def format_long_line(satrec, tsince, mu, r, v):
"""Long line, using the same format string that testcpp.cpp uses."""
short = format_short_line(tsince, r, v).strip('\n')
jd = satrec.jdsatepoch + satrec.jdsatepochF + tsince / 1440.0
year, mon, day, hr, minute, sec = invjday(jd)
(p, a, ecc, incl, node, argp, nu, m, arglat, truelon,
lonper) = rv2coe(r, v, mu)
return short + (' %14.6f %8.6f %10.5f %10.5f %10.5f %10.5f %10.5f'
' %5i%3i%3i %2i:%2i:%9.6f\n') % (
a,
ecc,
incl * rad,
node * rad,
argp * rad,
nu * rad,
m * rad,
year,
mon,
day,
hr,
minute,
sec,
)
def updateOrbitalParameters3(self, date=None):
if (date is None):
date = datetime.utcnow()
year = date.year
month = date.month
day = date.day
hour = date.hour
minute = date.minute
second = date.second + date.microsecond * 0.000001
pos, vel = self.sat.propagate(year, month, day, hour, minute, second)
p, a, e, i, raan, w, theta, m, argl, tlon, lonp = rv2coe(
pos, vel, self.mu * 0.000000001)
self.x = pos[0] * 1000
self.y = pos[1] * 1000
self.z = pos[2] * 1000
self.r = sqrt(self.x**2 + self.y**2 + self.z**2)
self.alt = self.r - self.getPlanetRadius()
self.r_iner[0, 0] = self.x
self.r_iner[1, 0] = self.y
self.r_iner[2, 0] = self.z
self.v_iner[0, 0] = vel[0] * 1000
self.v_iner[1, 0] = vel[1] * 1000
self.v_iner[2, 0] = vel[2] * 1000
self.p = p * 1000
self.a = a * 1000
self.e = e
self.incl = i
self.RAAN = raan
self.w = w
self.theta = theta
self.MA = m
self.n = sqrt(self.mu / (self.a**3))
self.h = sqrt(self.a * self.mu * (1 - self.e**2))
self.v_peri[0, 0] = -self.mu * sin(theta) / self.h
self.v_peri[1, 0] = self.mu * (e + cos(theta)) / self.h
def format_long_line(satrec, mu, r, v):
"""Long line, using the same format string that testcpp.cpp uses."""
short = format_short_line(satrec, r, v).strip("\n")
jd = satrec.jdsatepoch + satrec.t / 1440.0
year, mon, day, hr, minute, sec = invjday(jd)
(p, a, ecc, incl, node, argp, nu, m, arglat, truelon, lonper) = rv2coe(r, v, mu)
return short + (" %14.6f %8.6f %10.5f %10.5f %10.5f %10.5f %10.5f" " %5i%3i%3i %2i:%2i:%9.6f\n") % (
a,
ecc,
incl * rad,
node * rad,
argp * rad,
nu * rad,
m * rad,
year,
mon,
day,
hr,
minute,
sec,
)
def updateOrbitalParameters(self, date=None):
"""
Updates all the orbital parameters with the SGP4 propagation
model.
date : datetime
The orbital elements are updated for this date.
"""
if (date is None):
date = datetime.utcnow()
year = date.year
month = date.month
day = date.day
hour = date.hour
minute = date.minute
second = date.second + date.microsecond*0.000001
pos, vel = self.sat_model.propagate(year, month, day,
hour, minute, second)
p, a, e, i, raan, w, theta, m, argl, tlon, lonp = rv2coe(pos, vel,
self.mu*0.000000001)
self.x = pos[0]*1000
self.y = pos[1]*1000
self.z = pos[2]*1000
self.r = sqrt(self.x**2 + self.y**2 + self.z**2)
self.r_iner[0,0] = self.x
self.r_iner[1,0] = self.y
self.r_iner[2,0] = self.z
self.v_iner[0,0] = vel[0]*1000
self.v_iner[1,0] = vel[1]*1000
self.v_iner[2,0] = vel[2]*1000
self.p = p*1000
self.a = a*1000
self.e = e
self.incl = i
self.RAAN = raan
self.w = w
self.theta = theta
self.MA = m
self.n = sqrt(self.mu/(self.a**3))
self.h = sqrt(self.a*self.mu*(1 - self.e**2))
def sgp4_ephemeris(coords, prediction_dates_list):
