def test_dump_opm_interplanetary(jplfiles, orbit, ccsds_format, datafile,
helper):
create_frames("Mars")
orbit.frame = "Mars"
txt = dumps(orbit, fmt=ccsds_format)
helper.assert_string(datafile("opm_interplanetary"), txt)
def test_soi(jplfiles):
opm = ccsds.loads("""CCSDS_OPM_VERS = 2.0
CREATION_DATE = 2019-02-22T23:22:31
ORIGINATOR = N/A
META_START
OBJECT_NAME = N/A
OBJECT_ID = N/A
CENTER_NAME = EARTH
REF_FRAME = EME2000
TIME_SYSTEM = UTC
META_STOP
COMMENT State Vector
EPOCH = 2018-05-02T00:00:00.000000
X = 6678.000000 [km]
Y = 0.000000 [km]
Z = 0.000000 [km]
X_DOT = 0.000000 [km/s]
Y_DOT = 7.088481 [km/s]
Z_DOT = 3.072802 [km/s]
COMMENT Keplerian elements
SEMI_MAJOR_AXIS = 6678.000000 [km]
ECCENTRICITY = 0.000000
INCLINATION = 23.436363 [deg]
RA_OF_ASC_NODE = 0.000000 [deg]
ARG_OF_PERICENTER = 0.000000 [deg]
TRUE_ANOMALY = 0.000000 [deg]
COMMENT Escaping Earth
MAN_EPOCH_IGNITION = 2018-05-02T00:39:03.955092
MAN_DURATION = 0.000 [s]
MAN_DELTA_MASS = 0.000 [kg]
MAN_REF_FRAME = TNW
MAN_DV_1 = 3.456791 [km/s]
MAN_DV_2 = 0.000000 [km/s]
MAN_DV_3 = 0.000000 [km/s]
""")
planetary_step = timedelta(seconds=180)
solar_step = timedelta(hours=12)
jpl.create_frames()
central = jpl.get_body('Sun')
planets = jpl.get_body('Earth')
opm.propagator = SOIPropagator(solar_step, planetary_step, central, planets)
frames = set()
for orb in opm.iter(stop=timedelta(5)):
frames.add(orb.frame.name)
assert not frames.symmetric_difference(['Sun', 'EME2000'])
# Check if the last point is out of Earth sphere of influence
assert orb.copy(frame='EME2000', form="spherical").r > SOIPropagator.SOI['Earth'].radius
def test_soi(jplfiles):
opm = ccsds.loads("""CCSDS_OPM_VERS = 2.0
CREATION_DATE = 2019-02-22T23:22:31
ORIGINATOR = N/A
META_START
OBJECT_NAME = N/A
OBJECT_ID = N/A
CENTER_NAME = EARTH
REF_FRAME = EME2000
TIME_SYSTEM = UTC
META_STOP
COMMENT State Vector
EPOCH = 2018-05-02T00:00:00.000000
X = 6678.000000 [km]
Y = 0.000000 [km]
Z = 0.000000 [km]
X_DOT = 0.000000 [km/s]
Y_DOT = 7.088481 [km/s]
Z_DOT = 3.072802 [km/s]
COMMENT Keplerian elements
SEMI_MAJOR_AXIS = 6678.000000 [km]
ECCENTRICITY = 0.000000
INCLINATION = 23.436363 [deg]
RA_OF_ASC_NODE = 0.000000 [deg]
ARG_OF_PERICENTER = 0.000000 [deg]
TRUE_ANOMALY = 0.000000 [deg]
COMMENT Escaping Earth
MAN_EPOCH_IGNITION = 2018-05-02T00:39:03.955092
MAN_DURATION = 0.000 [s]
MAN_DELTA_MASS = 0.000 [kg]
MAN_REF_FRAME = TNW
MAN_DV_1 = 3.456791 [km/s]
MAN_DV_2 = 0.000000 [km/s]
MAN_DV_3 = 0.000000 [km/s]
""")
planetary_step = timedelta(seconds=180)
solar_step = timedelta(hours=12)
jpl.create_frames()
central = jpl.get_body('Sun')
planets = jpl.get_body('Earth')
opm.propagator = SOIPropagator(solar_step, planetary_step, central, planets)
frames = set()
for orb in opm.iter(stop=timedelta(5)):
frames.add(orb.frame.name)
assert not frames.symmetric_difference(['Sun', 'EME2000'])
# Check if the last point is out of Earth sphere of influence
assert orb.copy(frame='EME2000', form="spherical").r > SOIPropagator.SOI['Earth'].radius
def jplfiles():
config.set('env', 'jpl', 'files', [
str(Path(__file__).parent / "data" / "jpl" / "de403_2000-2020.bsp"),
str(Path(__file__).parent / "data" / "jpl" / "pck00010.tpc"),
str(Path(__file__).parent / "data" / "jpl" / "gm_de431.tpc"),
])
jpl.create_frames()
def test_load_interplanetary(jplfiles, orbit, datafile, helper):
create_frames(until="Mars")
orbit.frame = "Mars"
data_opm = loads(datafile("opm_interplanetary"))
helper.assert_orbit(orbit, data_opm)
def test_load_oem_interplanetary(jplfiles, ephem, datafile, helper):
create_frames(until="Mars")
ephem.frame = "Mars"
data = loads(datafile("oem_interplanetary"))
helper.assert_ephem(ephem, data)
def test_dump_oem_interplanetary(jplfiles, ephem, ccsds_format, datafile,
helper):
create_frames("Mars")
ephem.frame = "Mars"
ref = datafile("oem_interplanetary")
txt = dumps(ephem, fmt=ccsds_format)
