def test_smap(self):
target = 'SMAP'
et0 = spice.utc2et( '2016-06-01T12:00:00' )
dpr = spice.dpr()
a,b,c = [spice.gdpool('BODY399_RADII',i,1)[1] for i in range(3)]
ods = []
for deltatime in [0.1 * i for i in range(1080)]:
et = et0 + deltatime
stSmap,lsSmap = spice.spkezr( target, et, 'IAU_EARTH', 'NONE', 'EARTH' )
posn, veloc = stSmap[:3], stSmap[3:]
stSun,lsSun = spice.spkezr( 'SUN', et0, 'IAU_EARTH', 'LT', 'EARTH' )
mtx = spice.pxform( 'SMAP_REFLECTOR', 'IAU_EARTH', et)
boreEbf = spice.mxv( mtx, [1.0,0,0] )
point = spice.surfpt( posn, boreEbf, a, b, c)
rsurfpt,lon,lat = spice.reclat( point )
utc = spice.et2utc( et, 'ISOC', 3 )
ods += [ OD(deltatime=deltatime,posn=posn,veloc=veloc,boreEbf=boreEbf
,utc=utc,point=point,rsurfpt=rsurfpt
,rsmap=spice.vnorm(posn),lat=lat,lon=lon
,raynge=spice.vnorm(spice.vsub(point,posn))
,sunsep=spice.vsep( spice.ucrss(posn,veloc), stSun[:3] )
)
]
try:
### Moved matplotlib import to here so test runs to here at least
from matplotlib import pyplot as plt
plt.figure(1)
keys = 'lat lon raynge'.split()
secs = [od['deltatime'] for od in ods]
for idx in range(len(keys)):
scal = 1.0 if keys[idx] in 'rsurfpt rsmap raynge sunsep rp ecc t0 mu a P eccmean amean Pmean'.split() else dpr
ordinate = [od[keys[idx]]*scal for od in ods]
plt.subplot( 221+idx )
plt.plot( secs, ordinate )
plt.plot( secs, ordinate, '.')
plt.title( keys[idx] )
plt.ylabel( '%s%s' % (keys[idx],'' if scal==1.0 else ', deg') )
if idx>1: plt.xlabel( 'T-T0, s' )
abscissa = [od['lon']*dpr for od in ods]
ordinate = [od['lat']*dpr for od in ods]
plt.subplot( 221+idx+1 )
plt.title( 'lon vs. lat' )
plt.plot( abscissa, ordinate )
plt.xlabel( 'lon, deg' )
plt.ylabel( 'lat, deg' )
plt.show()
except:
print( "Bypassed, or failed, matplotlib tests" )
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 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
### 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
utcs = [spice.et2utc(et, 'isoc', 3), spice.et2utc(et, 'isod', 3)]
sclks = [spice.sce2s(scids[i], et) for i in rn]
encds = [spice.scencd(scids[i], sclks[i]) / 256e0 for i in rn]
### Build and print output
f3 = ' %.3f'
sencds = (f3 * n).strip() % tuple(
[spice.scencd(scids[i], sclks[i]) / 256e0 for i in rn])
diff3 = (f3 * (n + 1)).strip() % tuple([encds[0] - encds[1]] +
[et - encds[i] for i in rn])
print((
utcs,
sclks,
sencds,
diff3,
))
### Increment ET by 1d (spice.spd() = seconds/day)
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 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")
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
utcs = [ spice.et2utc( et, 'isoc', 3), spice.et2utc( et, 'isod', 3) ]
sclks = [ spice.sce2s(scids[i],et) for i in rn ]
encds = [ spice.scencd(scids[i],sclks[i])/256e0 for i in rn ]
### Build and print output
f3 = ' %.3f'
sencds = (f3*n).strip() % tuple([ spice.scencd(scids[i],sclks[i])/256e0 for i in rn ])
diff3 = (f3*(n+1)).strip() % tuple( [encds[0] - encds[1]] + [ et-encds[i] for i in rn ])
print( (utcs,sclks,sencds,diff3,) )
### Increment ET by 1d (spice.spd() = seconds/day)
et += spice.spd()
dcmd = pdsi._downone(faux)
### Extract start time from dcmd (CoreMetadata) as ISO UTC string
firstTomsUTC = '%sT%s' % (
