How to use the sgp4.model.Satellite function in sgp4

def test_legacy_initialized_with_sgp4init():
    sat = model.Satellite()
    sgp4init(
        wgs72, 'i', VANGUARD_ATTRS['satnum'], VANGUARD_EPOCH,
        *sgp4init_args(VANGUARD_ATTRS) + (sat,)
    )
    verify_vanguard_1(sat, legacy=True)

import os
import sys
from distutils.core import setup, Extension
from textwrap import dedent

import sgp4, sgp4.model

description, long_description = sgp4.__doc__.split('\n', 1)
satdoc = dedent(sgp4.model.Satellite.__doc__.split('\n', 1)[1])
long_description = long_description.replace('entry.', 'entry.' + satdoc)

# Force compilation on Travis CI + Python 3 to make sure it keeps working.
optional = True
if sys.version_info[0] != 2 and os.environ.get('TRAVIS') == 'true':
    optional = False

# It is hard to write C extensions that support both Python 2 and 3, so
# we opt here to support the acceleration only for Python 3.
ext_modules = []
if sys.version_info[0] == 3:
    ext_modules.append(Extension(
        'sgp4.vallado_cpp',
        optional=optional,
        sources=[
            'extension/SGP4.cpp',

kep(1x6 numpy array): the osculating keplerian elements at epoch
           epoch(float): the epoch
           bstar(float): bstar drag coefficient
           whichconst(float): gravity model. refer pypi sgp4 documentation
           afspc_mode(boolean): refer pypi sgp4 documentation

      Returns:
           Satellite object: an sgp4 satellite object encapsulating the arguments
    """

    deg2rad  =  np.pi / 180.0;         #    0.0174532925199433
    xpdotp   =  1440.0 / (2.0 * np.pi);  #  229.1831180523293

    tumin = whichconst.tumin

    satrec = Satellite()
    satrec.error = 0;
    satrec.whichconst = whichconst # Python extension: remembers its consts

    satrec.satnum = 0
    dt_obj = datetime.utcfromtimestamp(epoch)
    t_obj = dt_obj.timetuple()
    satrec.epochdays = (t_obj.tm_yday +
                        t_obj.tm_hour/24 +
                        t_obj.tm_min/1440 +
                        t_obj.tm_sec/86400)
    satrec.ndot = 0
    satrec.nddot = 0
    satrec.bstar = bstar

    satrec.inclo = kep[2]
    satrec.nodeo = kep[4]

kep(1x6 numpy array): the osculating keplerian elements at epoch
           epoch(float): the epoch
           bstar(float): bstar drag coefficient
           whichconst(float): gravity model. refer pypi sgp4 documentation
           afspc_mode(boolean): refer pypi sgp4 documentation

      Returns:
           Satellite object: an sgp4 satellite object encapsulating the arguments
    """

    deg2rad  =  np.pi / 180.0;         #    0.0174532925199433
    xpdotp   =  1440.0 / (2.0 * np.pi);  #  229.1831180523293

    tumin = whichconst.tumin

    satrec = Satellite()
    satrec.error = 0;
    satrec.whichconst = whichconst # Python extension: remembers its consts

    satrec.satnum = 0
    dt_obj = datetime.utcfromtimestamp(epoch)
    t_obj = dt_obj.timetuple()
    satrec.epochdays = (t_obj.tm_yday +
                        t_obj.tm_hour/24 +
                        t_obj.tm_min/1440 +
                        t_obj.tm_sec/86400)
    satrec.ndot = 0
    satrec.nddot = 0
    satrec.bstar = bstar

    satrec.inclo = kep[2]
    satrec.nodeo = kep[4]