update EHS BDS identification, add isBDS50or60() function
This commit is contained in:
Junzi Sun
parent
5697e5b88e
commit
4911e69171
@ -6,3 +6,5 @@ from .decoder import ehs
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from .decoder import els
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from .decoder import util
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from .decoder import modes_common
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from .extra import aero
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from .extra import beastclient
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@ -18,8 +18,9 @@ A python package for decoding ModeS (DF20, DF21) messages.
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"""
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from __future__ import absolute_import, print_function, division
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from . import util, modes_common
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from scipy.stats import multivariate_normal
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import numpy as np
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from pyModeS.decoder import util, modes_common
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from pyModeS.extra import aero
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def icao(msg):
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return modes_common.icao(msg)
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@ -972,6 +973,61 @@ def vr60ins(msg):
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return roc
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def isBDS50or60(msg, spd_ref, trk_ref, alt_ref):
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"""Use reference ground speed and trk to determine BDS50 and DBS60
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Args:
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msg (String): 28 bytes hexadecimal message string
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spd_ref (float): reference speed (ADS-B ground speed), kts
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trk_ref (float): reference track (ADS-B track angle), deg
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alt_ref (float): reference altitude (ADS-B altitude), ft
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Returns:
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String or None: BDS version, or possible versions, or None if nothing matches.
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"""
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def vxy(v, angle):
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vx = v * np.sin(np.deg2rad(angle))
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vy = v * np.cos(np.deg2rad(angle))
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return vx, vy
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if not (isBDS50(msg) and isBDS60(msg)):
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return None
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h50 = trk50(msg)
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v50 = gs50(msg)
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h50 = np.nan if h50 is None else h50
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v50 = np.nan if v50 is None else v50
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h60 = hdg60(msg)
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m60 = mach60(msg)
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i60 = ias60(msg)
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h60 = np.nan if h60 is None else h60
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m60 = np.nan if m60 is None else m60
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i60 = np.nan if i60 is None else i60
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XY5 = vxy(v50*aero.kts, h50)
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XY6m = vxy(aero.mach2tas(m60, alt_ref*aero.ft), h60)
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XY6i = vxy(aero.cas2tas(i60*aero.kts, alt_ref*aero.ft), h60)
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allbds = ['BDS50', 'BDS60', 'BDS60']
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X = np.array([XY5, XY6m, XY6i])
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Mu = np.array(vxy(spd_ref*aero.kts, trk_ref*aero.kts))
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# compute Mahalanobis distance matrix
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# Cov = [[20**2, 0], [0, 20**2]]
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# mmatrix = np.sqrt(np.dot(np.dot(X-Mu, np.linalg.inv(Cov)), (X-Mu).T))
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# dist = np.diag(mmatrix)
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# since the covariance matrix is identity matrix,
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# M-dist is same as eculidian distance
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dist = np.linalg.norm(X-Mu, axis=1)
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BDS = allbds[np.nanargmin(dist)]
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return BDS
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def BDS(msg):
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"""Estimate the most likely BDS code of an message
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@ -994,78 +1050,16 @@ def BDS(msg):
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is53 = isBDS53(msg)
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is60 = isBDS60(msg)
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BDS = ["BDS17", "BDS20", "BDS40", "BDS44", "BDS44REV", "BDS50", "BDS53", "BDS60"]
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allbds = np.array([
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"BDS17", "BDS20", "BDS40", "BDS44", "BDS44REV",
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"BDS50", "BDS53", "BDS60"
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])
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isBDS = [is17, is20, is40, is44, is44rev, is50, is53, is60]
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if sum(isBDS) == 0:
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bds = ','.join(sorted(allbds[isBDS]))
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if len(bds) == 0:
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return None
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elif sum(isBDS) == 1:
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return BDS[isBDS.index(True)]
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else:
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bds_ = [bds for (bds, i) in zip(BDS, isBDS) if i]
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return ','.join(bds_)
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def Vxy(V, angle):
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Vx = V*np.sin(np.deg2rad(angle))
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Vy = V*np.cos(np.deg2rad(angle))
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return Vx, Vy
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def BDSv2(msg, SPDref=np.nan, TRKref=np.nan, ALTref=np.nan):
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"""Use probabilistic method to determine the most likely BDS code of an message
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Args:
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msg (String): 28 bytes hexadecimal message string
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SPDref (float): reference speed (for example ADS-B GS)
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TRKref (float): reference track (for example ADS-B TRK)
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ALTref (float): reference altitude (for example ADS-B altitude)
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Returns:
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String or None: BDS version, or possible versions, or None if nothing matches.
