntraf = 0
self.cond = Condition() # Conditional commands list
self.wind = WindSim()
self.turbulence = Turbulence()
self.translvl = 5000.*ft # [m] Default transition level
# Define the periodic loggers
# ToDo: explain what these line sdo in comments (type of logs?)
datalog.definePeriodicLogger('SNAPLOG', 'SNAPLOG logfile.', settings.snapdt)
datalog.definePeriodicLogger('INSTLOG', 'INSTLOG logfile.', settings.instdt)
datalog.definePeriodicLogger('SKYLOG', 'SKYLOG logfile.', settings.skydt)
with RegisterElementParameters(self):
# Register the following parameters for logging
with datalog.registerLogParameters('SNAPLOG', self):
# Aircraft Info
self.id = [] # identifier (string)
self.type = [] # aircaft type (string)
# Positions
self.lat = np.array([]) # latitude [deg]
self.lon = np.array([]) # longitude [deg]
self.alt = np.array([]) # altitude [m]
self.hdg = np.array([]) # traffic heading [deg]
self.trk = np.array([]) # track angle [deg]
# Velocities
self.tas = np.array([]) # true airspeed [m/s]
self.gs = np.array([]) # ground speed [m/s]
self.gsnorth = np.array([]) # ground speed [m/s]
self.gseast = np.array([]) # ground speed [m/s]
self.cas = np.array([]) # calibrated airspeed [m/s]
self.M = np.array([]) # mach number
self.vs = np.array([]) # vertical speed [m/s]
#Creation time
self.cretime = np.array([]) #Creation time [s]
#time in conflict
self.timeinconf = np.array([]) #Time in conflict [s] (this value is updated in area)
# Atmosphere
self.p = np.array([]) # air pressure [N/m2]
self.rho = np.array([]) # air density [kg/m3]
self.Temp = np.array([]) # air temperature [K]
self.dtemp = np.array([]) # delta t for non-ISA conditions
# Traffic autopilot settings
self.selspd = np.array([]) # selected spd(CAS or Mach) [m/s or -]
self.aptas = np.array([]) # just for initializing
self.selalt = np.array([]) # selected alt[m]
self.selvs = np.array([]) # selected vertical speed [m/s]
# Whether to perform LNAV and VNAV
self.swlnav = np.array([], dtype=np.bool)
self.swvnav = np.array([], dtype=np.bool)
# Flight Models
self.asas = ASAS()
self.ap = Autopilot()
self.pilot = Pilot()
self.adsb = ADSB()
self.trails = Trails()
self.actwp = ActiveWaypoint()
self.perf = Perf()
# Traffic performance data
self.apvsdef = np.array([]) # [m/s]default vertical speed of autopilot
self.aphi = np.array([]) # [rad] bank angle setting of autopilot
self.ax = np.array([]) # [m/s2] absolute value of longitudinal accelleration
self.bank = np.array([]) # nominal bank angle, [radian]
self.swhdgsel = np.array([], dtype=np.bool) # determines whether aircraft is turning
# Crossover altitude
self.abco = np.array([])
self.belco = np.array([])
# limit settings
self.limspd = np.array([]) # limit speed
self.limspd_flag = np.array([], dtype=np.bool) # flag for limit spd - we have to test for max and min
self.limalt = np.array([]) # limit altitude
self.limalt_flag = np.array([]) # A need to limit altitude has been detected
self.limvs = np.array([]) # limit vertical speed due to thrust limitation
self.limvs_flag = np.array([]) # A need to limit V/S detected
# Display information on label
self.label = [] # Text and bitmap of traffic label
# Miscallaneous
self.coslat = np.array([]) # Cosine of latitude for computations
self.eps = np.array([]) # Small nonzero numbers
# Default bank angles per flight phase
self.bphase = np.deg2rad(np.array([15, 35, 35, 35, 15, 45]))
self.reset()
def __init__(self):
super(PerfBS, self).__init__()
self.warned = False # Flag: Did we warn for default perf parameters yet?
self.warned2 = False # Flag: Use of piston engine aircraft?
