def inter_bokeh():
epoch2000=datetime.datetime.strptime("01-01-2000 00:00","%d-%m-%Y %H:%M")
epoch2000=time.mktime(epoch2000.timetuple())
lat=request.args.get('lat')
long=request.args.get('lon')
spkid=request.args.get('spkid')
inicio=request.args.get('start')
neo=spkid+".bsp"
N=200
spi.kclear()
spi.furnsh("/home/cristobal/horizons_iterface/github/neo-challege-2016/spice/meta.fgl")
spi.furnsh("/home/cristobal/horizons_iterface/github/neo-challege-2016/spice/kernels/neos/"+neo)
inicio=inicio.replace("Z","").replace("T"," ")
final= dateutil.parser.parse(inicio)+datetime.timedelta(days=0.5)
final=str(final.year)+"-"+str(final.month).zfill(2)+"-"+str(final.day).zfill(2)+" "+str(final.hour).zfill(2)+":"+str(final.minute).zfill(2)+":"+str(final.second).zfill(2)+"."+str(final.microsecond)
tiempos=spi.str2et([inicio,final])
tiempos=np.linspace(tiempos[0],tiempos[1],N)
ar=list()
dec=list()
times_list=list()
for k in tiempos:
temp=spi.spkez(int(neo.split(".")[0]),k,"J2000","LT+S",399)
temp2=spi.recrad(temp[0][0:3])
ar.append(temp2[1]*(180/np.pi))
dec.append(temp2[2]*(180/np.pi))
times_list.append(datetime.datetime.utcfromtimestamp(k+epoch2000))
[altura,times_list]=conversion(ar,dec,times_list,lat,long)
json.dumps(altura)
bokeh_pinta(altura,list,neo)
return app.send_static_file('spice.html')
def calc_spice(initi,final,neo,puntos,db):
N=puntos#2880 #Precision
spi.kclear() #Limpiamos el pool de los kernels.
#MetaKernel con los datos genericos menos el neo.
spi.furnsh("./meta.fgl")
spi.furnsh("./kernels/neos/"+neo)
#tiempos=spi.str2et(["Jun 20 2004","Dec 1, 2005"])
ini=initi#"Apr 24 2016 0:00:00"
fin=final#"Jun 20 2016 0:00:00"
#Fran: It would be better to directly put the number of seconds of J2000 instead of this shit...
epoch2000=datetime.datetime.strptime("01-01-2000 00:00","%d-%m-%Y %H:%M")
epoch2000=time.mktime(epoch2000.timetuple())
tiempos=spi.str2et([ini,fin])
tiempos=np.linspace(tiempos[0],tiempos[1],N)
ar=list()
dec=list()
#pdb.set_trace()
for k in tiempos:
temp=spi.spkez(int(neo.split(".")[0]),k,"J2000","LT+S",399)
temp2=spi.recrad(temp[0][0:3])
ar.append(temp2[1]*(180/np.pi))
dec.append(temp2[2]*(180/np.pi))
for k in range(len(tiempos)):
document={"spkid":neo.split(".")[0],"name":neo.split(".")[0],"ra":ar[k],"dec":dec[k],"date":datetime.datetime.fromtimestamp(int(tiempos[k])+epoch2000)}
day=str(document["date"].day).zfill(2)+str(document["date"].month).zfill(2)+str(document["date"].year)
day="d"+day
exec("db.%s.insert_one(document)"%day)
def TrueToEccAnom(self,ta):
"""Convert True Anomaly to Eccentric Anomaly
https://en.wikipedia.org/wiki/Eccentric_anomaly#From_the_true_anomaly
"""
return sp.recrad(sp.vpack(self.eccChf + math.cos(ta)
,self.bOverA * math.sin(ta)
,0.