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"""
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BDS = pms.ehs.BDS(msg)
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if type(BDS) != list:
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return BDS
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else:
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if 'BDS53' in BDS:
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BDS.remove('BDS53')
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if 'BDS40' in BDS:
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fms = pms.ehs.alt40fms(msg)
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mcp = pms.ehs.alt40mcp(msg)
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baro = pms.ehs.p40baro(msg)
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if fms != None:
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if (((fms % 100) <= 8) or ((fms % 100) >= 92)) and fms < 50500:
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return 'BDS40'
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if mcp != None:
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if (((mcp % 100) <= 8) or ((mcp % 100) >= 92)) and mcp < 50500:
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return 'BDS40'
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if baro != None:
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if (983 <= baro <= 1043): #1013 -+ 30
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return 'BDS40'
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if set(BDS).issubset(['BDS50', 'BDS60']):
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if ~(np.isnan(SPDref) or np.isnan(TRKref) or np.isnan(ALTref)):
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meanV = Vxy(SPDref, TRKref)
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sigmaV = 20
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covV = [[sigmaV**2, 0], [0, sigmaV**2]]
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try: # Because register field is not available.
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pBDS50 = multivariate_normal(meanV, covV).pdf(Vxy(pms.ehs.gs50(msg), pms.ehs.trk50(msg)))
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pBDS60_1 = multivariate_normal(meanV, covV).pdf(Vxy(aero.mach2tas(pms.ehs.mach60(msg), ALTref*aero.ft)/aero.kts, pms.ehs.hdg60(msg)))
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pBDS60_2 = multivariate_normal(meanV, covV).pdf(Vxy(aero.cas2tas(pms.ehs.ias60(msg)*aero.kts, ALTref*aero.ft)/aero.kts, pms.ehs.hdg60(msg)))
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pBDS60 = max(pBDS60_1, pBDS60_2)
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except:
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return BDS
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if pBDS50 + pBDS60 > 0: #Avoid None values
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if pBDS50 > pBDS60:
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return 'BDS50'
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elif pBDS50 < pBDS60:
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return 'BDS60'
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return BDS
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return bds
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1
pyModeS/extra/__init__.py
Normal file
1
pyModeS/extra/__init__.py
Normal file
@ -0,0 +1 @@
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from __future__ import absolute_import, print_function, division
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@ -1,178 +1,178 @@
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"""
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Functions for aeronautics in this module
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- physical quantities always in SI units
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- lat,lon,course and heading in degrees
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International Standard Atmosphere
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p,rho,T = atmos(H) # atmos as function of geopotential altitude H [m]
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a = vsound(H) # speed of sound [m/s] as function of H[m]
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p = pressure(H) # calls atmos but retruns only pressure [Pa]
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T = temperature(H) # calculates temperature [K]
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rho = density(H) # calls atmos but retruns only pressure [Pa]
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Speed conversion at altitude H[m] in ISA:
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Mach = tas2mach(Vtas,H) # true airspeed (Vtas) to mach number conversion
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Vtas = mach2tas(Mach,H) # true airspeed (Vtas) to mach number conversion
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Vtas = eas2tas(Veas,H) # equivalent airspeed to true airspeed, H in [m]
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Veas = tas2eas(Vtas,H) # true airspeed to equivent airspeed, H in [m]
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Vtas = cas2tas(Vcas,H) # Vcas to Vtas conversion both m/s, H in [m]
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Vcas = tas2cas(Vtas,H) # Vtas to Vcas conversion both m/s, H in [m]
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Vcas = mach2cas(Mach,H) # Mach to Vcas conversion Vcas in m/s, H in [m]
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Mach = cas2mach(Vcas,H) # Vcas to mach copnversion Vcas in m/s, H in [m]
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"""
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import numpy as np
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"""Aero and geo Constants """
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kts = 0.514444 # knot -> m/s
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ft = 0.3048 # ft -> m
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fpm = 0.00508 # ft/min -> m/s
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inch = 0.0254 # inch -> m
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sqft = 0.09290304 # 1 square foot
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nm = 1852. # nautical mile -> m
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lbs = 0.453592 # pound -> kg
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g0 = 9.80665 # m/s2, Sea level gravity constant
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R = 287.05287 # m2/(s2 x K), gas constant, sea level ISA
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p0 = 101325. # Pa, air pressure, sea level ISA
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rho0 = 1.225 # kg/m3, air density, sea level ISA
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T0 = 288.15 # K, temperature, sea level ISA
