def load_kernel(filename):
"""Load the named kernel into memory.
The kernel must be in the current directory, or in `_kernel_path`.
No-op if the kernel is already loaded.
Parameters
----------
filename : string
Returns
-------
None
Raises
------
`OSError` if the file is not found.
"""
import os.path
global _kernel_path
if not os.path.exists(filename):
filename = os.path.join(_kernel_path, filename)
if not os.path.exists(filename):
raise OSError("{} not found".format(filename))
if spice.kinfo(filename) is None:
spice.furnsh(filename)
def compute_posvels(self, ephem="DE405", planets=False):
"""Compute positions and velocities of observatory and Earth.
Compute the positions and velocities of the observatory (wrt
the Geocenter) and the center of the Earth (referenced to the
SSB) for each TOA. The JPL solar system ephemeris can be set
using the 'ephem' parameter. The positions and velocities are
set with PosVel class instances which have astropy units.
"""
# Load the appropriate JPL ephemeris
load_kernels()
pth = os.path.join(pintdir, "datafiles")
ephem_file = os.path.join(pth, "%s.bsp"%ephem.lower())
spice.furnsh(ephem_file)
log.info("Loaded ephemeris from %s" % ephem_file)
j2000 = time.Time('2000-01-01 12:00:00', scale='utc')
j2000_mjd = utils.time_to_mjd_mpf(j2000)
for toa in self.toas:
xyz = observatories[toa.obs].xyz
toa.obs_pvs = erfautils.topo_posvels(xyz, toa)
# SPICE expects ephemeris time to be in sec past J2000 TDB
# We need to figure out how to get the correct time...
et = (toa.mjd.TDB - j2000_mjd) * SECS_PER_DAY
# SSB to observatory position/velocity:
toa.earth_pvs = objPosVel("EARTH", "SSB", et)
toa.pvs = toa.obs_pvs + toa.earth_pvs
# Obs to Sun PV:
toa.obs_sun_pvs = objPosVel("SUN", "EARTH", et) - toa.obs_pvs
if planets:
for p in ('jupiter', 'saturn', 'venus', 'uranus'):
pv = objPosVel(p.upper()+" BARYCENTER",
"EARTH", et) - toa.obs_pvs
setattr(toa, 'obs_'+p+'_pvs', pv)
def get_v_sun(kernelMetaFile, utcStartTime):
'''
compute radial component of CG towards/away from sun for given utcTime.
v_sun: velocity component on the comet-sun-line.
'''
spice.furnsh(kernelMetaFile)
et = spice.str2et(utcStartTime)
state, lightTime = spice.spkezr("CHURYUMOV-GERASIMENKO",
et, "J2000", "NONE", "SUN")
x = state[0]
y = state[1]
z = state[2]
vx = state[3]
vy = state[4]
vz = state[5]
r_length = np.sqrt(x**2 + y**2 + z**2)
r_hat = np.zeros(3)
v = np.zeros(3)
r_hat[0] = x / r_length
r_hat[1] = y / r_length
r_hat[2] = z / r_length
v[0] = r_hat[0] * vx
v[1] = r_hat[1] * vy
v[2] = r_hat[2] * vz
v_sun = v[0] + v[1] + v[2]
return v_sun
def setUp(self):
mydir = os.path.dirname(__file__)
self.kernels = [
os.path.join(mydir, i.strip()) for i in """
### Lines in this string that start with '#' are comments
### The other lines in this string are paths to kernels,
### relative to the parent directory of this Python script, __file__
###
kernels/naif0010.tls
kernels/smap_v00.tf
kernels/pck00009.tpc
kernels/spk_drm239_WithBurn-full.bsp
kernels/smap_test.bsp
###
### kernels/SMAP_ref_150529_180529.bsp
###
### That commented SMAP SPK kernel, or one like it, should be under this URL:
###
### http://naif.jpl.nasa.gov/pub/naif/SMAP/kernels/spk/
###
###
""".strip().split('\n') if i[0] != '#'
]
### Load default kernels (string variable "kernels" above")
for kernel in self.kernels:
spice.furnsh(kernel)
def setUp(self):
### Load default kernels
mydir = os.path.dirname(__file__)
self.kernels = [ os.path.join( mydir,i.strip()) for i in
"""
kernels/naif0010.tls
kernels/spk_drm239_WithBurn-full.bsp
""".strip().split('\n') ]
for kernel in self.kernels: spice.furnsh( kernel )
def setUp(self):
### Load default kernels
mydir = os.path.dirname(__file__)
self.kernels = [
os.path.join(mydir, i.strip()) for i in """
kernels/naif0010.tls
kernels/spk_drm239_WithBurn-full.bsp
""".strip().split('\n')
]
for kernel in self.kernels:
spice.furnsh(kernel)
def loadKernel(filenames):
"""
loadKernel(filenames)
Read SPICE kernels in filenames (including full paths)
"""
if type(filenames) is str:
spice.furnsh(filenames)
else:
for name in filenames:
spice.furnsh(name)
def transform(fname, metadata=False):
"""
This function reads a Mission Analysis Orbit file and performs a matrix
transformation on it. Currently only from the Mercury Equatorial frame to
the Earth Equatorial frame.
:param fname: The path to the orbit file.
:type fname: str.
:param metadata: Flag to return the metadata dictionary
:type state: bool.
:returns: numpy.array -- the return code.
