def init_date(self):
if self.epoch_yr < 57:
year = self.epoch_yr + 2000
else:
year = self.epoch_yr + 1900
mon, day, hr, minute, sec = days2mdhms(year, self.epoch_day)
sec_whole, sec_frac = divmod(sec, 1.0)
self.date = datetime(year, mon, day, hr, minute, int(sec_whole),
int(sec_frac * 1000000.0 // 1.0), timezone.utc)
self.timestamp = int(time.mktime(self.date.timetuple()))
self.jdate = jday(year, mon, day, hr, minute, sec)
def twoline2rv(cls, line1, line2, whichconst=WGS72):
whichconst = gravity_constants[whichconst]
self = cls()
twoline2rv(line1, line2, whichconst, 'i', self)
# Install a fancy split JD of the kind the C++ natively supports.
# We rebuild it from the TLE year and day to maintain precision.
year = self.epochyr
month, day, h, m, s = days2mdhms(year, self.epochdays)
self.jdsatepoch, self.jdsatepochF = jday2(year, month, day, h, m, s)
# Undo my non-standard 4-digit year
self.epochyr %= 100
return self
def twoline2rv(longstr1, longstr2, whichconst, opsmode='i', satrec=None):
"""Return a Satellite imported from two lines of TLE data.
Provide the two TLE lines as strings `longstr1` and `longstr2`,
and select which standard set of gravitational constants you want
by providing `gravity_constants`:
`sgp4.earth_gravity.wgs72` - Standard WGS 72 model
`sgp4.earth_gravity.wgs84` - More recent WGS 84 model
`sgp4.earth_gravity.wgs72old` - Legacy support for old SGP4 behavior
Normally, computations are made using various recent improvements
to the algorithm. If you want to turn some of these off and go
back into "opsmode" mode, then set `opsmode` to `a`.
"""
deg2rad = pi / 180.0
# 0.0174532925199433
xpdotp = 1440.0 / (2.0 * pi)
# 229.1831180523293
# For compatibility with our 1.x API, build an old Satellite object
# if the caller fails to supply a satrec. In that case we perform
# the necessary import here to avoid an import loop.
if satrec is None:
from sgp4.model import Satellite
satrec = Satellite()
satrec.error = 0
satrec.whichconst = whichconst # Python extension: remembers its consts
line = longstr1.rstrip()
if (len(line) >= 64 and line.startswith('1 ') and line[8] == ' '
and line[23] == '.' and line[32] == ' ' and line[34] == '.'
and line[43] == ' ' and line[52] == ' ' and line[61] == ' '
and line[63] == ' '):
_saved_satnum = satrec.satnum = _alpha5(line[2:7])
satrec.classification = line[7] or 'U'
satrec.intldesg = line[9:17].rstrip()
two_digit_year = int(line[18:20])
satrec.epochdays = float(line[20:32])
satrec.ndot = float(line[33:43])
satrec.nddot = float(line[44] + '.' + line[45:50])
nexp = int(line[50:52])
satrec.bstar = float(line[53] + '.' + line[54:59])
ibexp = int(line[59:61])
satrec.ephtype = line[62]
satrec.elnum = int(line[64:68])
else:
raise ValueError(error_message.format(1, LINE1, line))
line = longstr2.rstrip()
if (len(line) >= 69 and line.startswith('2 ') and line[7] == ' '
and line[11] == '.' and line[16] == ' ' and line[20] == '.'
and line[25] == ' ' and line[33] == ' ' and line[37] == '.'