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gamma = 1.40 # cp/cv for air
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gamma1 = 0.2 # (gamma-1)/2 for air
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gamma2 = 3.5 # gamma/(gamma-1) for air
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beta = -0.0065 # [K/m] ISA temp gradient below tropopause
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r_earth = 6371000. # m, average earth radius
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a0 = 340.293988 # m/s, sea level speed of sound ISA, sqrt(gamma*R*T0)
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def atmos(H):
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# H in metres
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T = np.maximum(288.15 - 0.0065 * H, 216.65)
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rhotrop = 1.225 * (T / 288.15)**4.256848030018761
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dhstrat = np.maximum(0., H - 11000.0)
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rho = rhotrop * np.exp(-dhstrat / 6341.552161)
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p = rho * R * T
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return p, rho, T
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def temperature(H):
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p, r, T = atmos(H)
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return T
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def pressure(H):
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p, r, T = atmos(H)
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return p
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def density(H):
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p, r, T = atmos(H)
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return r
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def vsound(H):
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"""Speed of sound"""
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T = temperature(H)
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a = np.sqrt(gamma * R * T)
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return a
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def distance(lat1, lon1, lat2, lon2, H=0):
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"""
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Compute spherical distance from spherical coordinates.
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For two locations in spherical coordinates
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(1, theta, phi) and (1, theta', phi')
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cosine( arc length ) =
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sin phi sin phi' cos(theta-theta') + cos phi cos phi'
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distance = rho * arc length
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"""
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# phi = 90 - latitude
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phi1 = np.radians(90.0 - lat1)
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phi2 = np.radians(90.0 - lat2)
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# theta = longitude
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theta1 = np.radians(lon1)
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theta2 = np.radians(lon2)
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cos = np.sin(phi1) * np.sin(phi2) * np.cos(theta1 - theta2) \
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+ np.cos(phi1) * np.cos(phi2)
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arc = np.arccos(cos)
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dist = arc * (r_earth + H) # meters, radius of earth
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return dist
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def bearing(lat1, lon1, lat2, lon2):
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lat1 = np.radians(lat1)
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lon1 = np.radians(lon1)
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lat2 = np.radians(lat2)
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lon2 = np.radians(lon2)
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x = np.sin(lon2-lon1) * np.cos(lat2)
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y = np.cos(lat1) * np.sin(lat2) \
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- np.sin(lat1) * np.cos(lat2) * np.cos(lon2-lon1)
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initial_bearing = np.arctan2(x, y)
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initial_bearing = np.degrees(initial_bearing)
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bearing = (initial_bearing + 360) % 360
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return bearing
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# -----------------------------------------------------
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# Speed conversions, altitude H all in meters
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# -----------------------------------------------------
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def tas2mach(Vtas, H):
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"""True Airspeed to Mach number"""
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a = vsound(H)
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Mach = Vtas/a
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return Mach
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def mach2tas(Mach, H):
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"""Mach number to True Airspeed"""
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a = vsound(H)
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Vtas = Mach*a
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return Vtas
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def eas2tas(Veas, H):
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"""Equivalent Airspeed to True Airspeed"""
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rho = density(H)
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Vtas = Veas * np.sqrt(rho0/rho)
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return Vtas
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def tas2eas(Vtas, H):
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"""True Airspeed to Equivalent Airspeed"""
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rho = density(H)
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Veas = Vtas * np.sqrt(rho/rho0)
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return Veas
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def cas2tas(Vcas, H):
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"""Calibrated Airspeed to True Airspeed"""
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p, rho, T = atmos(H)
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qdyn = p0*((1.+rho0*Vcas*Vcas/(7.*p0))**3.5-1.)
