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 test_bodvXds(self):
periState = spice.conics( self.elts, self.t0)
self.assertAlmostEqual( spice.vnorm(periState[:3]), self.rpKM, places=11)
helioIson = MPC_HELIOCENTRIC_ISON()
for jdtt,pos,vel in helioIson.jpv:
et = spice.str2et( jdtt )
conicState = spice.conics( self.elts, et )
print( conicState )
print( pos+vel )
self.assertAlmostEqual( spice.vdist(conicState[:3], pos), 0.0, places=3)
def createCompositeTrajectory(body, renderingConfig, parts):
trajArray = []
for part in parts:
trajArray.append(
getObjectTrajectory(
body, part['parent'], spice.str2et(part['from'] + ' TDB'),
spice.str2et(part['to'] + ' TDB'), part['error'],
part['rendering'] if 'rendering' in part else None,
part['step'] if 'step' in part else 60))
result = {
'type': 'composite',
'periodStart': min([t['periodStart'] for t in trajArray]),
'periodEnd': max([t['periodEnd'] for t in trajArray]),
'data': trajArray
}
if renderingConfig:
result['rendering'] = renderingConfig
return result
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' )
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 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 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 _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
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:
if instrument.name == 'sun':