"""
furnsh("/Users/jmcaulif/Code/naif/generic/lsk/naif0010.tls")
logging.basicConfig(level=logging.INFO)
mdata = {}
data = {}
with open(fname, "r") as fh:
for line in fh:
t, x, y, z, vx, vy, vz = [float(x) for x in line.split()]
T = np.array(
[
[0.98159386604468, 0.19098031873327, 0.0],
[-0.16775718426422, 0.86223242348167, 0.47792549108063],
[0.09127436261733, -0.46912873047114, 0.87840037851502],
]
)
Tinv = linalg.inv(T)
r = np.array([[x, y, z]])
v = np.array([[vx, vy, vz]])
r_new = Tinv.dot(r.T).T
v_new = Tinv.dot(v.T).T
x, y, z = r_new[0]
vx, vy, vz = v_new[0]
t = et2utc(t * 86400, "isoc", 2)
print("{} {:9.2f} {:9.2f} {:9.2f} {:9.6f} {:9.6f} {:9.6f}".format(t, x, y, z, vx, vy, vz))
fh.close()
if metadata:
return data, mdata
else:
return data
def setUp(self):
### Variables for comparison
self.Ddtp = ( 1, 'N', )
self.Idtp = ( 2, 'N', )
self.Cdtp = ( 3, 'C', )
self.var399 = ( 3, ( 1000.0, 2000.0, 3000.0, ), )
self.var99 = (4, ( 1099.5, 2099.25, 3099.125, 4099.0625, ), )
### Load the kernel
spice.furnsh( __file__ )
### Load a private name/code pair
spice.boddef( 'MYBOD', 99 )
def setUp(self):
### Load the kernel
spice.furnsh( __file__ )
### Convert MPC constants to CONICS_C elements
ison = MPC_ISON_C_2012_S1()
self.rpKM = spice.convrt( ison.qAU, 'AU', 'KM')
self.ecc = ison.e
self.incRAD = spice.convrt( ison.InclDEG, 'DEGREES', 'RADIANS')
self.lnodeRAD = spice.convrt( ison.NodeDEG, 'DEGREES', 'RADIANS')
self.argpRAD = spice.convrt( ison.PeriDEG, 'DEGREES', 'RADIANS')
self.m0RAD = spice.convrt( ison.M0, 'DEGREES', 'RADIANS')
self.t0 = spice.str2et( ison.T0_TDT[0] ) + spice.convrt( ison.T0_TDT[1], 'DAYS', 'SECONDS' )
self.mu = ison.MuM3S2 * 1e-9
self.elts = ( self.rpKM, self.ecc, self.incRAD, self.lnodeRAD, self.argpRAD, self.m0RAD, self.t0, self.mu )
self.ditime = spice.utc2et( '2013-01-16 12:00:00' )
def __init__(self, argv=None, verbose=True):
rf = readtemps.__file__
if rf[-4:-1] == '.py': rf = rf[:-1]
spice.furnsh(rf) ### metakernel
if argv and os.path.isfile(argv[0]):
fArg = argv[0]
fName = fArg
else:
fArg = sys.stdin
fName = 'STDIN'
if verbose:
print("Reading DI temperature data from %s ..." % (fName, ))
tts = readtemps.readtemps(fArg)
self.dii = readtemps.DiScuTemps(tts, which=-70)
self.dif = readtemps.DiScuTemps(tts, which=-140)
def __init__(self,argv=None,verbose=True):
rf = readtemps.__file__
if rf[-4:-1]=='.py': rf = rf[:-1]
spice.furnsh( rf ) ### metakernel
if argv and os.path.isfile(argv[0]):
fArg = argv[0]
fName = fArg
else:
fArg = sys.stdin
fName = 'STDIN'
if verbose:
print( "Reading DI temperature data from %s ..."%(fName,) )
tts = readtemps.readtemps( fArg )
self.dii = readtemps.DiScuTemps( tts, which=-70 )
self.dif = readtemps.DiScuTemps( tts, which=-140 )
def setUp(self):
mydir = os.path.dirname(__file__)
self.kernels = [ os.path.join( mydir, i.strip() ) for i in """
### Lines in this string that start with '#' are comments
### The other lines in this string are paths to kernels,
### relative to the parent directory of this Python script, __file__
###
kernels/naif0010.tls
kernels/smap_v00.tf
kernels/pck00009.tpc
kernels/spk_drm239_WithBurn-full.bsp
kernels/smap_test.bsp
###
### kernels/SMAP_ref_150529_180529.bsp
###
### That commented SMAP SPK kernel, or one like it, should be under this URL:
###
### http://naif.jpl.nasa.gov/pub/naif/SMAP/kernels/spk/
###
###
""".strip().split('\n') if i[0]!='#' ]
### Load default kernels (string variable "kernels" above")
for kernel in self.kernels: spice.furnsh( kernel )
def load_kernels(ephem="DE421"):
"""Ensure all kernels are loaded.
State is kept in the kernels_loaded module-global variable, so that this
function can (should!) be called any time the user anticipates needing
SPICE kernels.
"""
global kernels_loaded
if not kernels_loaded:
spice.furnsh(os.path.join(pintdir, "datafiles/pck00010.tpc"))
log.info("SPICE loaded planetary constants.")
spice.furnsh(os.path.join(pintdir, "datafiles/naif0010.tls"))
log.info("SPICE loaded leap seconds.")
spice.furnsh(os.path.join(pintdir,
"datafiles/earth_latest_high_prec.bpc"))
log.info("SPICE loaded Earth rotation parameters.")
spice.furnsh(os.path.join(pintdir, "datafiles/%s.bsp" % ephem.lower()))
log.info("SPICE loaded DE%s Planetary Ephemeris." % ephem[2:])
kernels_loaded = True
def load_kernels(ephem="DE421"):
"""Ensure all kernels are loaded.
State is kept in the kernels_loaded module-global variable, so that this
function can (should!) be called any time the user anticipates needing
SPICE kernels.
"""
global kernels_loaded
if not kernels_loaded:
spice.furnsh(datapath("pck00010.tpc"))
log.info("SPICE loaded planetary constants.")
try:
spice.furnsh(datapath("naif0012.tls"))
except:
log.error("Download updated leap second file (naif0012.tls)" +
" using download script in $PINT/datafiles directory.")
sys.exit()
log.info("SPICE loaded leap seconds.")
spice.furnsh(datapath("earth_latest_high_prec.bpc"))
log.info("SPICE loaded Earth rotation parameters.")
spice.furnsh(datapath("%s.bsp" % ephem.lower()))
log.info("SPICE loaded DE%s Planetary Ephemeris." % ephem[2:])
kernels_loaded = True
def load_kernels(ephem="DE421"):
"""Ensure all kernels are loaded.
State is kept in the kernels_loaded module-global variable, so that this
function can (should!) be called any time the user anticipates needing
SPICE kernels.
"""
global kernels_loaded
if not kernels_loaded:
spice.furnsh(datapath("pck00010.tpc"))
log.info("SPICE loaded planetary constants.")
try:
spice.furnsh(datapath("naif0012.tls"))
except:
log.error("Download updated leap second file (naif0012.tls)"+
" using download script in $PINT/datafiles directory.")
sys.exit()
log.info("SPICE loaded leap seconds.")
spice.furnsh(datapath("earth_latest_high_prec.bpc"))
log.info("SPICE loaded Earth rotation parameters.")
spice.furnsh(datapath("%s.bsp" % ephem.lower()))
log.info("SPICE loaded DE%s Planetary Ephemeris." % ephem[2:])
kernels_loaded = True
\begindata KERNELS_TO_LOAD = ( 'kernels/naif0010.tls' 'kernels/dif_sclkscet_00015_science.tsc' 'kernels/dii_sclkscet_00008_science_btc.tsc' ) ETTOIPSEUDO = @2005-07-04T05:44:34.2 \begintext ======================================================================== """ import spice import pprint spice.furnsh(__file__) ### Get UTC and SCLKs of TOI as strings utctoi = '2005-07-04T05:44:34.2' diitoi = '1/0173727875.105' diftoi = '1/0173727702.218' ### N.B. Old code: pseudo-ET to non-leapsecond-corrected calendar time ###utctoi = spice.etcal( spice.gdpool( 'ETTOIPSEUDO', 0, 1 )[1] ) ### Convert UTC and SCLKs strings to ETs toiet = spice.utc2et( utctoi ) diiet = spice.scs2e( -70, diitoi ) difet = spice.scs2e( -140, diftoi ) ### Output __doc__ string
def _gatherorbitdata(delta="1d", scale=15, verbose=False):
# print("Building orbit for planets with SPICE...")
spice.kclear()