helper.assert_string(ref, txt)
def test_create_frames(jplfiles):
create_frames(until='Mars')
mars = get_frame('Mars')
assert mars.name == "Mars"
# The frame for Venus is not yet created, due to the use of the 'until' keyword in the
# create_frame call
with raises(UnknownFrameError):
get_frame("Venus")
# Create all the frames available in the .bsp files
create_frames()
venus = get_frame('Venus')
assert venus.name == "Venus"
def test_soi(jplfiles, method):
planetary_step = timedelta(seconds=180)
solar_step = timedelta(hours=12)
jpl.create_frames()
central = jpl.get_body('Sun')
planets = jpl.get_body('Earth')
if method == "numerical":
propagator = SoINumerical(solar_step, planetary_step, central, planets)
txt = opm_with_man
else:
propagator = SoIAnalytical(central, planets)
propagator.step = solar_step
txt = opm_without_man
opm = ccsds.loads(txt).as_orbit(propagator)
# d, r = [], []
frames = set()
for orb in opm.iter(stop=timedelta(5)):
frames.add(orb.frame.name)
# r.append(orb.copy(frame="EME2000", form="spherical").r)
# d.append(orb.date)
# import matplotlib.pyplot as plt
# plt.plot(d, r)
# plt.show()
assert not frames.symmetric_difference(['Sun', 'EME2000'])
# Check if the last point is out of Earth sphere of influence
assert orb.copy(frame='EME2000',
form="spherical").r > SoINumerical.SOIS['Earth'].radius
def space_phase(*argv):
"""Compute the phase of the moon or other solar system bodies
Usage:
space-phase <body> [<date>] [--graph] [--frame <frame>] [-a] [--file <file>]
Options:
<body> Body
<date> Date to compute the moon phase at [default: now]
(format %Y-%m-%dT%H:%M:%S)
-g, --graph Display the moon phase
-a, --analytical Use analytical model instead of JPL files
--file <file> File
"""
import sys
from .clock import Date
from .utils import docopt, parse_date
from .station import StationDb
args = docopt(space_phase.__doc__)
if args["<date>"] is None:
args["<date>"] = "now"
try:
date = parse_date(args["<date>"])
except ValueError as e:
print(e, file=sys.stderr)
sys.exit(1)
StationDb.list()
body = args["<body>"]
if body == "Moon":
center = "EME2000"
second = "Sun"
else:
center = body
body = "Sun"
second = "Earth"
if args["--analytical"] and body.lower() == "moon":
first = solar.get_body(body).propagate(date)
second = solar.get_body(second).propagate(first.date)
src = "analytical"
else:
src = "JPL"
if args["--analytical"]:
log.warning(
"No analytical model available for '{}'. Switching to JPL source"
.format(body))
jpl.create_frames()
first = jpl.get_orbit(body, date)
second = jpl.get_orbit(second, first.date)
if body == "Moon":
phase = compute_phase(first, second, center)
else:
phase = np.pi - compute_phase(first, second, center)
body = center
illumin = illumination(phase)
log.debug("Computing {} phase using source '{}'".format(body, src))
log.info("{} at {:%Y-%m-%dT%H:%M:%S} : {:0.2f}%".format(
body, date, illumin * 100))
if args["--graph"] or args["--file"]:
draw_phase(date, phase, body=args["<body>"], filepath=args["--file"])
def space_planet(*args):
"""Compute position of a planet of the solar system and its major moons
Usage:
space-planet
space-planet fetch
space-planet <planet>... [options]
Options:
fetch Retrieve .bsp file
<planet> Names of the planet to compute the ephemeris of. If
absent, list all bodies available
-f, --frame <frame> Frame in which to display the ephemeris to
[default: EME2000]
-d, --date <date> Start date of the ephem (%Y-%m-%d) [default: midnight]
-r, --range <days> Duration of extrapolation [default: 3d]
-s, --step <step> Step size of the ephemeris. [default: 60m]
-a, --analytical Force analytical model instead of .bsp files
Example:
space-planet Mars # Position of Mars in EME2000
space-planet Moon -f Phobos # Position of the moon as seen from Phobos
This command relies on .bsp files, parsed by the incredible jplephem lib.