and line[42] == ' ' and line[46] == '.' and line[51] == ' '):
satrec.satnum = _alpha5(line[2:7])
if _saved_satnum != satrec.satnum:
raise ValueError('Object numbers in lines 1 and 2 do not match')
satrec.inclo = float(line[8:16])
satrec.nodeo = float(line[17:25])
satrec.ecco = float('0.' + line[26:33].replace(' ', '0'))
satrec.argpo = float(line[34:42])
satrec.mo = float(line[43:51])
satrec.no_kozai = float(line[52:63])
satrec.revnum = line[63:68]
#except (AssertionError, IndexError, ValueError):
else:
raise ValueError(error_message.format(2, LINE2, line))
# ---- find no, ndot, nddot ----
satrec.no_kozai = satrec.no_kozai / xpdotp
# rad/min
satrec.nddot = satrec.nddot * pow(10.0, nexp)
satrec.bstar = satrec.bstar * pow(10.0, ibexp)
# ---- convert to sgp4 units ----
satrec.ndot = satrec.ndot / (xpdotp * 1440.0)
# ? * minperday
satrec.nddot = satrec.nddot / (xpdotp * 1440.0 * 1440)
# ---- find standard orbital elements ----
satrec.inclo = satrec.inclo * deg2rad
satrec.nodeo = satrec.nodeo * deg2rad
satrec.argpo = satrec.argpo * deg2rad
satrec.mo = satrec.mo * deg2rad
"""
// ----------------------------------------------------------------
// find sgp4epoch time of element set
// remember that sgp4 uses units of days from 0 jan 1950 (sgp4epoch)
// and minutes from the epoch (time)
// ----------------------------------------------------------------
// ---------------- temp fix for years from 1957-2056 -------------------
// --------- correct fix will occur when year is 4-digit in tle ---------
"""
if two_digit_year < 57:
year = two_digit_year + 2000
else:
year = two_digit_year + 1900
mon, day, hr, minute, sec = days2mdhms(year, satrec.epochdays)
sec_whole, sec_fraction = divmod(sec, 1.0)
satrec.epochyr = year
satrec.jdsatepoch = jday(year, mon, day, hr, minute, sec)
try:
satrec.epoch = datetime(year, mon, day, hr, minute, int(sec_whole),
int(sec_fraction * 1000000.0 // 1.0))
except ValueError:
# Sometimes a TLE says something like "2019 + 366.82137887 days"
# which would be December 32nd which causes a ValueError.
year, mon, day, hr, minute, sec = invjday(satrec.jdsatepoch)
satrec.epoch = datetime(year, mon, day, hr, minute, int(sec_whole),
int(sec_fraction * 1000000.0 // 1.0))
# ---------------- initialize the orbit at sgp4epoch -------------------
sgp4init(whichconst, opsmode, satrec.satnum, satrec.jdsatepoch - 2433281.5,
satrec.bstar, satrec.ndot, satrec.nddot, satrec.ecco,
satrec.argpo, satrec.inclo, satrec.mo, satrec.no_kozai,
satrec.nodeo, satrec)
return satrec
def twoline2rv(longstr1, longstr2, whichconst, afspc_mode=False):
"""Return a Satellite imported from two lines of TLE data.
Provide the two TLE lines as strings `longstr1` and `longstr2`,
and select which standard set of gravitational constants you want
by providing `gravity_constants`:
`sgp4.earth_gravity.wgs72` - Standard WGS 72 model
`sgp4.earth_gravity.wgs84` - More recent WGS 84 model
`sgp4.earth_gravity.wgs72old` - Legacy support for old SGP4 behavior
Normally, computations are made using various recent improvements
to the algorithm. If you want to turn some of these off and go
back into "afspc" mode, then set `afspc_mode` to `True`.
"""
deg2rad = pi / 180.0
# 0.0174532925199433
xpdotp = 1440.0 / (2.0 * pi)
# 229.1831180523293
tumin = whichconst.tumin
satrec = Satellite()
satrec.error = 0
satrec.whichconst = whichconst # Python extension: remembers its consts
line = longstr1.rstrip()
# try/except is not well supported by Numba
if (len(line) >= 64 and line.startswith('1 ') and line[8] == ' '
and line[23] == '.' and line[32] == ' ' and line[34] == '.'
and line[43] == ' ' and line[52] == ' ' and line[61] == ' '
and line[63] == ' '):
_saved_satnum = satrec.satnum = int(line[2:7])
# classification = line[7] or 'U'
# intldesg = line[9:17]
two_digit_year = int(line[18:20])
satrec.epochdays = float(line[20:32])
satrec.ndot = float(line[33:43])
satrec.nddot = float(line[44] + '.' + line[45:50])
nexp = int(line[50:52])
satrec.bstar = float(line[53] + '.' + line[54:59])
ibexp = int(line[59:61])
# numb = int(line[62])
# elnum = int(line[64:68])
else:
raise ValueError(error_message.format(1, LINE1, line))
line = longstr2.rstrip()
line_format_ok = False
if (len(line) >= 69 and line.startswith('2 ') and line[7] == ' '
and line[11] == '.' and line[16] == ' ' and line[20] == '.'