# prepare for coefficient readin
coeffBS.coeff()
# Flight performance scheduling
self.dt = 0.1 # [s] update interval of performance limits
self.t0 = -self.dt # [s] last time checked (in terms of simt)
with RegisterElementParameters(self):
# index of aircraft types in library
self.coeffidxlist = np.array([])
# geometry and weight
self.mass = np.array([]) # Mass [kg]
self.Sref = np.array([]) # Wing surface area [m^2]
# reference velocities
self.refma = np.array([]) # reference Mach
self.refcas = np.array([]) # reference CAS
self.gr_acc = np.array([]) # ground acceleration
self.gr_dec = np.array([]) # ground deceleration
# limits
self.vm_to = np.array([]) # min takeoff spd (w/o mass, density)
self.vm_ld = np.array([]) # min landing spd (w/o mass, density)
self.vmto = np.array([]) # min TO spd
self.vmic = np.array([]) # min. IC speed
self.vmcr = np.array([]) # min cruise spd
self.vmap = np.array([]) # min approach speed
self.vmld = np.array([]) # min landing spd
self.vmin = np.array([]) # min speed over all phases
self.vmo = np.array([]) # max CAS
self.mmo = np.array([]) # max Mach
self.hmaxact = np.array([]) # max. altitude
self.maxthr = np.array([]) # maximum thrust
# aerodynamics
self.CD0 = np.array([]) # parasite drag coefficient
self.k = np.array([]) # induced drag factor
self.clmaxcr = np.array([]) # max. cruise lift coefficient
self.qS = np.array([]) # Dynamic air pressure [Pa]
self.atrans = np.array([]) # Transition altitude [m]
# engines
self.n_eng = np.array([]) # Number of engines
self.etype = np.array([]) # jet /turboprop
# jet engines:
self.rThr = np.array([]) # rated thrust (all engines)
self.SFC = np.array([]) # specific fuel consumption in cruise
self.ff = np.array([]) # fuel flow
self.ffto = np.array([]) # fuel flow takeoff
self.ffcl = np.array([]) # fuel flow climb
self.ffcr = np.array([]) # fuel flow cruise
self.ffid = np.array([]) # fuel flow idle
self.ffap = np.array([]) # fuel flow approach
# turboprop engines
self.P = np.array([]) # avaliable power at takeoff conditions
self.PSFC_TO = np.array([]) # specific fuel consumption takeoff
self.PSFC_CR = np.array([]) # specific fuel consumption cruise
self.Thr = np.array([]) # Thrust
self.Thr_pilot = np.array([]) # thrust required for pilot settings
self.D = np.array([]) # Drag
self.ESF = np.array(
[]) # Energy share factor according to EUROCONTROL
# flight phase
self.phase = np.array([]) # flight phase
self.bank = np.array([]) # bank angle
self.post_flight = np.array([]) # check for ground mode:
#taxi prior of after flight
self.pf_flag = np.array([])
self.engines = [] # avaliable engine type per aircraft type
self.eta = 0.8 # propeller efficiency according to Raymer
self.Thr_s = np.array(
[1., 0.85, 0.07,
0.3]) # Thrust settings per flight phase according to ICAO
return
def __init__(self):
super(PerfBADA, self).__init__()
self.warned = False # Flag: Did we warn for default perf parameters yet?
self.warned2 = False # Flag: Use of piston engine aircraft?
# Flight performance scheduling
self.warned2 = False # Flag: Did we warn for default engine parameters yet?