# Load the kernels that this program requires.
this_dir = os.path.dirname(os.path.realpath(__file__))
spice.furnsh(os.path.join(this_dir, 'epys.mk'))
# convert starting epoch to ET
et0 = spice.str2et('2024/05/07 00:00')
rate = 24 * 2 # Every 30 mins
days = [(et0 + (day * (86400 / rate))) for day in range(366 * rate)]
# internal variables and constants
planets = ("MERCURY", "VENUS", "EARTH")
AU = consts.AU / 1000. # AU [km]
argps = []
argpxys = []
xyvecs = []
nuvecs = []
for planet in planets:
# print(" > {}".format(planet))
dates = []
rvec = [] # vector of centric radii
xyvec = [] # vector of (x,y) coordinates
nuvec = [] # vector of nu (True Anomaly) values
incvec = [] # vector of inclination values
for et in days:
if verbose:
print('ET Seconds Past J2000: {}'.format(et))
# Compute the apparent state of MERCURY as seen from
# the SUN in ECLIPJ2000
starg, ltime = spice.spkezr(planet, et, 'ECLIPJ2000',
'NONE', 'SUN')
x, y, z, vx, vy, vz = [el / AU * scale for el in starg]
r = math.sqrt(x ** 2 + y ** 2 + z ** 2)
if verbose:
print('\nApparent state of MERCURY as seen from',
' Sun in the J2000:')
print(' X = {:10.4f} km (LT+S)'.format(x))
print(' Y = {:10.4f} km (LT+S)'.format(y))
print(' Z = {:10.4f} km (LT+S)'.format(z))
print('VX = {:10.4f} km/s (LT+S)'.format(vx))
print('VY = {:10.4f} km/s (LT+S)'.format(vy))
print('VZ = {:10.4f} km/s (LT+S)'.format(vz))
# calculate orbital elements from the starg state vector
elts = spice.oscelt(starg, et, planetmu('Sun'))
# define a solver for Kepler's equation
ks = pyasl.MarkleyKESolver()
# solve for the Eccentric Anomaly (E) with the
# Mean Anomaly (M = elts[5]) and the
# Eccentricity (ecc = elts[1])
E = ks.getE(elts[5], elts[1])
# calculate the True Anomaly (nu) from E and ecc (elts[1])
nuarg1 = math.sqrt(1 - elts[1]) * math.cos(E / 2)
nuarg2 = math.sqrt(1 + elts[1]) * math.sin(E / 2)
# atan2 in python needs the arguments as (y,x)
# rather than (x,y) ...?
nu = 2 * math.atan2(nuarg2, nuarg1)
rvec.append(r) # append r for each day
xyvec.append((x, y)) # append (x,y) coords for each day
nuvec.append(nu) # append True anomaly for each day
# build date in ISO format
date = '{} {}'.format(spice.et2utc(et, 'ISOC', 0).split('T')[0],
spice.et2utc(et, 'ISOC', 0).split('T')[1])
dates.append(date) # append date for each day
incvec.append(elts[2]) # append inc. for each day (rads)
# print(date, nu * spice.dpr(), x, y, z, r, elts[0])
# for this planet find the argument of pericenter (argp):
# find the index of the min. r value for calculated range.
argpi = rvec.index(min(rvec))
# calculate argp x and y values and argp using atan2
argpxy = (xyvec[argpi][0], xyvec[argpi][1] * math.cos(incvec[argpi]))
argp = math.degrees(math.atan2(argpxy[1], argpxy[0]))
argpxys.append(argpxy) # append argp (x,y) coords.
argps.append(argp) # append argp
xyvecs.append(xyvec) # append (x,y) coords. vector
nuvecs.append(nuvec) # append true anomaly vector
spice.kclear()
return days, dates, xyvecs, argps, argpxys, nuvecs
if nPixelsX > 1:
Dx = Lx / (nPixelsX - 1)
else:
Dx = Lx
if nPixelsY > 1:
Dy = Ly / (nPixelsY - 1)
else:
Dy = Ly
if iPointingCase == spice_:
#################################################
# get rosetta coordinates from spice
#################################################
spice.furnsh(StringKernelMetaFile)
Et = spice.str2et(StringUtcStartTime)
#R = spice.pxform("ROS_SPACECRAFT", "67P/C-G_CSO", Et) # create rotation matrix R to go from instrument reference frame to CSO
if ((iDim == 2) or (iDim == 1)):
rRosetta, lightTime = spice.spkpos("ROSETTA", Et, "67P/C-G_CSO", "NONE", "CHURYUMOV-GERASIMENKO") # s/c coordinates in CSO frame of reference
R = spice.pxform(InstrumentFrame, "67P/C-G_CSO", Et) # create rotation matrix R to go from instrument reference frame to CSO
elif iDim == 3:
print "iDim = 3"
rRosetta, lightTime = spice.spkpos("ROSETTA", Et, "67P/C-G_CK", "NONE", "CHURYUMOV-GERASIMENKO") # s/c coordinates in CSO frame of reference
R = spice.pxform(InstrumentFrame, "67P/C-G_CK", Et)
# do 3d stuff from here?
rSun, lt = spice.spkpos("SUN", Et, "67P/C-G_CK", "NONE", "CHURYUMOV-GERASIMENKO")
rSun = np.array(rSun)
rSun = rSun / np.sqrt((rSun**2).sum())