and line[25] == ' ' and line[33] == ' ' and line[37] == '.'
and line[42] == ' ' and line[46] == '.' and line[51] == ' '):
satrec.satnum = int(line[2:7])
if _saved_satnum != satrec.satnum:
raise ValueError('Object numbers in lines 1 and 2 do not match')
satrec.inclo = float(line[8:16])
satrec.nodeo = float(line[17:25])
satrec.ecco = float('0.' + line[26:33].replace(' ', '0'))
satrec.argpo = float(line[34:42])
satrec.mo = float(line[43:51])
satrec.no = float(line[52:63])
#revnum = line[63:68]
#except (AssertionError, IndexError, ValueError):
else:
raise ValueError(error_message.format(2, LINE2, line))
# ---- find no, ndot, nddot ----
satrec.no = satrec.no / xpdotp
# rad/min
satrec.nddot = satrec.nddot * pow(10.0, nexp)
satrec.bstar = satrec.bstar * pow(10.0, ibexp)
# ---- convert to sgp4 units ----
satrec.a = pow(satrec.no * tumin, (-2.0 / 3.0))
satrec.ndot = satrec.ndot / (xpdotp * 1440.0)
# ? * minperday
satrec.nddot = satrec.nddot / (xpdotp * 1440.0 * 1440)
# ---- find standard orbital elements ----
satrec.inclo = satrec.inclo * deg2rad
satrec.nodeo = satrec.nodeo * deg2rad
satrec.argpo = satrec.argpo * deg2rad
satrec.mo = satrec.mo * deg2rad
satrec.alta = satrec.a * (1.0 + satrec.ecco) - 1.0
satrec.altp = satrec.a * (1.0 - satrec.ecco) - 1.0
"""
// ----------------------------------------------------------------
// find sgp4epoch time of element set
// remember that sgp4 uses units of days from 0 jan 1950 (sgp4epoch)
// and minutes from the epoch (time)
// ----------------------------------------------------------------
// ---------------- temp fix for years from 1957-2056 -------------------
// --------- correct fix will occur when year is 4-digit in tle ---------
"""
if two_digit_year < 57:
year = two_digit_year + 2000
else:
year = two_digit_year + 1900
mon, day, hr, minute, sec = days2mdhms(year, satrec.epochdays)
sec_whole, sec_fraction = divmod(sec, 1.0)
satrec.epochyr = year
satrec.jdsatepoch = jday(year, mon, day, hr, minute, sec)
satrec.epoch = datetime(year, mon, day, hr, minute, int(sec_whole),
int(sec_fraction * 1000000.0 // 1.0))
# ---------------- initialize the orbit at sgp4epoch -------------------
sgp4init(whichconst, afspc_mode, satrec.satnum,
satrec.jdsatepoch - 2433281.5, satrec.bstar, satrec.ecco,
satrec.argpo, satrec.inclo, satrec.mo, satrec.no, satrec.nodeo,
satrec)
return satrec
def __init__(self, line1, line2):
self._line1 = line1
self._line2 = line2
line = line1.rstrip()
# deg2rad = pi / 180.0; # 0.0174532925199433
# xpdotp = 1440.0 / (2.0 * pi); # 229.1831180523293
# tumin = wgs84.tumin
try:
assert line.startswith('1 ')
self._satnum = int(line[2:7])
assert line[8] == ' '
two_digit_year = int(line[18:20])
assert line[23] == '.'
self.epochdays = float(line[20:32])
assert line[32] == ' '
assert line[34] == '.'
#self.ndot = float(line[33:43])
assert line[43] == ' '
#self.nddot = float(line[44] + '.' + line[45:50])
#nexp = int(line[50:52])
assert line[52] == ' '
#self.bstar = float(line[53] + '.' + line[54:59])
#ibexp = int(line[59:61])
assert line[61] == ' '
assert line[63] == ' '
except (AssertionError, IndexError, ValueError):
raise ValueError(error_message.format(1, LINE1, line))
line = line2.rstrip()
try:
assert line.startswith('2 ')
self._satnum = int(line[2:7]) # TODO: check it matches line 1?
assert line[7] == ' '
assert line[11] == '.'