)
)[iRA]
def invE(self,offsetArcLength=None,arcLengthArg=None,rtnIter=False):
"""Find eccentric anomaly corresponding to the input arc length"""
### Parse arguments
assert not (offsetArcLength is not None and arcLengthArg is not None)
if arcLengthArg is None: arcLengthTarget = self.arcChf + offsetArcLength
else : arcLengthTarget = float(arcLengthArg)
### Initial estimate of Eccentric Anomaly
### - highest positive or negative multiple of halfpi that gives
### an arc length less than or equal to targetLength
nQuad = int(arcLengthTarget / self.quadArc)
arcLengthGuess = nQuad * self.quadArc
if arcLengthGuess > arcLengthTarget:
nQuad -= 1
arcLengthGuess -= self.quadArc
eaGuess0 = eaGuess = nQuad * halfpi
eaGuess0PlusTwoPi = eaGuess0 + twopi
deltaArc = arcLengthTarget - arcLengthGuess
tol = self.aChf * 1e-9
itter = 0
while abs(deltaArc) > tol:
itter += 1
### Vector from primary focus to Ecc. Anom. guess
cosea = math.cos(eaGuess)
sinea = math.sin(eaGuess)
x = self.aChf * cosea
y = self.bChf * sinea
### Delta-[x,y] of tangent at (x,y) for distance of deltaArc
delx = -self.aChf * sinea
dely = self.bChf * cosea
fac = deltaArc / sp.vnorm(sp.vpack(delx,dely,0.))
delx *= fac
dely *= fac
### Delta-vector tangent at (x,y) for distance of deltaArc
### - [X,Y,Z] = [x+delx, y+dely, 0]
### - scale X by 1/a and Y by 1/b to get Eccentric Anomaly
eaGuess = sp.recrad(sp.vpack((x+delx)/self.aChf
,(y+dely)/self.bChf
,0.
)
)[iRA]
while eaGuess0 > eaGuess: eaGuess += twopi
while (eaGuess0PlusTwoPi) <= eaGuess: eaGuess -= twopi
arcLengthGuess = self.E(eaGuess)
deltaArc = arcLengthTarget - arcLengthGuess
return rtnIter and (eaGuess,itter,) or eaGuess
def main():
neo="2000433.bsp"
N=200
ini="Apr 24 2016 0:00:00"
fin="Apr 25 2016 0:00:00"
ALT=390
LAT=40.123
LONG=-3.70
obser=EarthLocation(lat=LAT*u.deg,lon=LONG*u.deg,height=ALT*u.m)
#===================================================
epoch2000=datetime.datetime.strptime("01-01-2000 00:00","%d-%m-%Y %H:%M")
epoch2000=time.mktime(epoch2000.timetuple())
#===================================================
spi.kclear()
spi.furnsh("./meta.fgl")
spi.furnsh("./../kernels/neos/"+neo)
tiempos=spi.str2et([ini,fin])
tiempos=np.linspace(tiempos[0],tiempos[1],N)
alt_list=list()
times_list=list()
for k in tiempos:
temp=spi.spkez(int(neo.split(".")[0]),k,"J2000","LT+S",399)
temp2=spi.recrad(temp[0][0:3])
ar=(temp2[1]*(180/np.pi))
dec=(temp2[2]*(180/np.pi))
aux=datetime.datetime.utcfromtimestamp(k+epoch2000)
fechas_aux=((str(aux.year)+"-"+str(aux.month).zfill(2)+"-"+str(aux.day).zfill(2)+" "+str(aux.hour).zfill(2)+":"+str(aux.minute).zfill(2)+":"+str(aux.second).zfill(2)+"."+str(aux.microsecond)))
times_list.append(aux)
fechas_aux=Time(fechas_aux)
frames_loc=AltAz(obstime=fechas_aux,location=obser)
#pdb.set_trace()
alt_list.append((SkyCoord(ra=ar*u.deg,dec=dec*u.deg,frame='icrs')).transform_to(frames_loc).alt.value)
#pdb.set_trace()
output_file("spice.html",title="NEO SOURCE")
p=figure(title="NEO Visual",x_axis_label="Time",tools="pan,box_zoom,reset,save,hover",y_axis_label="Elevation (deg)")
p.line(times_list,alt_list,legend=neo)
hover=p.select_one(HoverTool)
hover.point_policy="follow_mouse"
show(p)
dt = spice.vdot(state[:3],state[3:]) / spice.vdot(state[3:],state[3:])
oldet = et
et = et - dt
while abs(et-oldet)>0.:
state,lt = spice.spkezr(spacecraft,et,'J2000','NONE',target)
dt = spice.vdot(state[:3],state[3:]) / spice.vdot(state[3:],state[3:])
oldet = et
et = et - dt
utcPRG = spice.et2utc(et,'ISOC',3,99)
mtxJ2kToBF = spice.tipbod('J2000', targetID, et)
velocityPRG_BF = spice.mxv(mtxJ2kToBF,state[3:])
V_prg,ra,Theta = spice.recrad(velocityPRG_BF)
Theta_deg = Theta * dpr
print((dt,dt/et,utcPRG,V_prg,Theta_deg))
import matplotlib.pyplot as plt
days = 7
hours = xrange(-24*days,24*days + 1)
speeds = [ spice.vnorm(spice.spkezr(spacecraft,et+(hour*3600.),'J2000','NONE',target)[0][3:]) for hour in hours]
Vmin = min(speeds)
plt.axhline(y=V_prg,label='V_prg = %.3fkm/s' % (V_prg,))
plt.axhline(y=Vmin,label='Vmin = %.3fkm/s' % (Vmin,))
def Asincos(i): epoch = t * i / N state = sp.conics(elts,epoch) trueAnom = sp.recrad(state[:3])[1] return state[3:5],numpy.array([math.cos(trueAnom),math.sin(trueAnom),1])
def main():
antes=datetime.datetime.now()
N=100 #Precision
spi.kclear() #Limpiamos el pool de los kernels.