dcmd['INVENTORYMETADATA']['RANGEDATETIME']['RANGEBEGINNINGDATE']
['VALUE'],
dcmd['INVENTORYMETADATA']['RANGEDATETIME']['RANGEBEGINNINGTIME']
['VALUE'],
)
### Combine start time and /Time offset to get the TOMS data zero epoch as seconds past J2000 epoch
### N.B. is typically (always?) equivalent to 1993-01-01T00:00:00 UTC
tomsZeroEpoch = spice.utc2et(firstTomsUTC) - tomsOffsetTimes[0]
print('%s(Epoch) %s(Start) %s' % (
spice.et2utc(tomsZeroEpoch, 'ISOC', 1),
firstTomsUTC,
fnInput,
))
### Iterators
twoDshape = surfLonDegs.shape
rowIter, pixelIter = map(xrange, twoDshape)
glintAngles = numpy.zeros(twoDshape, dtype=numpy.float32)
for row in rowIter:
### Earth-Sun vector, convert to unit vector
earth2Sun = spice.spkezr('SUN',
tomsZeroEpoch + tomsOffsetTimes[row],
def test_smap(self):
target = 'SMAP'
et0 = spice.utc2et('2016-06-01T12:00:00')
dpr = spice.dpr()
a, b, c = [spice.gdpool('BODY399_RADII', i, 1)[1] for i in range(3)]
ods = []
for deltatime in [0.1 * i for i in range(1080)]:
et = et0 + deltatime
stSmap, lsSmap = spice.spkezr(target, et, 'IAU_EARTH', 'NONE',
'EARTH')
posn, veloc = stSmap[:3], stSmap[3:]
stSun, lsSun = spice.spkezr('SUN', et0, 'IAU_EARTH', 'LT', 'EARTH')
mtx = spice.pxform('SMAP_REFLECTOR', 'IAU_EARTH', et)
boreEbf = spice.mxv(mtx, [1.0, 0, 0])
point = spice.surfpt(posn, boreEbf, a, b, c)
rsurfpt, lon, lat = spice.reclat(point)
utc = spice.et2utc(et, 'ISOC', 3)
ods += [
OD(deltatime=deltatime,
posn=posn,
veloc=veloc,
boreEbf=boreEbf,
utc=utc,
point=point,
rsurfpt=rsurfpt,
rsmap=spice.vnorm(posn),
lat=lat,
lon=lon,
raynge=spice.vnorm(spice.vsub(point, posn)),
sunsep=spice.vsep(spice.ucrss(posn, veloc), stSun[:3]))
]
try:
### Moved matplotlib import to here so test runs to here at least
from matplotlib import pyplot as plt
plt.figure(1)
keys = 'lat lon raynge'.split()
secs = [od['deltatime'] for od in ods]
for idx in range(len(keys)):
scal = 1.0 if keys[
idx] in 'rsurfpt rsmap raynge sunsep rp ecc t0 mu a P eccmean amean Pmean'.split(
) else dpr
ordinate = [od[keys[idx]] * scal for od in ods]
plt.subplot(221 + idx)
plt.plot(secs, ordinate)
plt.plot(secs, ordinate, '.')
plt.title(keys[idx])
plt.ylabel('%s%s' %
(keys[idx], '' if scal == 1.0 else ', deg'))
if idx > 1: plt.xlabel('T-T0, s')
abscissa = [od['lon'] * dpr for od in ods]
ordinate = [od['lat'] * dpr for od in ods]
plt.subplot(221 + idx + 1)
plt.title('lon vs. lat')
plt.plot(abscissa, ordinate)
plt.xlabel('lon, deg')
plt.ylabel('lat, deg')
plt.show()
except:
print("Bypassed, or failed, matplotlib tests")
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 result = spice.objects.Cell(spice.DataType.SPICE_DP,500) ### Make the call to the generic Geometry Finder call cnfine, result = spice.gfposc( target, frame, abcorr, obsrvr, crdsys, coord, relate, refval, adjust, step, nintvls, cnfine, result ) ### Output results as four columns ### - Crossing ordinal ### - UTC of crossing as ISO calendar time ### - TDB of crossing as calendar time (no leapseconds) ### - The Z value of Venus in the Jupiter-centered IAU_JUPITER frame for i in xrange(spice.wncard(result)): et0,et1 = spice.wnfetd(result,i) assert et0 == et1 print( ( i+1, spice.et2utc(et0,'ISOC',3), spice.etcal(et0), spice.spkezr(target,et0,frame,abcorr,obsrvr)[0][2] ,) )