#self.inclo = float(line[8:16])
assert line[16] == ' '
assert line[20] == '.'
#self.nodeo = float(line[17:25])
assert line[25] == ' '
#self.ecco = float('0.' + line[26:33].replace(' ', '0'))
assert line[33] == ' '
assert line[37] == '.'
#self.argpo = float(line[34:42])
assert line[42] == ' '
assert line[46] == '.'
#self.mo = float(line[43:51])
assert line[51] == ' '
#self.no = float(line[52:63])
#revnum = line[63:68]
except (AssertionError, IndexError, ValueError):
raise ValueError(error_message.format(2, LINE2, line))
# ---- find no, ndot, nddot ----
#self.no = self.no / xpdotp; # rad/min
#self.nddot= self.nddot * pow(10.0, nexp);
#self.bstar= self.bstar * pow(10.0, ibexp);
# ---- convert to sgp4 units ----
#self.a = pow( self.no*tumin , (-2.0/3.0) );
#self.ndot = self.ndot / (xpdotp*1440.0); # ? * minperday
#self.nddot= self.nddot / (xpdotp*1440.0*1440);
# ---- find standard orbital elements ----
#self.inclo = self.inclo * deg2rad;
#self.nodeo = self.nodeo * deg2rad;
#self.argpo = self.argpo * deg2rad;
#self.mo = self.mo * deg2rad;
#self.alta = self.a*(1.0 + self.ecco) - 1.0;
#self.altp = self.a*(1.0 - self.ecco) - 1.0;
if two_digit_year < 57:
year = two_digit_year + 2000;
else:
year = two_digit_year + 1900;
mon,day,hr,minute,sec = days2mdhms(year, self.epochdays);
sec_whole, sec_fraction = divmod(sec, 1.0)
self.epochyr = year
self.jdsatepoch = jday(year,mon,day,hr,minute,sec);
self._epoch = datetime(year, mon, day, hr, minute, int(sec_whole),
int(sec_fraction * 1000000.0 // 1.0), tzinfo=timezone.utc)
def twoline2rv(longstr1, longstr2, whichconst, afspc_mode=False):
"""Return a Satellite imported from two lines of TLE data.
Provide the two TLE lines as strings `longstr1` and `longstr2`,
and select which standard set of gravitational constants you want
by providing `gravity_constants`:
`sgp4.earth_gravity.wgs72` - Standard WGS 72 model
`sgp4.earth_gravity.wgs84` - More recent WGS 84 model
`sgp4.earth_gravity.wgs72old` - Legacy support for old SGP4 behavior
Normally, computations are made using various recent improvements
to the algorithm. If you want to turn some of these off and go
back into "afspc" mode, then set `afspc_mode` to `True`.
"""
opsmode = 'a' if afspc_mode else 'i'
deg2rad = pi / 180.0; # 0.0174532925199433
xpdotp = 1440.0 / (2.0 *pi); # 229.1831180523293
revnum = 0;
elnum = 0;
tumin = whichconst.tumin
satrec = Satellite()
satrec.error = 0;
satrec.whichconst = whichconst # Python extension: remembers its consts
# This is Python, so we convert the strings into mutable lists of
# characters before setting the C++ code loose on them.
longstr1 = [ c for c in longstr1 ]
longstr2 = [ c for c in longstr2 ]
# set the implied decimal points since doing a formated read
# fixes for bad input data values (missing, ...)
for j in range(10, 16):
if longstr1[j] == ' ':
longstr1[j] = '_';
if longstr1[44] != ' ':
longstr1[43] = longstr1[44];
longstr1[44] = '.';
if longstr1[7] == ' ':
longstr1[7] = 'U';
if longstr1[9] == ' ':
longstr1[9] = '.';
for j in range(45, 50):
if longstr1[j] == ' ':
longstr1[j] = '0';
if longstr1[51] == ' ':
longstr1[51] = '0';
if longstr1[53] != ' ':
longstr1[52] = longstr1[53];
longstr1[53] = '.';
longstr2[25] = '.';
for j in range(26, 33):
if longstr2[j] == ' ':
longstr2[j] = '0';
if longstr1[62] == ' ':
longstr1[62] = '0';
if longstr1[68] == ' ':
longstr1[68] = '0';