#MetaKernel con los datos.
spi.furnsh("./meta.fgl")
#tiempos=spi.str2et(["Jun 20 2004","Dec 1, 2005"])
ini="Apr 20 2016 0:00:00"
fin="Apr 20 2017 0:00:00"
tiempos=spi.str2et([ini,fin])
tiempos=np.linspace(tiempos[0],tiempos[1],N)
#tiempos=spi.str2et(["Apr 20 2016 0:00:00"])
#pdb.set_trace()
#pdb.set_trace() #Esto es lo mas fino que he llegado:
#try:
a=list()
#Chapuza metida tras sacar velocidad
#=====================================
x=list()
y=list()
z=list()
dx=list()
dy=list()
dz=list()
#=============
#Test para spaceapps
#colat=list()
#longi=list()
#radio=list()
ar=list()
dec=list()
radio=list()
ayuda=list()
#Test para spaceapps (end)
for k in tiempos:
#temp=spi.spkez(2000433,k,"IAU_EARTH","LT+S",399)
temp=spi.spkez(2000433,k,"J2000","LT+S",399)
#temp2=spi.xfmsta(temp[0],'RECTANGULAR','SPHERICAL',399)
temp2=spi.recrad(temp[0][0:3])
#radio.append(temp2[0])
#colat.append(temp2[1])
#longi.append(temp2[2])
radio.append(temp2[0])
ayuda.append(temp2)
ar.append(temp2[1]*(180/np.pi))
dec.append(temp2[2]*(180/np.pi))
x.append(temp[0][0]) #Este ya devuelve el vector completo
y.append(temp[0][1])
z.append(temp[0][2])
dx.append(temp[0][3]) #Este ya devuelve el vector completo
dy.append(temp[0][4])
dz.append(temp[0][5])
despues=datetime.datetime.now()
#spi.xfmtsta(temp[0],'RECTANGULAR','SPHERICAL',399)
pdb.set_trace() # despues-antes
x=np.array(x)
y=np.array(y)
z=np.array(z)
dx=np.array(dx)
dy=np.array(dy)
dz=np.array(dz)
mdscc=station(0)
#=========================== ====
print "Geocentric position for MDSCC:"
print "----------------------------------"
print mdscc
print "----------------------------------"
if False:
a=np.array(a)
x=list()
y=list()
z=list()
for k in a[0]:
x.append(k[0])
y.append(k[1])
z.append(k[2])
#Tenia el dato referedio al centro de masas de la Tierra. Ahora lo refiero a MDSCC.