# quick and dirty fix --> andre needs to define instrument object for all instruments!
try:
'naif0010.tls' 'pck00010.tpc' ) ETLO = @1900-01-01T12:00:00 ETHI = @2099-12-31T12:00:00 \begintext """ ### https://github.com/rca/PySPICE , or ### https://github.com/drbitboy/PySPICE import spice dot = '.' ### Load kernels using this source as SPICE meta-kernel spice.furnsh(dot.join(__file__.split(dot)[:-1] + ['py'])) ### Set arguments for Geometry Finder call ### - Times when VENUS crosses equator of Jupiter (Zjup = 0) ### - abcorr='LT+S' - correct for light time and stellar aberration ### - Timestep of 10 days (spice.spd() = seconds per day) ### - nintvls - 450 seems to work here target, frame, abcorr, obsrvr = 'VENUS', 'IAU_JUPITER', 'LT+S', 'JUPITER' relate, crdsys, coord = '=', 'RECTANGULAR', 'Z' refval, adjust, step, nintvls = 0.0, 0.0, spice.spd()*10, 450 ### Range of ETs to test etlo,ethi = [spice.gdpool(s,0,1)[1] for s in 'ETLO ETHI'.split()] cnfine = spice.wninsd( etlo, ethi, spice.objects.Cell(spice.DataType.SPICE_DP,2)) ### Create DP window to receive results
def test_example_loading():
currentdir = os.getcwd()
os.chdir(kernelpath)
spice.furnsh("ck/moc42_2010100_2010100_v01.bc")
spice.furnsh("fk/lro_frames_2012255_v02.tf")
spice.furnsh("fk/lro_dlre_frames_2010132_v04.tf")
spice.furnsh("ick/lrodv_2010090_2010121_v01.bc")
spice.furnsh("lsk/naif0010.tls")
spice.furnsh('sclk/lro_clkcor_2010096_v00.tsc')
spice.furnsh("spk/fdf29_2010100_2010101_n01.bsp")
spice.furnsh('./planet_spk/de421.bsp')
utc = dt.strptime('2010100 05', '%Y%j %H').isoformat()
et = spice.utc2et(utc)
t = spice.spkpos('sun', et, 'LRO_DLRE_SCT_REF', 'lt+s', 'lro')
print(t)
answer = ((-63972935.85033857, -55036272.7848299, 123524941.9877458),
499.009424105693)
for i, j in zip(t[0], answer[0]):
assert_equals(round(i, 3), round(j, 3))
os.chdir(currentdir)
ETTOI-108d is TOI(tparse('2005-07-04T05:44:34.2')) + 64.184s - 108d
Alternate DII SCLK kernels:
'$K/dii_sclkscet_00008_science.tsc'
'$K/dii_sclkscet_00008.tsc'
========================================================================
"""
import os
import sys
import spice
import pprint
import timediffs
import matplotlib.pyplot as plt
### Load meta-kernel, get start time ETTOI-108d
spice.furnsh(__file__)
### Override any kernels with sys.argv[1:]
for sclkk in sys.argv[1:]: spice.furnsh(sclkk)
### Get TEXT kernel list
ks = '\n'.join([os.path.basename(spice.kdata(i,'text')[0]) for i in range(spice.ktotal('TEXT'))])
### Get TOI-108d, set up for one point per day for 108d
et = spice.gdpool( 'ETTOI-108d', 0, 1 )[1]
spanDays = 108
diffs = range(spanDays+1)
doys = [ i+185-spanDays for i in diffs ]
### Spacecraft IDs to plot
scids = [-70,-140]
KERNELS_TO_LOAD = (
'$K/naif0010.tls'
'$K/dif_sclkscet_00015_science.tsc'
'$K/dii_sclkscet_00008_science_btc.tsc'
)
ETSTART = @2005-06-19T05:45:38.384
\begintext
N.B. ETSTART is TOI(tparse('2005-07-04T05:44:34.2')) + 64.184s - 15d
========================================================================
"""
import spice
import pprint
print(__doc__.replace('\b', '\\b'))
spice.furnsh(__file__)
### ET of TOI-15d
found, et = spice.gdpool('ETSTART', 0, 1)
### S/C IDs
scids = [-70, -140]
n = len(scids)
rn = range(len(scids))
### for 15 days leading up to TOI
for i in range(16):
### Convert
### - ET to ISO Calendar and DOY UTCs
### - ET to DII and DIF SCLKs
### - SCLKs to encoded SCLK, scale by 1/256 to get s past J2k epoch
from __future__ import division, print_function
import spice
import os
from diviner.file_utils import kernelpath
from datetime import datetime as dt
from numpy import degrees, arccos
currentdir = os.getcwd()
os.chdir(kernelpath)
spice.furnsh("fk/lro_frames_2012255_v02.tf")
spice.furnsh("fk/lro_dlre_frames_2010132_v04.tf")
spice.furnsh("ick/lrodv_2010090_2010121_v01.bc")
spice.furnsh("lsk/naif0010.tls")
spice.furnsh('sclk/lro_clkcor_2009182_v00.tsc')
spice.furnsh("spk/fdf29_2010100_2010101_n01.bsp")
spice.furnsh('./planet_spk/de421.bsp')
# spice.furnsh("ck/moc42_2010100_2010100_v01.bc")
time = dt(2009,6,24,0,1,8)
print("Testing for time ", time, '\nIn kernel-time: ', time.strftime("%Y%j"),
'plus {0} hours.'.format(time.hour))
et = spice.utc2et(time.isoformat())
# ckernels = ['moc42_2010100_2010100_v01.bc', 'moc42_2010100_2010101_v01.bc',
# 'moc42_2010100_2010101_v02.bc']
ckernels = ['moc42_2009174_2009175_v01.bc','moc42_2009175_2009176_v02.bc']
for ck in ckernels:
spice.furnsh('ck/'+ck)
print("Loading {0}".format(ck))
def planetsplot(userdates=None, delta="1d", master_scale=15, demo=False,
showplots=False):
"""
... explain what this does...
"""
outdir = './sample_data/output'
# if demo:
# shutil.rmtree(outdir)
# os.makedirs(outdir)
# else:
# if not os.path.exists(outdir):
# os.makedirs(outdir)
# else:
# print('\n Uh-oh! The directory {} already exists.'.format(
# outdir))
# if yesno(' Do you want to replace it?'):
# shutil.rmtree(outdir)
# os.makedirs(outdir)
# else:
# return
orbitdata = _gatherorbitdata(delta=delta, scale=master_scale)
ets, dates, orbits, argps, argpxys, nus = orbitdata
if userdates is None:
userdates = dates
if showplots:
plt.subplot(1, 1, 1)
for xy in orbits:
plt.plot([x[0] for x in xy], [y[1] for y in xy],
'rx', label='SPICE')
for xy in argpxys:
plt.plot(xy[0], xy[1], 'go')
plt.show()
if len(orbits[0]) == len(dates) == len(ets):
# This rotation will put the Hermean perihelion on the X-axis.
rotang = -argps[0]
# Load the kernels that this program requires.
spice.kclear()
this_dir = os.path.dirname(os.path.realpath(__file__))
spice.furnsh(os.path.join(this_dir, 'epys.mk'))
output_files = []
# A graphic will be created for each 'date' in 'userdates':
for date in userdates:
# get the position-index of the 'et' in the 'orbitdata' list
# of 'ets' that is closest to the 'date' in the 'userdates'
et = spice.str2et(date)
dx = ets.index(getclosest(ets, et))
# -- Outer frame -------------------------------------------------
# Opacity of degree frame and Venus graphic
frame_op = 0.8
# Process calendar time strings
date = '{} {}'.format(spice.et2utc(et, 'ISOC', 0).split('T')[0],
spice.et2utc(et, 'ISOC', 0).split('T')[1])
edate, etime = date.split()
eyear = "{}".format(edate.split('-')[0])
emonth = "{0:02d}".format(int(edate.split('-')[1]))
eday = "{0:02d}".format(int(edate.split('-')[2]))
epoch = "{}/{}/{}".format(eday, emonth, eyear)
ep_name = "{}{}{}_{}".format(eyear, emonth, eday,
etime.replace(':', ''))
frame = _outerframe(epoch, frmSize=master_scale, frm_op=frame_op)
# -- First Point of Aires ----------------------------------------
# merc_loan = 48.331
# merc_argp = 29.124
arend = svg.make_marker("fopa_arrowend", "arrow_end",
fill_opacity=0.4)
x1, y1 = 10, 0
x2, y2 = master_scale * 1.3, 0
fpoa = svg.Line(x1, y1, x2, y2, stroke_width=".4pt",
stroke_opacity=0.4, arrow_end=arend)
xp = (x2 * math.cos(math.radians(rotang)) -
y2 * math.sin(math.radians(rotang)))
yp = (x2 * math.sin(math.radians(rotang)) +
y2 * math.cos(math.radians(rotang)))
fpoa_text = svg.Text(xp + 6.5, yp - 1.0, "First Point of Aries",
font_size=3, opacity=0.75)
fpoa = svg.Fig(svg.Fig(fpoa, trans=svg.rotate(rotang, 0, 0)),
fpoa_text)
# -- Some containers ---------------------------------------------
orbs = []
circles = []
defs = svg.SVG("defs")
