313 lines
8.3 KiB
Python
313 lines
8.3 KiB
Python
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#!/usr/bin/env python
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import os
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import tempfile
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import isce
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import numpy as np
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import datetime
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from isceobj.Orbit.Orbit import StateVector, Orbit
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from collections import OrderedDict
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try:
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import SpiceyPy
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except ImportError:
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raise Exception('SpiceyPy Python bindings need to be installed to be able to use this library.')
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class SpiceDatabase(object):
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'''
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Class for dealing with SPICE kernel files.
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'''
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dbdir = os.path.join(os.path.dirname(__file__), 'db')
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dblist = os.path.join(dbdir, 'kernels.list')
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def __init__(self):
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'''
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Load the databasename.
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'''
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rdict = OrderedDict()
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infile = open(self.dblist, 'r')
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line = infile.readline()
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while line:
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llist = line.split('=')
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if len(llist)==2 :
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rdict[llist[0].strip()] = os.path.join(self.dbdir, llist[1].strip())
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line = infile.readline()
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infile.close()
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self.data = rdict
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def getList(self):
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'''Get list of kernel files.'''
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ll = []
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for key, val in self.data.items():
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ll.append(val)
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return ll
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def getKernel(self, key):
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return self.data[key]
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def __getitem__(self, key):
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return self.data[key]
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class ISCEOrbit(object):
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'''
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Class for converting ISCE orbits to CSPICE orbits.
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'''
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def __init__(self, orbit):
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self.orbit = orbit
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self.db = SpiceDatabase()
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def exportToSPK(self, spkfile,frame='ITRF93'):
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'''
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Export ISCE orbit to SPK file.
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'''
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if frame not in ('ITRF93', 'J2000', 'ECI_TOD', 'ECLIPJ2000'):
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raise Exception('CSPICE currently only supports ITRF93, J2000, ECLIPJ2000, ECI_TOD.')
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tmpDir = tempfile.mkdtemp(dir='.')
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hdrfile = os.path.join(tmpDir, 'hdrfile')
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setupfile = os.path.join(tmpDir, 'setupfile')
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self.exportOrbitToHeader(hdrfile)
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self.createSetupFile(setupfile, frame=frame)
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self.runMkspk(hdrfile, setupfile, spkfile)
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for root, dirs, files in os.walk(tmpDir):
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for filename in files:
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try:
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os.unlink(os.path.join(tmpDir, filename))
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except:
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os.system("rm "+os.path.join(tmpDir, filename))
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os.rmdir(tmpDir)
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def exportOrbitToHeader(self, hdrfile):
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'''
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Exports a given Orbit to SPICE compatible HDR format.
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'''
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fid = open(hdrfile, 'w')
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for sv in self.orbit:
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tim = sv.getTime()
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pos = sv.getPosition()
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vel = sv.getVelocity()
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pos =[str(x/1000.) for x in pos]
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vel = [str(x/1000.) for x in vel]
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out = [str(tim)] + pos + vel
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fid.write(','.join(out) + '\n')
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fid.close()
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def createSetupFile(self, setupfile, frame=None):
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'''
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Creates a setup file to use with mkspk.
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'''
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fmtString = """\\begindata
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INPUT_DATA_TYPE = 'STATES'
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OUTPUT_SPK_TYPE = 13
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OBJECT_ID = -123710
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OBJECT_NAME = 'RADARSAT'
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CENTER_ID = 399
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CENTER_NAME = 'EARTH'
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REF_FRAME_NAME = '{0}'
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PRODUCER_ID = 'ISCE py3'
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DATA_ORDER = 'EPOCH X Y Z VX VY VZ'
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INPUT_DATA_UNITS = ( 'ANGLES=DEGREES' 'DISTANCES=km')
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DATA_DELIMITER = ','
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LINES_PER_RECORD = 1
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LEAPSECONDS_FILE = '{1}'
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POLYNOM_DEGREE = 3
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SEGMENT_ID = 'SPK_STATES_13'
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TIME_WRAPPER = '# UTC'
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PCK_FILE = ('{2}')
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"""
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frameString = """FRAME_DEF_FILE = ('{0}')
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"""
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txtString="\\begintext"
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tfirst = self.orbit._stateVectors[0].getTime()
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leap = self.db['LEAPSECONDS']
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if tfirst.date() < datetime.date(2000,1,1):
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pck = self.db['EARTHHIGHRES']
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else:
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pck = self.db['EARTHHIGHRESLATEST']
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tod = self.db['EARTHECI_TOD']
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#####Link them to temp dir
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tmpdir = os.path.dirname(setupfile)
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leaplnk = os.path.join(tmpdir, os.path.basename(leap))
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try:
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os.link(leap, leaplnk)
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except:
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os.system("ln -s "+leap+" "+leaplnk)
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pcklnk = os.path.join(tmpdir, os.path.basename(pck))
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try:
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os.link(pck, pcklnk)
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except:
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os.system("ln -s "+pck+" "+pcklnk)
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if frame == 'ECI_TOD':
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todlnk = os.path.join(tmpdir, os.path.basename(tod))
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try:
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os.link(tod, todlnk)
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except:
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os.system("ln -s "+tod+" "+todlnk)
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outstr = fmtString.format(frame, leaplnk, pcklnk)
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if frame == 'ECI_TOD':
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outstr = outstr + frameString.format(todlnk)
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outstr = outstr + txtString
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fid = open(setupfile, 'w')
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fid.write(outstr)
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fid.close()
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def runMkspk(self, hdrfile, setupfile, spkfile):
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if os.path.exists(spkfile):
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print('Removing old version of spk file')
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os.remove(spkfile)
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cmd = ['mkspk', '-input '+hdrfile,
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'-setup '+ setupfile, '-output ' + spkfile]
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os.system(' '.join(cmd))
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pass
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class SpiceOrbit(object):
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'''
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Orbit for dealing with Spice bsp files.