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Vtas = np.sqrt(7.*p/rho*((1.+qdyn/p)**(2./7.)-1.))
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return Vtas
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def tas2cas(Vtas, H):
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"""True Airspeed to Calibrated Airspeed"""
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p, rho, T = atmos(H)
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qdyn = p*((1.+rho*Vtas*Vtas/(7.*p))**3.5-1.)
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Vcas = np.sqrt(7.*p0/rho0*((qdyn/p0+1.)**(2./7.)-1.))
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return Vcas
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def mach2cas(Mach, H):
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"""Mach number to Calibrated Airspeed"""
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Vtas = mach2tas(Mach, H)
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Vcas = tas2cas(Vtas, H)
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return Vcas
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def cas2mach(Vcas, H):
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"""Calibrated Airspeed to Mach number"""
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Vtas = cas2tas(Vcas, H)
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Mach = tas2mach(Vtas, H)
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return Mach
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"""
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Functions for aeronautics in this module
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- physical quantities always in SI units
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- lat,lon,course and heading in degrees
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International Standard Atmosphere
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p,rho,T = atmos(H) # atmos as function of geopotential altitude H [m]
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a = vsound(H) # speed of sound [m/s] as function of H[m]
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p = pressure(H) # calls atmos but retruns only pressure [Pa]
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T = temperature(H) # calculates temperature [K]
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rho = density(H) # calls atmos but retruns only pressure [Pa]
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Speed conversion at altitude H[m] in ISA:
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Mach = tas2mach(Vtas,H) # true airspeed (Vtas) to mach number conversion
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Vtas = mach2tas(Mach,H) # true airspeed (Vtas) to mach number conversion
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Vtas = eas2tas(Veas,H) # equivalent airspeed to true airspeed, H in [m]
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Veas = tas2eas(Vtas,H) # true airspeed to equivent airspeed, H in [m]
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Vtas = cas2tas(Vcas,H) # Vcas to Vtas conversion both m/s, H in [m]
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Vcas = tas2cas(Vtas,H) # Vtas to Vcas conversion both m/s, H in [m]
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Vcas = mach2cas(Mach,H) # Mach to Vcas conversion Vcas in m/s, H in [m]
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Mach = cas2mach(Vcas,H) # Vcas to mach copnversion Vcas in m/s, H in [m]
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"""
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import numpy as np
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"""Aero and geo Constants """
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kts = 0.514444 # knot -> m/s
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ft = 0.3048 # ft -> m
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fpm = 0.00508 # ft/min -> m/s
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inch = 0.0254 # inch -> m
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sqft = 0.09290304 # 1 square foot
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nm = 1852. # nautical mile -> m
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lbs = 0.453592 # pound -> kg
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g0 = 9.80665 # m/s2, Sea level gravity constant
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R = 287.05287 # m2/(s2 x K), gas constant, sea level ISA
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p0 = 101325. # Pa, air pressure, sea level ISA
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rho0 = 1.225 # kg/m3, air density, sea level ISA
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T0 = 288.15 # K, temperature, sea level ISA
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gamma = 1.40 # cp/cv for air
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gamma1 = 0.2 # (gamma-1)/2 for air
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gamma2 = 3.5 # gamma/(gamma-1) for air
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beta = -0.0065 # [K/m] ISA temp gradient below tropopause
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r_earth = 6371000. # m, average earth radius
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a0 = 340.293988 # m/s, sea level speed of sound ISA, sqrt(gamma*R*T0)
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def atmos(H):
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# H in metres
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T = np.maximum(288.15 - 0.0065 * H, 216.65)
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rhotrop = 1.225 * (T / 288.15)**4.256848030018761
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dhstrat = np.maximum(0., H - 11000.0)
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rho = rhotrop * np.exp(-dhstrat / 6341.552161)
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p = rho * R * T
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return p, rho, T
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def temperature(H):
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p, r, T = atmos(H)
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return T
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def pressure(H):
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p, r, T = atmos(H)
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return p
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def density(H):
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p, r, T = atmos(H)
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return r
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def vsound(H):
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"""Speed of sound"""
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T = temperature(H)
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a = np.sqrt(gamma * R * T)
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return a
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def distance(lat1, lon1, lat2, lon2, H=0):
|
||||
"""
|
||||
Compute spherical distance from spherical coordinates.