# Concatenate lists back into real strings.
longstr1 = ''.join(longstr1)
longstr2 = ''.join(longstr2)
(cardnumb,satrec.satnum,classification, intldesg, two_digit_year,
satrec.epochdays,satrec.ndot, satrec.nddot, nexp, satrec.bstar,
ibexp, numb, elnum) = \
sscanf(longstr1,"%2d %5ld %1c %10s %2d %12lf %11lf %7lf %2d %7lf %2d %2d %6ld ",
)
if longstr2[52] == ' ':
(cardnumb,satrec.satnum, satrec.inclo,
satrec.nodeo,satrec.ecco, satrec.argpo, satrec.mo, satrec.no,
revnum) = \
sscanf(longstr2,"%2d %5ld %9lf %9lf %8lf %9lf %9lf %10lf %6ld \n",
)
else:
(cardnumb,satrec.satnum, satrec.inclo,
satrec.nodeo,satrec.ecco, satrec.argpo, satrec.mo, satrec.no,
revnum) = \
sscanf(longstr2,"%2d %5ld %9lf %9lf %8lf %9lf %9lf %11lf %6ld \n",
)
# ---- find no, ndot, nddot ----
satrec.no = satrec.no / xpdotp; # rad/min
satrec.nddot= satrec.nddot * pow(10.0, nexp);
satrec.bstar= satrec.bstar * pow(10.0, ibexp);
# ---- convert to sgp4 units ----
satrec.a = pow( satrec.no*tumin , (-2.0/3.0) );
satrec.ndot = satrec.ndot / (xpdotp*1440.0); # ? * minperday
satrec.nddot= satrec.nddot / (xpdotp*1440.0*1440);
# ---- find standard orbital elements ----
satrec.inclo = satrec.inclo * deg2rad;
satrec.nodeo = satrec.nodeo * deg2rad;
satrec.argpo = satrec.argpo * deg2rad;
satrec.mo = satrec.mo * deg2rad;
satrec.alta = satrec.a*(1.0 + satrec.ecco) - 1.0;
satrec.altp = satrec.a*(1.0 - satrec.ecco) - 1.0;
"""
// ----------------------------------------------------------------
// find sgp4epoch time of element set
// remember that sgp4 uses units of days from 0 jan 1950 (sgp4epoch)
// and minutes from the epoch (time)
// ----------------------------------------------------------------
// ---------------- temp fix for years from 1957-2056 -------------------
// --------- correct fix will occur when year is 4-digit in tle ---------
"""
if two_digit_year < 57:
year = two_digit_year + 2000;
else:
year = two_digit_year + 1900;
mon,day,hr,minute,sec = days2mdhms(year, satrec.epochdays);
sec_whole, sec_fraction = divmod(sec, 1.0)
satrec.epochyr = year
satrec.jdsatepoch = jday(year,mon,day,hr,minute,sec);
satrec.epoch = datetime(year, mon, day, hr, minute, int(sec_whole),
int(sec_fraction * 1000000.0 // 1.0))
# ---------------- initialize the orbit at sgp4epoch -------------------
sgp4init( whichconst, opsmode, satrec.satnum, satrec.jdsatepoch-2433281.5, satrec.bstar,
satrec.ecco, satrec.argpo, satrec.inclo, satrec.mo, satrec.no,
satrec.nodeo, satrec);
return satrec
def get_sat_epoch(y, d):
y += 2000
return sum(jday(y, *days2mdhms(y, d)))
def twoline2rv(longstr1, longstr2, whichconst, afspc_mode=False):
"""Return a Satellite imported from two lines of TLE data.
Provide the two TLE lines as strings `longstr1` and `longstr2`,
and select which standard set of gravitational constants you want
by providing `gravity_constants`:
`sgp4.earth_gravity.wgs72` - Standard WGS 72 model
`sgp4.earth_gravity.wgs84` - More recent WGS 84 model
`sgp4.earth_gravity.wgs72old` - Legacy support for old SGP4 behavior
Normally, computations are made using various recent improvements
to the algorithm. If you want to turn some of these off and go
back into "afspc" mode, then set `afspc_mode` to `True`.