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'''
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def __init__(self, spkfile):
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'''
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Constructor.
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'''
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self.spkfile = spkfile
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self.db = SpiceDatabase()
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def initSpice(self):
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ll = self.db.getList()
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for val in ll:
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SpiceyPy.furnsh(val)
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SpiceyPy.furnsh(self.spkfile)
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def interpolateOrbit(self, time, frame='ITRF93'):
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if frame not in ('ITRF93', 'J2000', 'ECI_TOD', 'ECLIPJ2000'):
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raise Exception('Currently only ITRF93/J2000 frames are supported.')
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et = SpiceyPy.str2et(str(time))
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res,lt = SpiceyPy.spkezr('-123710', et,
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frame, 'None', 'EARTH')
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sv = StateVector()
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sv.setTime(time)
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sv.setPosition([x*1000.0 for x in res[0:3]])
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sv.setVelocity([x*1000.0 for x in res[3:6]])
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return sv
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def loadHdrAsOrbit(fname, date=None):
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'''Read a hdr file and convert to ISCE orbit'''
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from isceobj.Orbit.Orbit import Orbit, StateVector
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if date is None:
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date = datetime.datetime.now().date()
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t0 = datetime.datetime(year=date.year,
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month = date.month,
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day = date.day)
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orb = Orbit()
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inData = np.loadtxt(fname)
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for line in inData:
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time = t0 + datetime.timedelta(seconds = line[0])
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sv = StateVector()
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sv.setTime(time)
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sv.setPosition(line[1:4].tolist())
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sv.setVelocity(line[4:7].tolist())
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orb.addStateVector(sv)
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print(sv)
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return orb
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def dumpOrbitToHdr(orbit, filename, date=None):
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'''
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Dump orbit to ROI_PAC style hdr file.
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'''
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if date is None:
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date = orbit._stateVectors[0].getTime().date()
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t0 = datetime.datetime(year = date.year,
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month = date.month,
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day = date.day)
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nVec = len(orbit._stateVectors)
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arr = np.zeros((nVec, 7))
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for ind,sv in enumerate(orbit._stateVectors):
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arr[ind][0] = (sv.getTime() - t0).total_seconds()
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arr[ind][1:4] = sv.getPosition()
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arr[ind][4:] = sv.getVelocity()
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np.savetxt(filename, arr, fmt='%10.6f')
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class ECI2ECEF(object):
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'''
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Class for converting Inertial orbits to ECEF orbits using JPL's SPICE library.
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'''
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def __init__(self, orbit, eci='J2000', ecef='ITRF93'):
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'''
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Currently J2000 and ITRF3 frames are supported by the SPICE library.
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'''
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self.eci = eci
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self.ecef = ecef
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self.orbit = orbit
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def convert(self):
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'''Convert ECI orbit to ECEF orbit.'''
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date = self.orbit._stateVectors[0].getTime().date()
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bspName = 'inertial_orbit_' + date.strftime('%Y%m%d') + '.bsp'
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####Convert ISCE orbit to SPICE orbit file
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sorb = ISCEOrbit(self.orbit)
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sorb.exportToSPK(bspName, frame=self.eci)
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####Convert coordinates with corrections
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spk = SpiceOrbit(bspName)
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spk.initSpice()
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wgsOrbit = Orbit()
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wgsOrbit.setOrbitSource( self.orbit.getOrbitSource())
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wgsOrbit.setOrbitQuality( self.orbit.getOrbitQuality())
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for sv in self.orbit:
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tim = sv.getTime()
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spksv = spk.interpolateOrbit(tim, frame=self.ecef)
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wgsOrbit.addStateVector(spksv)
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return wgsOrbit
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