# -- Orbit circles -----------------------------------------------
# Build the SVG for each orbit.
for orbit in orbits:
if orbits.index(orbit) == 1:
orbit_op = 0.4
else:
orbit_op = 1.0
# Mercury's orbit will have perihelion on the X-axis
circles.append(svg.Fig(svg.Poly(orbit, stroke_width=".25pt",
stroke_opacity=orbit_op),
trans=svg.rotate(rotang, 0, 0)))
# -- Planet orbs -------------------------------------------------
points = [orbits[0][dx], orbits[1][dx], orbits[2][dx]]
# Build the planet orb for each planet for this chart.
for point in points:
# Planetary inputs ...
if points.index(point) == 0:
name = "MERCURY"
nu = math.degrees(math.atan2(point[1], point[0])) + rotang
if nu < 0:
nu = nu + 360
# print(nu, nu-rotang, rotang)
nu = "{0:03d}".format(int(nu))
if points.index(point) == 1:
name = "VENUS"
if points.index(point) == 2:
name = "EARTH"
# point_r = [x/AU for x in point]
orb, grad = _planetdiag(name, point, rotang)
orbs.append(orb)
defs.append(grad)
# -- Build final figure ------------------------------------------
wa = master_scale * 1.5
svgout = svg.Fig(fpoa, frame,
circles[0], circles[1], circles[2],
orbs[0], orbs[1], orbs[2]
).SVG(svg.window(-wa, wa, -wa, wa))
svgout.prepend(defs)
out_path = os.path.join(outdir,
"merc_orbit_plot_{}_{}.svg".format(
ep_name, nu))
svgout.save(out_path)
output_files.append(out_path)
spice.kclear()
return output_files
else:
# You'll jump to hear if the epochs for all 3 planets are not equal.
print("There is an epoch error between the planet time values...")
def test_horizons(self):
import horizons
target = 'C/2013 S1'
target = 'C/2011 L4'
spkFilename,spiceId,status = horizons.gomain(target)
spice.furnsh( spkFilename )
self.kernels += [spkFilename]
target_ = '_'.join( target.split() )
et0 = spice.utc2et( '2013-01-10T12:00:00' )
ls2au = spice.convrt( spice.clight(), 'KM', 'AU' )
dpr = spice.dpr()
spd = spice.spd()
deltatime = None
while deltatime is None or abs(deltatime) > 5e-7:
stS2I,lsS2I = spice.spkgeo( spiceId, et0, 'J2000', 10 )
posn, veloc = stS2I[:3], stS2I[3:]
deltatime = - spice.vdot( posn, veloc ) / spice.vdot( veloc, veloc )
et0 += deltatime
valarrs = [ ]
print( (deltatime,spice.et2utc(et0,'ISOC',3),) )
deltatime = 1.0
sixmonths = spice.pi() * 1e7
while deltatime < sixmonths:
for pmdet in (-deltatime,deltatime):
et = et0 + pmdet
utc = spice.et2utc(et,'ISOC',1)
stD2I,lsD2I = spice.spkgeo( spiceId, et, 'J2000', -140)
stI2S,lsI2S = spice.spkgeo( 10, et, 'J2000', spiceId )
stD2S,lsD2S = spice.spkgeo( 10, et, 'J2000', -140 )
rD2I, rI2S = [ ls * ls2au for ls in [lsD2I,lsI2S] ]
aDIS, aSDI = [ ang * dpr for ang in
[ spice.vsep( spice.vminus(stD2I[:3]), stI2S[:-3] )
, spice.vsep( stD2S[:3], stD2I[:-3] )
]
]
valarrs += [ (et,pmdet,rD2I,rI2S,aDIS,aSDI,utc,) ]
deltatime *= 1.2
valarrs.sort()
for valarr in valarrs:
print( '%12.1f %9.3f %9.3f %7.2f %7.2f %s' % valarr[1:] )
days = [i[1]/spd for i in valarrs]
titles = [ i % (target_,) for i in """
Range, %s-DI, AU
Range, %s-Sun, AU
Phase, DI-%s-Sun, deg
Elongation, Sun-DI-%s, deg
""".strip().split('\n')]
try:
### Moved matplotlib import to here so test runs to here at least
from matplotlib import pyplot as plt
plt.figure(1)
for idx in range(len(titles)):
ordinate = [i[idx+2] for i in valarrs]
plt.subplot( 221+idx )
plt.plot( days, ordinate )
plt.plot( days, ordinate, '.')
plt.title( titles[idx] )
plt.ylabel( titles[idx] )
if idx>1: plt.xlabel( 'T-Tperi, d' )
plt.show()
except:
print( "Bypassed, or failed, matplotlib tests" )
def compute_posvels(self, ephem="DE421", planets=False):
"""Compute positions and velocities of the observatories and Earth.
Compute the positions and velocities of the observatory (wrt
the Geocenter) and the center of the Earth (referenced to the
SSB) for each TOA. The JPL solar system ephemeris can be set
using the 'ephem' parameter. The positions and velocities are
set with PosVel class instances which have astropy units.
"""
# Record the planets choice for this instance
self.planets = planets
# Remove any existing columns
cols_to_remove = ['ssb_obs_pos', 'ssb_obs_vel', 'obs_sun_pos']
for c in cols_to_remove:
if c in self.table.colnames:
log.info('Column {0} already exists. Removing...'.format(c))
self.table.remove_column(c)
for p in ('jupiter', 'saturn', 'venus', 'uranus'):
name = 'obs_'+p+'_pos'
if name in self.table.colnames:
log.info('Column {0} already exists. Removing...'.format(name))
self.table.remove_column(name)
load_kernels(ephem)
pth = os.path.join(pintdir, "datafiles")
ephem_file = os.path.join(pth, "%s.bsp"%ephem.lower())
log.info("Loading %s ephemeris." % ephem_file)
spice.furnsh(ephem_file)
self.table.meta['ephem'] = ephem
ssb_obs_pos = table.Column(name='ssb_obs_pos',
data=numpy.zeros((self.ntoas, 3), dtype=numpy.float64),
unit=u.km, meta={'origin':'SSB', 'obj':'OBS'})
ssb_obs_vel = table.Column(name='ssb_obs_vel',
data=numpy.zeros((self.ntoas, 3), dtype=numpy.float64),
unit=u.km/u.s, meta={'origin':'SSB', 'obj':'OBS'})
obs_sun_pos = table.Column(name='obs_sun_pos',
data=numpy.zeros((self.ntoas, 3), dtype=numpy.float64),
unit=u.km, meta={'origin':'OBS', 'obj':'SUN'})
if planets:
plan_poss = {}
for p in ('jupiter', 'saturn', 'venus', 'uranus'):
name = 'obs_'+p+'_pos'
plan_poss[name] = table.Column(name=name,
data=numpy.zeros((self.ntoas, 3), dtype=numpy.float64),
unit=u.km, meta={'origin':'OBS', 'obj':p})
# Now step through in observatory groups
for ii, key in enumerate(self.table.groups.keys):
grp = self.table.groups[ii]
obs = self.table.groups.keys[ii]['obs']
loind, hiind = self.table.groups.indices[ii:ii+2]
if (key['obs'] == 'Barycenter'):
for jj, grprow in enumerate(grp):
ind = jj+loind
et = float((grprow['tdbld'] - J2000ld) * SECS_PER_DAY)
obs_sun = objPosVel("SSB", "SUN", et)
obs_sun_pos[ind,:] = obs_sun.pos
elif (key['obs'] == 'Spacecraft'):