|
||||
|
||||
For two locations in spherical coordinates
|
||||
(1, theta, phi) and (1, theta', phi')
|
||||
cosine( arc length ) =
|
||||
sin phi sin phi' cos(theta-theta') + cos phi cos phi'
|
||||
distance = rho * arc length
|
||||
"""
|
||||
|
||||
# phi = 90 - latitude
|
||||
phi1 = np.radians(90.0 - lat1)
|
||||
phi2 = np.radians(90.0 - lat2)
|
||||
|
||||
# theta = longitude
|
||||
theta1 = np.radians(lon1)
|
||||
theta2 = np.radians(lon2)
|
||||
|
||||
cos = np.sin(phi1) * np.sin(phi2) * np.cos(theta1 - theta2) + np.cos(phi1) * np.cos(phi2)
|
||||
cos = np.where(cos>1, 1, cos)
|
||||
|
||||
arc = np.arccos(cos)
|
||||
dist = arc * (r_earth + H) # meters, radius of earth
|
||||
return dist
|
||||
|
||||
|
||||
def bearing(lat1, lon1, lat2, lon2):
|
||||
lat1 = np.radians(lat1)
|
||||
lon1 = np.radians(lon1)
|
||||
lat2 = np.radians(lat2)
|
||||
lon2 = np.radians(lon2)
|
||||
x = np.sin(lon2-lon1) * np.cos(lat2)
|
||||
y = np.cos(lat1) * np.sin(lat2) \
|
||||
- np.sin(lat1) * np.cos(lat2) * np.cos(lon2-lon1)
|
||||
initial_bearing = np.arctan2(x, y)
|
||||
initial_bearing = np.degrees(initial_bearing)
|
||||
bearing = (initial_bearing + 360) % 360
|
||||
return bearing
|
||||
|
||||
|
||||
# -----------------------------------------------------
|
||||
# Speed conversions, altitude H all in meters
|
||||
# -----------------------------------------------------
|
||||
def tas2mach(Vtas, H):
|
||||
"""True Airspeed to Mach number"""
|
||||
a = vsound(H)
|
||||
Mach = Vtas/a
|
||||
return Mach
|
||||
|
||||
|
||||
def mach2tas(Mach, H):
|
||||
"""Mach number to True Airspeed"""
|
||||
a = vsound(H)
|
||||
Vtas = Mach*a
|
||||
return Vtas
|
||||
|
||||
|
||||
def eas2tas(Veas, H):
|
||||
"""Equivalent Airspeed to True Airspeed"""
|
||||
rho = density(H)
|
||||
Vtas = Veas * np.sqrt(rho0/rho)
|
||||
return Vtas
|
||||
|
||||
|
||||
def tas2eas(Vtas, H):
|
||||
"""True Airspeed to Equivalent Airspeed"""
|
||||
rho = density(H)
|
||||
Veas = Vtas * np.sqrt(rho/rho0)
|
||||
return Veas
|
||||
|
||||
|
||||
def cas2tas(Vcas, H):
|
||||
"""Calibrated Airspeed to True Airspeed"""
|
||||
p, rho, T = atmos(H)
|
||||
qdyn = p0*((1.+rho0*Vcas*Vcas/(7.*p0))**3.5-1.)