r = coords[['x', 'y', 'z']].values
v = coords[['Vx', 'Vy', 'Vz']].values
ref_date = coords["epoch"]
p, sma, ecc, inc, raan, arg_p, nu, mean_an, arglat, truelon, lonper = rv2coe(
r, v, wgs72.mu)
inc = math.degrees(inc)
raan = math.degrees(raan)
arg_p = math.degrees(arg_p)
mean_an = math.degrees(mean_an)
tle = params2tle(ref_epoch=ref_date,
inc=inc,
raan=raan,
ecc=ecc,
arg_p=arg_p,
mean_an=mean_an,
sma=sma)
lines = tle2tle_lines(tle)
sat = twoline2rv(lines[0], lines[1], wgs72)
ephemeris = []
for date in prediction_dates_list:
date_ = epoch2datetime(date)
y_ = date_.year
m_ = date_.month
d_ = date_.day
h_ = date_.hour
min_ = date_.minute
sec_ = date_.second + date_.microsecond * 1e-6
r, v = sat.propagate(y_, m_, d_, h_, min_, sec_)
ephemeris.append([date] + list(r) + list(v))
return pd.DataFrame(
data=ephemeris,
columns=['epoch'] +
[c + "_sim_upd" for c in ['x', 'y', 'z', 'Vx', 'Vy', 'Vz']])
def test_epoch_methods():
line00 = line0 + " Apogee"
line1 = "1 28888U 05042A 14063.83505828 0.00032100 00000-0 29747-3 0 09"
# 3 iters
# line10 = '1 28888U 05042A 14063.82545230 0.00032100 00000-0 29747-3 0 09'
# 30 iters
line10 = '1 28888U 05042A 14063.82545230 0.00032096 00000-0 29747-3 0 03' # satfit.cpp
line100 = '1 28888T 05042A 14063.82545230 0.00032100 00000-0 29747-3 0 09' # Mine
line2 = "2 28888 96.8945 115.9842 0499287 308.6206 51.3792 14.85742003 02"
# 3 iters
#line20 = '2 28888 96.8945 115.9758 0499291 308.6530 0.0000 14.85741387 00'
# 30 iters
line20 = '2 28888 96.8945 115.9758 0499282 308.6530 0.0000 14.85741387 00' # satfit.cpp
line200 = '2 28888 96.8945 115.9758 0499293 308.6530 360.0000 14.85742003 07' # mine
# sat0 : Elements regressed to perigee by satfit.cpp TLE0 epoch
TLE0 = tle_util.TruSatellite(line0=line00, line1=line10, line2=line20)
sat0 = satfit.initsat(TLE0)
sat0 = satfit.delta_t(sat0,sat0.jdsatepoch)
# sat2 : Elements regressed to perigee by satfit.py TLE0 epoch
TLE2 = tle_util.TruSatellite(line0=line00, line1=line100, line2=line200)
sat2 = satfit.initsat(TLE2)
sat2 = satfit.delta_t(sat2,sat0.jdsatepoch)
# "satx: Original elements back-propagated to perigee (epoch of sat0)"
TLE = tle_util.TruSatellite(line0=line0, line1=line1, line2=line2)
sat1 = satfit.initsat(TLE)
sat1 = satfit.delta_t(sat1,sat0.jdsatepoch) # Changing tsince changes the mean elements
# satA : Elements created from sat0 mean elements after propagating to TLE0 epoch
satA = copy.deepcopy(sat0)
satA = satfit.delta_el(satA,xincl=satA.im,xnodeo=satA.Om,ec=satA.em,omegao=satA.om,xmo=satA.mm,xno=satA.no_kozai,bsr=sat1.bstar, jdsatepoch=sat0.jdsatepoch)
satA = satfit.delta_t(satA,sat0.jdsatepoch)
# satB : Elements created from sat1 mean elements after propagating to TLE0 epoch
satB = copy.deepcopy(sat1)
satB = satfit.delta_el(satB,xincl=satB.im,xnodeo=satB.Om,ec=satB.em,omegao=satB.om,xmo=satB.mm,xno=satB.no_kozai,bsr=sat1.bstar, jdsatepoch=sat0.jdsatepoch)
# satB.jdsatepoch = sat0.jdsatepoch
# satB.jdSGP4epoch = satB.jdsatepoch - 2433281.5
# satB.epoch_datetime = satfit.jday_to_datetime(satB.jdsatepoch)
satB = satfit.delta_t(satB,sat0.jdsatepoch)
# satr : Elements created from rv2coe from sat1x r,v vectors TLE0 epoch
satr = copy.deepcopy(sat1)