# For a time recorded at a spacecraft, use the position of
# the spacecraft recorded in the TOA to compute the needed
# vectors.
pass
elif (key['obs'] == 'Geocenter'):
for jj, grprow in enumerate(grp):
ind = jj+loind
et = float((grprow['tdbld'] - J2000ld) * SECS_PER_DAY)
ssb_earth = objPosVel("SSB", "EARTH", et)
obs_sun = objPosVel("EARTH", "SUN", et)
obs_sun_pos[ind,:] = obs_sun.pos
ssb_obs = ssb_earth
ssb_obs_pos[ind,:] = ssb_obs.pos
ssb_obs_vel[ind,:] = ssb_obs.vel
if planets:
for p in ('jupiter', 'saturn', 'venus', 'uranus'):
name = 'obs_'+p+'_pos'
dest = p.upper()+" BARYCENTER"
pv = objPosVel("EARTH", dest, et)
plan_poss[name][ind,:] = pv.pos
elif (key['obs'] in observatories):
earth_obss = erfautils.topo_posvels(obs, grp)
for jj, grprow in enumerate(grp):
ind = jj+loind
et = float((grprow['tdbld'] - J2000ld) * SECS_PER_DAY)
ssb_earth = objPosVel("SSB", "EARTH", et)
obs_sun = objPosVel("EARTH", "SUN", et) - earth_obss[jj]
obs_sun_pos[ind,:] = obs_sun.pos
ssb_obs = ssb_earth + earth_obss[jj]
ssb_obs_pos[ind,:] = ssb_obs.pos
ssb_obs_vel[ind,:] = ssb_obs.vel
if planets:
for p in ('jupiter', 'saturn', 'venus', 'uranus'):
name = 'obs_'+p+'_pos'
dest = p.upper()+" BARYCENTER"
pv = objPosVel("EARTH", dest, et) - earth_obss[jj]
plan_poss[name][ind,:] = pv.pos
else:
log.error("Unknown observatory {0}".format(key['obs']))
cols_to_add = [ssb_obs_pos, ssb_obs_vel, obs_sun_pos]
if planets:
cols_to_add += plan_poss.values()
self.table.add_columns(cols_to_add)
iceyfp.close()
modelFP = open(cfg['SERVERS'][server]['DOCROOT']+"/"+cfg['TYPES']['Coma']['CONFIG'])
Models = json.load(modelFP)
modelFP.close()
pathToExecutable = cfg['SERVERS'][server]['DOCROOT']+"/"+cfg['MODELS']+"/LoS/pyComa/bin"
#pathToExecutable = '/Users/ices/www-dev/htdocs/ICES/Models/LoS/pyComa/bin'
#pathToExecutable = '/Users/abieler/pyComa/bin'
if args.StringMeasurement == 'LOS':
print 'LOS hybrid case...'
#####################################################################
# get position of s/c and pointing towards Earth from SPICE
#####################################################################
spice.furnsh(args.StringKernelMetaFile)
Et = spice.str2et(args.StringUtcStartTime)
rEarth, lightTime = spice.spkpos("EARTH", Et, "67P/C-G_CSO", "NONE", "ROSETTA")
rRosetta, lightTime = spice.spkpos("ROSETTA", Et, "67P/C-G_CSO", "NONE", "CHURYUMOV-GERASIMENKO")
rEarth = np.array(rEarth)
rRosetta = np.array(rRosetta) * 1000 # transform km to m
print 'Distance from comet: %.2e' % (np.sqrt(np.sum(rRosetta ** 2)))
# p = normalized vector pointing from s/c to Earth in cso coordinates
p = rEarth / np.sqrt(np.sum(rEarth**2))
# rRay = position of rosetta s/c in cso coordinates
rRay = np.array([value for value in rRosetta])
######################################################################
# build line of sight ray xTravel, and extract x, y, z coordinates
def compute_posvels(self, ephem="DE421", planets=False):
"""Compute positions and velocities of the observatories and Earth.
Compute the positions and velocities of the observatory (wrt
the Geocenter) and the center of the Earth (referenced to the
SSB) for each TOA. The JPL solar system ephemeris can be set
using the 'ephem' parameter. The positions and velocities are
set with PosVel class instances which have astropy units.
"""
# Record the planets choice for this instance
self.planets = planets
# Remove any existing columns
cols_to_remove = ['ssb_obs_pos', 'ssb_obs_vel', 'obs_sun_pos']
for c in cols_to_remove:
if c in self.table.colnames:
log.info('Column {0} already exists. Removing...'.format(c))
self.table.remove_column(c)
for p in ('jupiter', 'saturn', 'venus', 'uranus'):
name = 'obs_' + p + '_pos'
if name in self.table.colnames:
log.info('Column {0} already exists. Removing...'.format(name))
self.table.remove_column(name)
load_kernels(ephem)
ephem_file = datapath("%s.bsp" % ephem.lower())
log.info("Loading %s ephemeris." % ephem_file)
spice.furnsh(ephem_file)
self.table.meta['ephem'] = ephem
ssb_obs_pos = table.Column(name='ssb_obs_pos',
data=numpy.zeros((self.ntoas, 3),
dtype=numpy.float64),
unit=u.km,
meta={
'origin': 'SSB',
'obj': 'OBS'
})
ssb_obs_vel = table.Column(name='ssb_obs_vel',
data=numpy.zeros((self.ntoas, 3),
dtype=numpy.float64),
unit=u.km / u.s,
meta={
'origin': 'SSB',
'obj': 'OBS'
})
obs_sun_pos = table.Column(name='obs_sun_pos',
data=numpy.zeros((self.ntoas, 3),
dtype=numpy.float64),
unit=u.km,
meta={
'origin': 'OBS',
'obj': 'SUN'
})
if planets:
plan_poss = {}
for p in ('jupiter', 'saturn', 'venus', 'uranus'):
name = 'obs_' + p + '_pos'
plan_poss[name] = table.Column(name=name,
data=numpy.zeros(
(self.ntoas, 3),
dtype=numpy.float64),
unit=u.km,
meta={
'origin': 'OBS',
'obj': p
})
# Now step through in observatory groups
for ii, key in enumerate(self.table.groups.keys):
grp = self.table.groups[ii]
obs = self.table.groups.keys[ii]['obs']
loind, hiind = self.table.groups.indices[ii:ii + 2]
if (key['obs'] == 'Barycenter'):
for jj, grprow in enumerate(grp):
ind = jj + loind
et = float((grprow['tdbld'] - J2000ld) * SECS_PER_DAY)
obs_sun = objPosVel("SSB", "SUN", et)
obs_sun_pos[ind, :] = obs_sun.pos
elif (key['obs'] == 'Spacecraft'):