|
||||
Vtas = np.sqrt(7.*p/rho*((1.+qdyn/p)**(2./7.)-1.))
|
||||
return Vtas
|
||||
|
||||
|
||||
def tas2cas(Vtas, H):
|
||||
"""True Airspeed to Calibrated Airspeed"""
|
||||
p, rho, T = atmos(H)
|
||||
qdyn = p*((1.+rho*Vtas*Vtas/(7.*p))**3.5-1.)
|
||||
Vcas = np.sqrt(7.*p0/rho0*((qdyn/p0+1.)**(2./7.)-1.))
|
||||
return Vcas
|
||||
|
||||
|
||||
def mach2cas(Mach, H):
|
||||
"""Mach number to Calibrated Airspeed"""
|
||||
Vtas = mach2tas(Mach, H)
|
||||
Vcas = tas2cas(Vtas, H)
|
||||
return Vcas
|
||||
|
||||
|
||||
def cas2mach(Vcas, H):
|
||||
"""Calibrated Airspeed to Mach number"""
|
||||
Vtas = cas2tas(Vcas, H)
|
||||
Mach = tas2mach(Vtas, H)
|
||||
return Mach
|
||||
@ -5,11 +5,11 @@ import argparse
|
||||
import curses
|
||||
import numpy as np
|
||||
import time
|
||||
import pyModeS as pms
|
||||
from threading import Lock
|
||||
from client import BaseClient
|
||||
from stream import Stream
|
||||
from screen import Screen
|
||||
from pyModeS.decoder import util
|
||||
from pyModeS.extra.beastclient import BaseClient
|
||||
from pyModeS.streamer.stream import Stream
|
||||
from pyModeS.streamer.screen import Screen
|
||||
|
||||
LOCK = Lock()
|
||||
ADSB_MSG = []
|
||||
@ -43,7 +43,7 @@ class ModesClient(BaseClient):
|
||||
if len(msg) < 28: # only process long messages
|
||||
continue
|
||||
|
||||
df = pms.df(msg)
|
||||
df = util.df(msg)
|
||||
|
||||
if df == 17 or df == 18:
|
||||
local_buffer_adsb_msg.append(msg)
|
||||
|
||||
@ -1,8 +1,7 @@
|
||||
from __future__ import print_function, division
|
||||
from __future__ import absolute_import, print_function, division
|
||||
import numpy as np
|
||||
import time
|
||||
import pyModeS as pms
|
||||
|
||||
from pyModeS.decoder import adsb, ehs
|
||||
|
||||
class Stream():
|
||||
def __init__(self, lat0, lon0):
|
||||
@ -32,8 +31,8 @@ class Stream():
|
||||
|
||||
# process adsb message
|
||||
for t, msg in zip(adsb_ts, adsb_msgs):
|
||||
icao = pms.adsb.icao(msg)
|
||||
tc = pms.adsb.typecode(msg)
|
||||
icao = adsb.icao(msg)
|
||||
tc = adsb.typecode(msg)
|
||||
|
||||
if icao not in self.acs:
|
||||
self.acs[icao] = {
|
||||
@ -52,10 +51,10 @@ class Stream():
|
||||
self.acs[icao]['t'] = t
|
||||
|
||||
if 1 <= tc <= 4:
|
||||
self.acs[icao]['callsign'] = pms.adsb.callsign(msg)
|
||||
self.acs[icao]['callsign'] = adsb.callsign(msg)
|
||||
|
||||
if (5 <= tc <= 8) or (tc == 19):
|
||||
vdata = pms.adsb.velocity(msg)
|
||||
vdata = adsb.velocity(msg)
|
||||
if vdata is None:
|
||||
continue
|
||||
|
||||
@ -69,7 +68,7 @@ class Stream():
|
||||
self.acs[icao]['tv'] = t
|
||||
|
||||
if (5 <= tc <= 18):
|
||||
oe = pms.adsb.oe_flag(msg)
|
||||
oe = adsb.oe_flag(msg)