# Register the per-aircraft parameter arrays
with RegisterElementParameters(self):
# engine
self.jet = np.array([])
self.turbo = np.array([])
self.piston = np.array([])
# masses and dimensions
self.mass = np.array([]) # effective mass [kg]
# self.mref = np.array([]) # ref. mass [kg]: 70% between min and max. mass
self.mmin = np.array([]) # OEW (or assumption) [kg]
self.mmax = np.array([]) # MTOW (or assumption) [kg]
# self.mpyld = np.array([]) # MZFW-OEW (or assumption) [kg]
self.gw = np.array([]) # weight gradient on max. alt [m/kg]
self.Sref = np.array([]) # wing reference surface area [m^2]
# flight enveloppe
self.vmto = np.array([]) # min TO spd [m/s]
self.vmic = np.array([]) # min climb spd [m/s]
self.vmcr = np.array([]) # min cruise spd [m/s]
self.vmap = np.array([]) # min approach spd [m/s]
self.vmld = np.array([]) # min landing spd [m/s]
self.vmin = np.array([]) # min speed over all phases [m/s]
self.vmo = np.array([]) # max operating speed [m/s]
self.mmo = np.array([]) # max operating mach number [-]
self.hmax = np.array(
[]) # max. alt above standard MSL (ISA) at MTOW [m]
self.hmaxact = np.array(
[]) # max. alt depending on temperature gradient [m]
self.hmo = np.array([]) # max. operating alt abov standard MSL [m]
self.gt = np.array([]) # temp. gradient on max. alt [ft/k]
self.maxthr = np.array([]) # maximum thrust [N]
# Buffet Coefficients
self.clbo = np.array([]) # buffet onset lift coefficient [-]
self.k = np.array([]) # buffet coefficient [-]
self.cm16 = np.array([]) # CM16
# reference CAS speeds
self.cascl = np.array([]) # climb [m/s]
self.cascr = np.array([]) # cruise [m/s]
self.casdes = np.array([]) # descent [m/s]
#reference mach numbers [-]
self.macl = np.array([]) # climb
self.macr = np.array([]) # cruise
self.mades = np.array([]) # descent
# parasitic drag coefficients per phase [-]
self.cd0to = np.array([]) # phase takeoff
self.cd0ic = np.array([]) # phase initial climb
self.cd0cr = np.array([]) # phase cruise
self.cd0ap = np.array([]) # phase approach
self.cd0ld = np.array([]) # phase land
self.gear = np.array([]) # drag due to gear down
# induced drag coefficients per phase [-]
self.cd2to = np.array([]) # phase takeoff
self.cd2ic = np.array([]) # phase initial climb
self.cd2cr = np.array([]) # phase cruise
self.cd2ap = np.array([]) # phase approach
self.cd2ld = np.array([]) # phase land
# max climb thrust coefficients
self.ctcth1 = np.array([]) # jet/piston [N], turboprop [ktN]
self.ctcth2 = np.array([]) # [ft]
self.ctcth3 = np.array(
[]) # jet [1/ft^2], turboprop [N], piston [ktN]
# reduced climb power coefficient
self.cred = np.array([]) # [-]
# 1st and 2nd thrust temp coefficient
self.ctct1 = np.array([]) # [k]
self.ctct2 = np.array([]) # [1/k]
self.dtemp = np.array([]) # [k]
# Descent Fuel Flow Coefficients
# Note: Ctdes,app and Ctdes,lnd assume a 3 degree descent gradient during app and lnd
self.ctdesl = np.array(
[]) # low alt descent thrust coefficient [-]
self.ctdesh = np.array(
[]) # high alt descent thrust coefficient [-]
self.ctdesa = np.array([]) # approach thrust coefficient [-]
self.ctdesld = np.array([]) # landing thrust coefficient [-]
# transition altitude for calculation of descent thrust
self.hpdes = np.array([]) # [m]
# Energy Share Factor
self.ESF = np.array([]) # [-]
# reference speed during descent
self.vdes = np.array([]) # [m/s]
self.mdes = np.array([]) # [-]
# flight phase
self.phase = np.array([])
self.post_flight = np.array([]) # taxi prior of post flight?
self.pf_flag = np.array([])
# Thrust specific fuel consumption coefficients
self.cf1 = np.array(
[]
) # jet [kg/(min*kN)], turboprop [kg/(min*kN*knot)], piston [kg/min]
self.cf2 = np.array([]) # [knots]
self.cf3 = np.array([]) # [kg/min]
self.cf4 = np.array([]) # [ft]
self.cf_cruise = np.array([]) # [-]
# performance
self.Thr = np.array([]) # thrust
self.D = np.array([]) # drag
self.fuelflow = np.array([]) # fuel flow
# ground
self.tol = np.array([]) # take-off length[m]
self.ldl = np.array([]) # landing length[m]
self.ws = np.array([]) # wingspan [m]
self.len = np.array([]) # aircraft length[m]
self.gr_acc = np.array([]) # ground acceleration [m/s^2]