(p, a, ecc, incl, omega, argp, nu, m, arglat, truelon, lonper) = rv2coe(satr.rr_km, satr.vv_kmpersec, satr.whichconst.mu)
# satx = satfit.delta_el(sat1,xincl=sat1.inclo,xnodeo=sat1.nodeo,ec=sat1.ecco,omegao=sat1.argpo,xmo=sat1.mo,xno=sat1.no_kozai,bsr=sat1.bstar)
mean_motion = sqrt(satr.whichconst.mu/(pow(a,3)))*60.0 # radians per minute
satr = satfit.delta_el(satr,xincl=incl,xnodeo=omega,ec=ecc,omegao=argp,xmo=m,xno=mean_motion,bsr=satr.bstar, jdsatepoch=sat0.jdsatepoch)
# satr.jdsatepoch = sat0.jdsatepoch
# satr.jdSGP4epoch = satr.jdsatepoch - 2433281.5
# satr.epoch_datetime = satfit.jday_to_datetime(satr.jdsatepoch)
satr = satfit.delta_t(satr,sat0.jdsatepoch)
print()
print("sat1: Original elements back-propagated to perigee (epoch of sat0)")
print("sat2 : Elements regressed to perigee by satfit.py TLE0 epoch")
print("sat0 : Elements regressed to perigee by satfit.cpp TLE0 epoch")
print("satA : Elements created from sat0 mean elements after propagating to TLE0 epoch")
print("satB : Elements created from sat1 mean elements after propagating to TLE0 epoch")
print("satr : Elements created from rv2coe from sat1x r,v vectors TLE0 epoch")
print()
print("At TLE epoch jd {}".format(sat0.jdsatepoch))
print("sat1.rr {} sat1.vv {}".format(sat1.rr_km,sat1.vv_kmpersec))
print("sat2.rr {} sat2.vv {}".format(sat2.rr_km,sat2.vv_kmpersec))
print("sat0.rr {} sat0.vv {}".format(sat0.rr_km,sat0.vv_kmpersec))
print("satA.rr {} satA.vv {}".format(satA.rr_km,satA.vv_kmpersec))
print("satB.rr {} satB.vv {}".format(satB.rr_km,satB.vv_kmpersec))
print("satr.rr {} satr.vv {}".format(satr.rr_km,satr.vv_kmpersec))
dayahead = sat0.jdsatepoch + 1
sat0 = satfit.delta_t(sat0,dayahead)
sat1 = satfit.delta_t(sat1,dayahead) # Changing tsince changes the mean elements
sat2 = satfit.delta_t(sat2,dayahead) # Changing tsince changes the mean elements
satA = satfit.delta_t(satA,dayahead)
satB = satfit.delta_t(satB,dayahead)
print()
print("At TLE epoch jd {} (Epoch + 1 day)".format(dayahead))
print("sat1.rr {} sat1.vv {}".format(sat1.rr_km,sat1.vv_kmpersec))
print("sat2.rr {} sat2.vv {}".format(sat2.rr_km,sat2.vv_kmpersec))
print("sat0.rr {} sat0.vv {}".format(sat0.rr_km,sat0.vv_kmpersec))
print("satA.rr {} satA.vv {}".format(satA.rr_km,satA.vv_kmpersec))
print("satB.rr {} satB.vv {}".format(satB.rr_km,satB.vv_kmpersec))
print("satr.rr {} satr.vv {}".format(satr.rr_km,satr.vv_kmpersec))
dayahead = sat0.jdsatepoch + 10
sat0 = satfit.delta_t(sat0,dayahead)
sat1 = satfit.delta_t(sat1,dayahead) # Changing tsince changes the mean elements
sat2 = satfit.delta_t(sat2,dayahead) # Changing tsince changes the mean elements
satA = satfit.delta_t(satA,dayahead)
satB = satfit.delta_t(satB,dayahead)
print()
print("At TLE epoch jd {} (Epoch + 10 day)".format(dayahead))
print("sat1.rr {} sat1.vv {}".format(sat1.rr_km,sat1.vv_kmpersec))
print("sat2.rr {} sat2.vv {}".format(sat2.rr_km,sat2.vv_kmpersec))
print("sat0.rr {} sat0.vv {}".format(sat0.rr_km,sat0.vv_kmpersec))
print("satA.rr {} satA.vv {}".format(satA.rr_km,satA.vv_kmpersec))
print("satB.rr {} satB.vv {}".format(satB.rr_km,satB.vv_kmpersec))
print("satr.rr {} satr.vv {}".format(satr.rr_km,satr.vv_kmpersec))