x=x-mdscc[0]
y=y-mdscc[1]
z=z-mdscc[2]
#data2=list()
#for k in range(len(x)):
# data2.append(spi.recrad([x[k],y[k],z[k]]))
#data2=np.array(data2)
pdb.set_trace()
plt.figure()
plt.subplot(211)
plt.plot(x,y)
plt.xlabel("x [Km]")
plt.ylabel("y [Km]")
plt.subplot(212)
plt.plot(y,z)
plt.xlabel("y Km")
plt.ylabel("z Km")
plt.figure()
plt.plot(dist(dx,dy,dz))
frase="Relative speed as seen from Robledo to Eros from %s to %s"%(ini,fin)
plt.title(frase)
plt.ylabel("Kilometers")
plt.xlabel("Samples")
plt.grid()
fig=plt.figure()
ax=fig.add_subplot(111,projection='3d')
frase="Distance from Eros to Robledo. Starting: %s End: %s"%(ini,fin)
ax.plot(x,y,z,label=frase)
plt.legend()
plt.show()
def XYtoTrueAnom(self,x,y): return sp.recrad(sp.vpack(x-self.cChf,y,0.))[iRA]
def __init__(self,stateChf,mu,stateDep=None):
"""Make chief-only calculations. Save deputy-based calculations for
Deputy() method below; call it now if stateDep is provided
mu = GM, km**3 s**-2
"""
####################################################################
### Extract ECI Positions and ECI velocities from 6-element ECI states
### Save mu in self object
self.rChfEci,self.velChfEci = stateChf[:3], stateChf[3:]
self.mu = mu
####################################################################
### Equations (1) and (2)
### Convert chief position and velocity to [Rhat|Shat|What]1 matrix
self.mtxEciToRsw1 = RVtoRSW(self.rChfEci,self.velChfEci)
####################################################################
### Transform chief position and velocity to RSW1 frame
(self.rChfRsw1
,self.velChfRsw1
) = [ sp.mxv(self.mtxEciToRsw1,v)
for v in
[self.rChfEci,self.velChfEci]
]
####################################################################
### Equations (3) - postponed to deputy calculation
####################################################################
### Equations (4)
### Eccentricity and semi-major axis
### - vHChf = momentum vector
### - self.pChf = semiparameter or semilatus rectum = distance from
### the primary focus to the orbit, measured
### perpendicular to the semi-major axis
### - self.eccChfSquared = Square of Eccentricity
### - derivation, dot product of vEccChf with itself, will always
### be non-negative
### - square root of (1-self.eccChfSquared) will throw math domain
### exception if eccentricity exceeds unity.
### - reciprocal of (1-self.eccChfSquared) will throw division by
### zero exception if eccentricity is unity
### - self.eccChf = Eccentricity (also Elliptic Modulus, k)
### - self.bOverA = ratio of semi-minor to semi-major axes' lengths
### - self.aChf = length of semi-major axis
### - self.bChf = length of semi-minor axis
vHChf = sp.vcrss(self.rChfRsw1,self.velChfRsw1)
self.pChf = sp.vdot(vHChf,vHChf) / self.mu
vEccChf = sp.vsub(sp.vscl(1./self.mu,sp.vcrss(self.velChfRsw1,vHChf)),sp.vhat(self.rChfRsw1))
self.eccChfSquared = sp.vdot(vEccChf,vEccChf)
self.eccChf = math.sqrt(self.eccChfSquared)
self.bOverA = math.sqrt(1 - self.eccChfSquared)
self.aChf = self.pChf / (1. - self.eccChfSquared)
self.bChf = self.pChf / self.bOverA
self.cChf = self.aChf * self.eccChf
if self.eccChfSquared>0.: self.vEccHatChf = sp.vhat(vEccChf)
else : self.vEccHatChf = sp.vhat(self.rChfRsw1)
### Use SPICE toolkit routine to calculate perfocal distance (rp), eccentricity, and semi-major axis
self.rpChf,self.eccChfSpice,inc,lnode,argp,m0,t0,muTmp = sp.oscelt(stateChf,0.,self.mu)
self.aChfSpice = self.rpChf / (1. - self.eccChfSpice)
### Quadrant arc length; used later
self.quadArc = self.aChf * E(halfpi,self.eccChfSquared)
####################################################################
### Equations (5)
### Chief True anomaly posiiton
### Deputy True anomaly postponed to deputy calculation
self.lambdaPerigee = sp.recrad(self.vEccHatChf)[iRA]
self.trueAnom1 = (twopi - self.lambdaPerigee) % twopi
####################################################################
### Equations (6 through 9) - postponed to deputy calculation
####################################################################
### Equations (9) - chief only
### 9.1) Convert True Anomaly 1 (chief) to Eccentric Anomaly
self.eccAnom1 = self.TrueToEccAnom(self.trueAnom1)
### Get the arc length from periapse to the chief
self.arcChf = self.E(self.eccAnom1)
####################################################################
### Complete conversion to EQCM for Deputy if Deputy state is present
if not (stateDep is None): self.Deputy(stateDep)
def Deputy(self,stateDep):
"""Make depyty-based calculations. Chief-only calculations were
performed in __init__() method above
"""
####################################################################
### Extract Deputy ECI Position and velocity from 6-element deputy
### ECI state
self.rDepEci,self.velDepEci = stateDep[:3], stateDep[3:]
####################################################################
### Equations (1) and (2)
### Convert deputy position and velocity to RSW using
### [Rhat|Shat|What]1 matrix
(self.rDepRsw1
,self.velDepRsw1
) = [ sp.mxv(self.mtxEciToRsw1,v)
for v in
[self.rDepEci,self.velDepEci]
]