# For a time recorded at a spacecraft, use the position of
# the spacecraft recorded in the TOA to compute the needed
# vectors.
pass
elif (key['obs'] == 'Geocenter'):
for jj, grprow in enumerate(grp):
ind = jj + loind
et = float((grprow['tdbld'] - J2000ld) * SECS_PER_DAY)
ssb_earth = objPosVel("SSB", "EARTH", et)
obs_sun = objPosVel("EARTH", "SUN", et)
obs_sun_pos[ind, :] = obs_sun.pos
ssb_obs = ssb_earth
ssb_obs_pos[ind, :] = ssb_obs.pos
ssb_obs_vel[ind, :] = ssb_obs.vel
if planets:
for p in ('jupiter', 'saturn', 'venus', 'uranus'):
name = 'obs_' + p + '_pos'
dest = p.upper() + " BARYCENTER"
pv = objPosVel("EARTH", dest, et)
plan_poss[name][ind, :] = pv.pos
elif (key['obs'] in observatories):
earth_obss = erfautils.topo_posvels(obs, grp)
for jj, grprow in enumerate(grp):
ind = jj + loind
et = float((grprow['tdbld'] - J2000ld) * SECS_PER_DAY)
ssb_earth = objPosVel("SSB", "EARTH", et)
obs_sun = objPosVel("EARTH", "SUN", et) - earth_obss[jj]
obs_sun_pos[ind, :] = obs_sun.pos
ssb_obs = ssb_earth + earth_obss[jj]
ssb_obs_pos[ind, :] = ssb_obs.pos
ssb_obs_vel[ind, :] = ssb_obs.vel
if planets:
for p in ('jupiter', 'saturn', 'venus', 'uranus'):
name = 'obs_' + p + '_pos'
dest = p.upper() + " BARYCENTER"
pv = objPosVel("EARTH", dest, et) - earth_obss[jj]
plan_poss[name][ind, :] = pv.pos
else:
log.error("Unknown observatory {0}".format(key['obs']))
cols_to_add = [ssb_obs_pos, ssb_obs_vel, obs_sun_pos]
if planets:
cols_to_add += plan_poss.values()
self.table.add_columns(cols_to_add)
def mpoplot(userdates, master_scale=15, demo=False):
"""
... explain what this does...
"""
outdir = '../sample_data/output'
# if demo:
# shutil.rmtree(outdir)
# os.makedirs(outdir)
# else:
# if not os.path.exists(outdir):
# os.makedirs(outdir)
# else:
# print('\n Uh-oh! The directory {} already exists.'.format(
# outdir))
# if yesno(' Do you want to replace it?'):
# shutil.rmtree(outdir)
# os.makedirs(outdir)
# else:
# return
# Clear and load the kernels that this program requires.
spice.kclear()
spice.furnsh('epys.mk')
# A graphic will be created for each 'date' in 'dates':
for date in userdates:
et = spice.str2et(date)
datestr = (spice.et2utc(et, 'ISOC', 0))
# -- Outer frame -------------------------------------------------
dist_scl = 250.0
elts = getorbelts(date)
arg_peri = elts[4]
# Opacity of degree frame and Venus graphic
frame_op = 0.5
# # Process JD time into calendar time strings
# datestr = spice.et2utc(et, 'ISOC', 0)
date = '{} {}'.format(datestr.split('T')[0],
datestr.split('T')[1])
edate, etime = date.split()
eyear = "{}".format(edate.split('-')[0])
emonth = "{0:02d}".format(int(edate.split('-')[1]))
eday = "{0:02d}".format(int(edate.split('-')[2]))
epoch = "{}/{}/{}".format(eday, emonth, eyear)
ep_name = "{}{}{}".format(eyear, emonth, eday)
frame = _outerframe(epoch, frmSize=master_scale, frm_op=frame_op,
mpoargp=arg_peri)
# -- Mercury Planet --------------------------------------------------
# tru_ano = 90
# look_from = 270
# x1 = "{}%".format((100*math.sin(math.radians((tru_ano+90)/2.))))
# x2 = "{}%".format(100-(100*sin(radians((tru_ano+90)/2.))))
angs = range(0, 360, 1)
plt.plot(angs, ["{}".format((100 * math.sin(math.radians(x / 2))))
for x in angs], 'yo-')
plt.plot(angs, ["{}".format(100 - (100 *
math.sin(math.radians(x / 2)))) for x in angs], 'ro-')
# plt.show()
stop1 = "#C8C5E2"
# stop2 = "#373163"
defs = svg.SVG("defs",
svg.SVG("linearGradient",
svg.SVG("stop", stop_color=stop1,
stop_opacity=1, offset="45%"),
svg.SVG("stop", stop_color=stop1,
stop_opacity=1, offset="55%"),
x1="0%", y1="0%", x2="100%", y2="0%",
spreadMethod="pad",
id="mercGrad")
)
# defs = svg.SVG('defs',
# svg.SVG('radialGradient',
# svg.SVG('stop',
# stop_color=stop1,
# stop_opacity=1,
# offset='38%'),
# svg.SVG('stop',
# stop_color=stop2,
# stop_opacity=1,
# offset='40%'),
# cx='50%', cy='50%',
# fx='230%', fy='50%',
# r='300%',
# spreadMethod='pad',
# id='mercGrad')
# )
merc_rad = 2439.99 # km
merc_rad_scl = merc_rad / dist_scl
merc_ball = svg.Ellipse(0, 0, 0, merc_rad_scl, merc_rad_scl,
fill="url(#mercGrad)", stroke_width="0.15pt")
# -- MPO Orbit --
mpo_orb_ecc = 0.163229
mpo_orb_sma = 3394.0 # km
mpo_orb_sma_scl = mpo_orb_sma / dist_scl
mpo_orb_smi_scl = mpo_orb_sma_scl * math.sqrt(1 - mpo_orb_ecc ** 2)
# Make things cleaner
a = mpo_orb_sma_scl
b = mpo_orb_smi_scl
mpo_orb = svg.Ellipse(-math.sqrt(a ** 2 - b ** 2), 0, 0, a, b,
fill="none", stroke_width="0.25pt")
# apof = 8
mpo_orb_apses = svg.Line(-_rellipse(a, b, 180) - 5, 0,
_rellipse(a, b, 0) + 10, 0,
stroke_width="0.15pt",
stroke_dasharray="2, 2")
dot_angs = range(0, 360, 20)
dots = [_orbitdot(a, b, x, color="black") for x in dot_angs]
mpo_orb_dots = svg.Fig()
for dot in dots:
mpo_orb_dots.d.append(dot)
mpo_orb_trans = svg.rotate(arg_peri, 0, 0)
mpo_orb_plot = svg.Fig(mpo_orb, mpo_orb_apses, mpo_orb_dots,
trans=mpo_orb_trans)
# -- Direction arrow -------------------------------------------------
dirarend = svg.make_marker("dirarrowend", "arrow_end",
fill_opacity=0.2)
dirarend.attr["markerWidth"] = 7.5
x1, y1 = master_scale + 1, 0.4,
x2, y2 = master_scale + 1, 1
dirarwstrt = svg.Line(x1, y1, x2, y2, stroke_width=".4pt",