|
||||
self.acs[icao][oe] = msg
|
||||
self.acs[icao]['t'+str(oe)] = t
|
||||
|
||||
@ -77,12 +76,12 @@ class Stream():
|
||||
# use single message decoding
|
||||
rlat = self.acs[icao]['lat']
|
||||
rlon = self.acs[icao]['lon']
|
||||
latlon = pms.adsb.position_with_ref(msg, rlat, rlon)
|
||||
latlon = adsb.position_with_ref(msg, rlat, rlon)
|
||||
elif ('t0' in self.acs[icao]) and ('t1' in self.acs[icao]) and \
|
||||
(abs(self.acs[icao]['t0'] - self.acs[icao]['t1']) < 10):
|
||||
# use multi message decoding
|
||||
try:
|
||||
latlon = pms.adsb.position(
|
||||
latlon = adsb.position(
|
||||
self.acs[icao][0],
|
||||
self.acs[icao][1],
|
||||
self.acs[icao]['t0'],
|
||||
@ -99,29 +98,29 @@ class Stream():
|
||||
self.acs[icao]['tpos'] = t
|
||||
self.acs[icao]['lat'] = latlon[0]
|
||||
self.acs[icao]['lon'] = latlon[1]
|
||||
self.acs[icao]['alt'] = pms.adsb.altitude(msg)
|
||||
self.acs[icao]['alt'] = adsb.altitude(msg)
|
||||
local_updated_acs_buffer.append(icao)
|
||||
|
||||
# process ehs message
|
||||
for t, msg in zip(ehs_ts, ehs_msgs):
|
||||
icao = pms.ehs.icao(msg)
|
||||
icao = ehs.icao(msg)
|
||||
|
||||
if icao not in self.acs:
|
||||
continue
|
||||
|
||||
bds = pms.ehs.BDS(msg)
|
||||
bds = ehs.BDS(msg)
|
||||
|
||||
if bds == 'BDS50':
|
||||
tas = pms.ehs.tas50(msg)
|
||||
tas = ehs.tas50(msg)
|
||||
|
||||
if tas:
|
||||
self.acs[icao]['t50'] = t
|
||||
self.acs[icao]['tas'] = tas
|
||||
|
||||
elif bds == 'BDS60':
|
||||
ias = pms.ehs.ias60(msg)
|
||||
hdg = pms.ehs.hdg60(msg)
|
||||
mach = pms.ehs.mach60(msg)
|
||||
ias = ehs.ias60(msg)
|
||||
hdg = ehs.hdg60(msg)
|
||||
mach = ehs.mach60(msg)
|
||||
|
||||
if ias or hdg or mach:
|
||||
self.acs[icao]['t60'] = t
|
||||
|
||||
@ -14,10 +14,14 @@ def test_df20alt():
|
||||
def test_ehs_BDS():
|
||||
assert ehs.BDS("A0001838201584F23468207CDFA5") == 'BDS20'
|
||||
assert ehs.BDS("A0001839CA3800315800007448D9") == 'BDS40'
|
||||
# assert ehs.BDS("A000031DBAA9DD18622C441330E9") == 'BDS44'
|
||||
assert ehs.BDS("A000139381951536E024D4CCF6B5") == 'BDS50'
|
||||
assert ehs.BDS("A00004128F39F91A7E27C46ADC21") == 'BDS60'
|
||||
|
||||
def test_ehs_isBDS50or60():
|
||||
assert ehs.isBDS50or60("A0001838201584F23468207CDFA5", 0, 0, 0) == None
|
||||
assert ehs.isBDS50or60("A0000000FFDA9517000464000000", 182, 237, 1250) == 'BDS50'
|
||||
assert ehs.isBDS50or60("A0000000919A5927E23444000000", 413, 54, 18700) == 'BDS60'
|
||||
|
||||
def test_ehs_BDS20_callsign():
|
||||
assert ehs.callsign("A000083E202CC371C31DE0AA1CCF") == 'KLM1017_'
|
||||
assert ehs.callsign("A0001993202422F2E37CE038738E") == 'IBK2873_'
|
||||
|
||||
Loading…
Reference in New Issue
Block a user