####################################################################
### Equations (3)
### Get delta-lambda to deputy as RA from (Radius,RA,DEC)
### returned by recrad.
RrdDepRsw1 = sp.recrad(self.rDepRsw1)
self.deltaLambdaDep = sp.recrad(self.rDepRsw1)[iRA]
####################################################################
### Equations (5)
### Deputy True anomaly
self.trueAnom2 = (twopi + self.deltaLambdaDep - self.lambdaPerigee) % twopi
####################################################################
### Equations (6)
### Equivalent chief position at point 2, using PQW2
rChf2 = self.pChf / (1. + (self.eccChf * math.cos(self.trueAnom2)))
pHat = self.vEccHatChf
qHat = sp.ucrss([0.,0.,1.],pHat)
self.rChfPqw2 = sp.vscl(rChf2,sp.vadd(sp.vscl(math.cos(self.trueAnom2),pHat),sp.vscl(math.sin(self.trueAnom2),qHat)))
self.velChfPqw2 = sp.vscl(math.sqrt(self.mu/self.pChf)
,sp.vadd(sp.vscl( -math.sin(self.trueAnom2),pHat)
,sp.vscl(self.eccChf+math.cos(self.trueAnom2),qHat)
)
)
####################################################################
### Equations (7)
### Convert from PQW2 to RSW2
self.mtxPqw2toRsw2 = RVtoRSW(self.rChfPqw2,self.velChfPqw2)
self.rChfRsw2 = sp.mxv(self.mtxPqw2toRsw2,self.rChfPqw2)
self.velChfRsw2 = sp.mxv(self.mtxPqw2toRsw2,self.velChfPqw2)
####################################################################
### Equations (8)
### Transform Deputy vectors to SEZ frame
### - deltaPhiDep is DEC from [Radius,RA,DEC] of rDepRsw1
### - Matrix is ROT2[90-deltaPhiDep] ROT3[deltaLambdaDep]
self.deltaPhiDep = RrdDepRsw1[iDEC]
self.mtxRswToSez = sp.eul2m(halfpi-self.deltaPhiDep,self.deltaLambdaDep,0.,2,3,1)
self.rDepSez = sp.mxv(self.mtxRswToSez,self.rDepRsw1)
self.velDepSez = sp.mxv(self.mtxRswToSez,self.velDepRsw1)
####################################################################
### Equations (9)
### Transform Deputy vectors from SEZ to EQCM frame
### 9.1) Convert True Anomalies 2 (Deputy) to Eccentric Anomaly 2
### - https://en.wikipedia.org/wiki/Eccentric_anomaly#From_the_true_anomaly
### - Possible exceptions: divBy0; domain error.
### - Chief done in __init__() method above
self.eccAnom2 = self.TrueToEccAnom(self.trueAnom2)
### Ensure .eccAnom2 is within PI/2 of .eccAnom1
while self.eccAnom2 > (self.eccAnom1+math.pi): self.eccAnom2 -= (2 * math.pi)
while self.eccAnom2 <= (self.eccAnom1-math.pi): self.eccAnom2 += (2 * math.pi)
### 9.2) Get arc length from positive semi-major axis to deputy
self.arcDep = self.E(self.eccAnom2)
### 9.3) Relate the deputy relative to chief at point 2
self.rDepEqcm = sp.vpack( self.rDepSez[iZsez] - self.rChfRsw2[iRrsw]
, self.arcDep - self.arcChf
, self.deltaPhiDep * rChf2
)
self.velDepEqcm = sp.vpack( self.velDepSez[iZsez] - self.velChfRsw2[iRrsw]
#, (self.velDepSez[iE] * rChf2 / (RrdDepRsw1[iRadius] * self.deltaPhiDep )) - self.velChfRsw1[iE]
, (self.velDepSez[iE] * rChf2 / (RrdDepRsw1[iRadius] * math.cos(self.deltaPhiDep))) - self.velChfRsw1[iE]
, -self.velDepSez[iSsez] * rChf2 / RrdDepRsw1[iRadius]
)
return self.rDepEqcm, self.velDepEqcm