"""
opsmode = 'a' if afspc_mode else 'i'
deg2rad = pi / 180.0; # 0.0174532925199433
xpdotp = 1440.0 / (2.0 *pi); # 229.1831180523293
tumin = whichconst.tumin
satrec = Satellite()
satrec.error = 0;
satrec.whichconst = whichconst # Python extension: remembers its consts
line = longstr1.rstrip()
try:
assert line.startswith('1 ')
satrec.satnum = int(line[2:7])
# classification = line[7] or 'U'
assert line[8] == ' '
# intldesg = line[9:17]
two_digit_year = int(line[18:20])
assert line[23] == '.'
satrec.epochdays = float(line[20:32])
assert line[32] == ' '
assert line[34] == '.'
satrec.ndot = float(line[33:43])
assert line[43] == ' '
satrec.nddot = float(line[44] + '.' + line[45:50])
nexp = int(line[50:52])
assert line[52] == ' '
satrec.bstar = float(line[53] + '.' + line[54:59])
ibexp = int(line[59:61])
assert line[61] == ' '
assert line[63] == ' '
# numb = int(line[62])
# elnum = int(line[64:68])
except (AssertionError, IndexError, ValueError):
raise ValueError(error_message.format(1, LINE1, line))
line = longstr2.rstrip()
try:
assert line.startswith('2 ')
satrec.satnum = int(line[2:7]) # TODO: check it matches line 1?
assert line[7] == ' '
assert line[11] == '.'
satrec.inclo = float(line[8:16])
assert line[16] == ' '
assert line[20] == '.'
satrec.nodeo = float(line[17:25])
assert line[25] == ' '
satrec.ecco = float('0.' + line[26:33].replace(' ', '0'))
assert line[33] == ' '
assert line[37] == '.'
satrec.argpo = float(line[34:42])
assert line[42] == ' '
assert line[46] == '.'
satrec.mo = float(line[43:51])
assert line[51] == ' '
satrec.no = float(line[52:63])
#revnum = line[63:68]
except (AssertionError, IndexError, ValueError):
raise ValueError(error_message.format(2, LINE2, line))
# ---- find no, ndot, nddot ----
satrec.no = satrec.no / xpdotp; # rad/min
satrec.nddot= satrec.nddot * pow(10.0, nexp);
satrec.bstar= satrec.bstar * pow(10.0, ibexp);
# ---- convert to sgp4 units ----
satrec.a = pow( satrec.no*tumin , (-2.0/3.0) );
satrec.ndot = satrec.ndot / (xpdotp*1440.0); # ? * minperday
satrec.nddot= satrec.nddot / (xpdotp*1440.0*1440);
# ---- find standard orbital elements ----
satrec.inclo = satrec.inclo * deg2rad;
satrec.nodeo = satrec.nodeo * deg2rad;
satrec.argpo = satrec.argpo * deg2rad;
satrec.mo = satrec.mo * deg2rad;
satrec.alta = satrec.a*(1.0 + satrec.ecco) - 1.0;
satrec.altp = satrec.a*(1.0 - satrec.ecco) - 1.0;
"""
// ----------------------------------------------------------------
// find sgp4epoch time of element set
// remember that sgp4 uses units of days from 0 jan 1950 (sgp4epoch)
// and minutes from the epoch (time)
// ----------------------------------------------------------------
// ---------------- temp fix for years from 1957-2056 -------------------
// --------- correct fix will occur when year is 4-digit in tle ---------
"""
if two_digit_year < 57:
year = two_digit_year + 2000;
else:
year = two_digit_year + 1900;
mon,day,hr,minute,sec = days2mdhms(year, satrec.epochdays);
sec_whole, sec_fraction = divmod(sec, 1.0)
satrec.epochyr = year
satrec.jdsatepoch = jday(year,mon,day,hr,minute,sec);
satrec.epoch = datetime(year, mon, day, hr, minute, int(sec_whole),
int(sec_fraction * 1000000.0 // 1.0))
# ---------------- initialize the orbit at sgp4epoch -------------------
sgp4init(whichconst, opsmode, satrec.satnum, satrec.jdsatepoch-2433281.5, satrec.bstar,