stroke_opacity=0.2, arrow_end=dirarend)
dirarw = svg.Fig(dirarwstrt, trans="x*cos(y), x*sin(y)")
# -- Apsis view ------------------------------------------------------
apvx, apvy = master_scale + 3, -master_scale - 3
apsisviewball = svg.Ellipse(apvx, apvy,
0, merc_rad_scl * 0.25,
merc_rad_scl * 0.25,
fill="url(#mercGrad)",
stroke_width="0.15pt")
apsisviewlats = svg.Fig()
for x in range(-9, 10, 3):
hscl = math.sin(math.radians(x * 10))
wscl = math.cos(math.radians(x * 10))
x1 = apvx - (merc_rad_scl * 0.25 * wscl)
y1 = apvy + (merc_rad_scl * 0.25 * hscl)
x2 = apvx + (merc_rad_scl * 0.25 * wscl)
y2 = apvy + (merc_rad_scl * 0.25 * hscl)
apsisviewlats.d.append(svg.Line(x1, y1, x2, y2,
stroke_width=".2pt",
stroke_opacity=0.4))
apvarend = svg.make_marker("apvarrowend",
"arrow_end",
fill_opacity=0.6)
apvarend.attr["markerWidth"] = 3.0
apvarend.attr["markerHeight"] = 3.0
x1, y1 = apvx, apvy - 3
x2, y2 = apvx, apvy + 3
apsisvieworbit = svg.Line(x1, y1, x2, y2,
stroke_width=".4pt",
stroke_opacity=0.6,
arrow_end=apvarend)
xd = apvx
yd = apvy + (merc_rad_scl * 0.25 * math.sin(math.radians(arg_peri)))
apsisviewdot = svg.Fig(svg.Dots([(xd, yd)],
svg.make_symbol("apsisdot",
fill="black",
fill_opacity=0.6
),
0.6, 0.6
)
)
apsisview = svg.Fig(apsisviewball,
apsisviewlats,
apsisvieworbit,
apsisviewdot)
# -- Build final figure ----------------------------------------------
wa = master_scale * 1.5
svgout = svg.Fig(frame,
merc_ball,
mpo_orb_plot,
dirarw,
apsisview
).SVG(svg.window(-wa, wa, -wa, wa))
svgout.prepend(defs)
argp = int(arg_peri)
svgout.save(os.path.join(outdir,
"mpo_orbit_plot_{}_{}.svg".format(ep_name,
argp)
)
)
def test_example_loading():
currentdir = os.getcwd()
os.chdir(kernelpath)
spice.furnsh("ck/moc42_2010100_2010100_v01.bc")
spice.furnsh("fk/lro_frames_2012255_v02.tf")
spice.furnsh("fk/lro_dlre_frames_2010132_v04.tf")
spice.furnsh("ick/lrodv_2010090_2010121_v01.bc")
spice.furnsh("lsk/naif0010.tls")
spice.furnsh('sclk/lro_clkcor_2010096_v00.tsc')
spice.furnsh("spk/fdf29_2010100_2010101_n01.bsp")
spice.furnsh('./planet_spk/de421.bsp')
utc = dt.strptime('2010100 05', '%Y%j %H').isoformat()
et = spice.utc2et(utc)
t = spice.spkpos('sun', et, 'LRO_DLRE_SCT_REF', 'lt+s', 'lro')
print(t)
answer = ((-63972935.85033857, -55036272.7848299, 123524941.9877458),
499.009424105693)
for i, j in zip(t[0], answer[0]):
assert_equals(round(i, 3), round(j, 3))
os.chdir(currentdir)
def test_horizons(self):
import horizons
target = 'C/2013 S1'
target = 'C/2011 L4'
spkFilename, spiceId, status = horizons.gomain(target)
spice.furnsh(spkFilename)
self.kernels += [spkFilename]
target_ = '_'.join(target.split())
et0 = spice.utc2et('2013-01-10T12:00:00')
ls2au = spice.convrt(spice.clight(), 'KM', 'AU')
dpr = spice.dpr()
spd = spice.spd()
deltatime = None
while deltatime is None or abs(deltatime) > 5e-7:
stS2I, lsS2I = spice.spkgeo(spiceId, et0, 'J2000', 10)
posn, veloc = stS2I[:3], stS2I[3:]
deltatime = -spice.vdot(posn, veloc) / spice.vdot(veloc, veloc)
et0 += deltatime
valarrs = []
print((
deltatime,
spice.et2utc(et0, 'ISOC', 3),
))
deltatime = 1.0
sixmonths = spice.pi() * 1e7
while deltatime < sixmonths:
for pmdet in (-deltatime, deltatime):
et = et0 + pmdet
utc = spice.et2utc(et, 'ISOC', 1)
stD2I, lsD2I = spice.spkgeo(spiceId, et, 'J2000', -140)
stI2S, lsI2S = spice.spkgeo(10, et, 'J2000', spiceId)
stD2S, lsD2S = spice.spkgeo(10, et, 'J2000', -140)
rD2I, rI2S = [ls * ls2au for ls in [lsD2I, lsI2S]]
aDIS, aSDI = [
ang * dpr for ang in [
spice.vsep(spice.vminus(stD2I[:3]), stI2S[:-3]),
spice.vsep(stD2S[:3], stD2I[:-3])
]
]
valarrs += [(
et,
pmdet,
rD2I,
rI2S,
aDIS,
aSDI,
utc,
)]
deltatime *= 1.2
valarrs.sort()
for valarr in valarrs:
print('%12.1f %9.3f %9.3f %7.2f %7.2f %s' % valarr[1:])
days = [i[1] / spd for i in valarrs]
titles = [
i % (target_, ) for i in """
Range, %s-DI, AU
Range, %s-Sun, AU
Phase, DI-%s-Sun, deg
Elongation, Sun-DI-%s, deg
""".strip().split('\n')
]
try:
### Moved matplotlib import to here so test runs to here at least
from matplotlib import pyplot as plt
plt.figure(1)
for idx in range(len(titles)):
ordinate = [i[idx + 2] for i in valarrs]
plt.subplot(221 + idx)
plt.plot(days, ordinate)
plt.plot(days, ordinate, '.')
plt.title(titles[idx])
plt.ylabel(titles[idx])
if idx > 1: plt.xlabel('T-Tperi, d')
plt.show()
except:
print("Bypassed, or failed, matplotlib tests")
ETTOI-108d is TOI(tparse('2005-07-04T05:44:34.2')) + 64.184s - 108d
Alternate DII SCLK kernels:
'$K/dii_sclkscet_00008_science.tsc'
'$K/dii_sclkscet_00008.tsc'
========================================================================
"""
import os
import sys
import spice
import pprint
import timediffs
import matplotlib.pyplot as plt
### Load meta-kernel, get start time ETTOI-108d
spice.furnsh(__file__)
### Override any kernels with sys.argv[1:]
for sclkk in sys.argv[1:]:
spice.furnsh(sclkk)
### Get TEXT kernel list
ks = '\n'.join([
os.path.basename(spice.kdata(i, 'text')[0])
for i in range(spice.ktotal('TEXT'))
])
### Get TOI-108d, set up for one point per day for 108d
et = spice.gdpool('ETTOI-108d', 0, 1)[1]
spanDays = 108
diffs = range(spanDays + 1)