Bsp file can be retrieved at
https://naif.jpl.nasa.gov/pub/naif/generic_kernels/spk/planets/
Files examples:
de432s.bsp Moon, Sun, Mercury, Venus and main bodies barycentre
mar097.bsp Mars, Phobos and Deimos
jup310.bsp Jupiter and its major moons
sat360xl.bsp Saturn and its major moons
The 'beyond.env.jpl' config variable must be set to a list of bsp files
paths. See beyond documentation about JPL files:
http://beyond.readthedocs.io/en/latest/api/env.html#module-beyond.env.jpl
If no .bsp file is provided, the command falls back to analytical methods
for Moon and Sun. Other bodies are not provided.
"""
import requests
from logging import getLogger
log = getLogger(__name__)
args = docopt(space_planet.__doc__)
if args["fetch"]:
folder = ws.folder / "jpl"
if not folder.exists():
folder.mkdir()
naif = "https://naif.jpl.nasa.gov/pub/naif/generic_kernels/"
baseurl = {
"de403_2000-2020.bsp":
naif + "spk/planets/a_old_versions/", # Data until 2020-01-01
"de430.bsp": naif + "spk/planets/",
"de432s.bsp": naif + "spk/planets/",
"de435.bsp": naif + "spk/planets/",
"jup310.bsp": naif + "spk/satellites/",
"sat360xl.bsp": naif + "spk/satellites/",
"mar097.bsp": naif + "spk/satellites/",
"pck00010.tpc": naif + "pck/",
"gm_de431.tpc": naif + "pck/",
}
success = []
filelist = ws.config.get("beyond",
"env",
"jpl",
fallback="de403_2000-2020.bsp")
if not isinstance(filelist, list):
filelist = [filelist]
for filepath in filelist:
filepath = Path(filepath)
if not filepath.is_absolute():
filepath = folder / filepath
if not filepath.exists():
url = baseurl.get(filepath.name, "") + str(filepath.name)
log.info("Fetching {}".format(filepath.name))
log.debug(url)
try:
r = requests.get(url, stream=True)
except requests.exceptions.ConnectionError as e:
log.error(e)
else:
try:
r.raise_for_status()
except requests.exceptions.HTTPError as e:
log.error("{} {}".format(filepath.name, e))
else:
total = int(r.headers.get("content-length", 0))
size = 0
with filepath.open("bw") as fp:
for chunk in r.iter_content(chunk_size=1024):
fp.write(chunk)
if total:
size += len(chunk)
print(
"\r> {:6.2f} % {} / {}".format(
100 * size / total,
humanize(size),
humanize(total),
),
end="",
)
if total:
print("\r", " " * 40, end="\r")
success.append(str(filepath.absolute()))
log.debug("Adding {} to the list of jpl files".format(
filepath.name))
else:
success.append(str(filepath.absolute()))
log.info("File {} already downloaded".format(filepath.name))
# Adding the file to the list and saving the new state of configuration
if success:
ws.config.set("beyond", "env", "jpl", success)
ws.config.save()
elif args["<planet>"]:
try:
date = parse_date(args["--date"], fmt="date")
stop = parse_timedelta(args["--range"])
step = parse_timedelta(args["--step"])
except ValueError as e:
print(e, file=sys.stderr)
sys.exit(1)
if not args["--analytical"]:
# Create all frames from .bsp files, if they are available
try:
jpl.create_frames()
except jpl.JplError:
jpl_error = True
else:
jpl_error = False
# Create all frames from stations database
StationDb.list()
try:
frame = get_frame(args["--frame"])
except UnknownFrameError as e:
print(e, file=sys.stderr)
sys.exit(1)
# Computation
ephems = []
for body_name in args["<planet>"]:
try:
if args["--analytical"] or jpl_error:
body = solar.get_body(body_name).propagate(date)
else:
body = jpl.get_orbit(body_name, date)
except UnknownBodyError as e:
print(e, file=sys.stderr)
sys.exit(1)
ephem = body.ephem(start=date, stop=stop, step=step)
ephem.frame = frame
ephem.name = body_name
ephems.append(ephem)
else:
print(ccsds.dumps(ephems))
else:
print("List of all available bodies")
try:
jpl.create_frames()
txt = recurse(jpl.get_frame("Earth").center.node, set())
except jpl.JplError as e:
print(" Sun")
print(" Moon")
else:
print(txt)
import matplotlib.pyplot as plt
from beyond.dates import Date
from beyond.env import jpl
from beyond.frames import create_station
from beyond.config import config
# Load the ".bsp" file
config.update({"env": {"jpl": ["/home/jules/.space/jpl/jup310.bsp"]}})
date = Date.now()
# Definition of the location of observation
station = create_station('TLS', (43.428889, 1.497778, 178.0))
jpl.create_frames()
# Retrieve Jupiter and its moons state-vectors
jupiter = jpl.get_orbit('Jupiter', date)
io = jpl.get_orbit('Io', date)
europa = jpl.get_orbit('Europa', date)
ganymede = jpl.get_orbit('Ganymede', date)
callisto = jpl.get_orbit('Callisto', date)
# Convert them to the observer frame
jupiter.frame = station
io.frame = station
europa.frame = station
ganymede.frame = station
callisto.frame = station