satrec.ecco, satrec.argpo, satrec.inclo, satrec.mo, satrec.no,
satrec.nodeo, satrec)
return satrec
def twoline2rv(longstr1, longstr2, whichconst, afspc_mode=False):
deg2rad = pi / 180.0; # 0.0174532925199433
xpdotp = 1440.0 / (2.0 *pi); # 229.1831180523293
tumin = whichconst.tumin
satrec = Satellite()
satrec.error = 0;
satrec.whichconst = whichconst # Python extension: remembers its consts
line = longstr1.rstrip()
# try/except is not well supported by Numba
if (len(line) >= 64 and
line.startswith('1 ') and
line[8] == ' ' and
line[23] == '.' and
line[32] == ' ' and
line[34] == '.' and
line[43] == ' ' and
line[52] == ' ' and
line[61] == ' ' and
line[63] == ' '):
_saved_satnum = satrec.satnum = int(line[2:7])
# classification = line[7] or 'U'
# intldesg = line[9:17]
two_digit_year = int(line[18:20])
satrec.epochdays = float(line[20:32])
satrec.ndot = float(line[33:43])
satrec.nddot = float(line[44] + '.' + line[45:50])
nexp = int(line[50:52])
satrec.bstar = float(line[53] + '.' + line[54:59])
ibexp = int(line[59:61])
# numb = int(line[62])
# elnum = int(line[64:68])
else:
raise ValueError(error_message.format(1, LINE1, line))
line = longstr2.rstrip()
if (len(line) >= 69 and
line.startswith('2 ') and
line[7] == ' ' and
line[11] == '.' and
line[16] == ' ' and
line[20] == '.' and
line[25] == ' ' and
line[33] == ' ' and
line[37] == '.' and
line[42] == ' ' and
line[46] == '.' and
line[51] == ' '):
satrec.satnum = int(line[2:7])
if _saved_satnum != satrec.satnum:
raise ValueError('Object numbers in lines 1 and 2 do not match')
satrec.inclo = float(line[8:16])
satrec.nodeo = float(line[17:25])
satrec.ecco = float('0.' + line[26:33].replace(' ', '0'))
satrec.argpo = float(line[34:42])
satrec.mo = float(line[43:51])
satrec.no = float(line[52:63])
#revnum = line[63:68]
#except (AssertionError, IndexError, ValueError):
else:
raise ValueError(error_message.format(2, LINE2, line))
# ---- find no, ndot, nddot ----
satrec.no = satrec.no / xpdotp; # rad/min
satrec.nddot= satrec.nddot * pow(10.0, nexp);
satrec.bstar= satrec.bstar * pow(10.0, ibexp);
# ---- convert to sgp4 units ----
satrec.a = pow( satrec.no*tumin , (-2.0/3.0) );
satrec.ndot = satrec.ndot / (xpdotp*1440.0); # ? * minperday
satrec.nddot= satrec.nddot / (xpdotp*1440.0*1440);
# ---- find standard orbital elements ----
satrec.inclo = satrec.inclo * deg2rad;
satrec.nodeo = satrec.nodeo * deg2rad;
satrec.argpo = satrec.argpo * deg2rad;
satrec.mo = satrec.mo * deg2rad;
satrec.alta = satrec.a*(1.0 + satrec.ecco) - 1.0;
satrec.altp = satrec.a*(1.0 - satrec.ecco) - 1.0;
if two_digit_year < 57:
year = two_digit_year + 2000;
else:
year = two_digit_year + 1900;
mon,day,hr,minute,sec = days2mdhms(year, satrec.epochdays);
sec_whole, sec_fraction = divmod(sec, 1.0)
satrec.epochyr = year
satrec.jdsatepoch = jday(year,mon,day,hr,minute,sec);
satrec.epoch = datetime(year, mon, day, hr, minute, int(sec_whole),
int(sec_fraction * 1000000.0 // 1.0))
# ---------------- initialize the orbit at sgp4epoch -------------------
sgp4init(whichconst, afspc_mode, satrec.satnum, satrec.jdsatepoch-2433281.5, satrec.bstar,
satrec.ecco, satrec.argpo, satrec.inclo, satrec.mo, satrec.no,
satrec.nodeo, satrec)
return satrec
def get_satepoch(y, d):
"""
Compute satellite epoch Julian date
"""
y += 2000
return sum(jday(y, *days2mdhms(y, d)))