def pseudostart(self, jd, dv, phi, elv):
elv = math.radians(elv)
phi = math.radians(phi)
ldv = np.array([
dv * np.cos(elv) * np.cos(phi),
dv * np.cos(elv) * np.sin(phi),
dv * np.sin(elv)
])
bpos, bvel = self.spacebase.posvel(jd)
sunpos, sunvel = common.SPKposvel(10, jd)
return bpos, bvel + common.ldv2ecldv(ldv, bpos, bvel, sunpos, sunvel)
def _epacc(self, td, y, kernel):
# comupte acceleration of Electric Propulsion System
acc = np.array([
self._epdv * np.cos(self._epelv) * np.cos(self._epphi),
self._epdv * np.cos(self._epelv) * np.sin(self._epphi),
self._epdv * np.sin(self._epelv)
])
pos = y[0:3]
vel = y[3:6]
sunpos, sunvel = kernel[0, 10].compute_and_differentiate(td)
sunpos = common.eqn2ecl(sunpos) * 1000.0
sunvel = common.eqn2ecl(sunvel) * 1000.0 / common.secofday
return common.ldv2ecldv(acc, pos, vel, sunpos, sunvel)
def set_pred_dv(self, dv, phi, elv):
relv = math.radians(elv)
rphi = math.radians(phi)
ldv = np.array([
dv * np.cos(relv) * np.cos(rphi),
dv * np.cos(relv) * np.sin(rphi),
dv * np.sin(relv)
])
self.pred_vel = self.pvel + \
common.ldv2ecldv(ldv, self.ppos, self.pvel, \
self.sunpos, self.sunvel)
jdsec = self.jd * common.secofday
pos = self.ppos - self.sunpos
vel = self.pred_vel - self.sunvel
self.orbit.setOrbCart(jdsec, pos, vel)
return
def exec_man(self, man, target, pbar=None, plabel=None, ptext=''):
if man['type'] != 'START' and not self.onflight:
return False, self.errormes06.format(man['type'])
if man['type'] == 'START' and self.onflight:
return False, self.errormes07.format(man['type'])
cman = man.copy()
cman['epon'] = False
cman['epdvpd'] = 0.0
cman['epmode'] = 'L'
cman['sson'] = False
cman['ssmode'] = 'L'
status = np.zeros(7)
tsjd, tejd = target.getsejd()
if man['type'] == 'START':
self.jd = man['time']
if self.jd < tsjd or self.jd >= tejd:
return False, self.errormes05
self.pos, self.vel = self.pseudostart(self.jd, dv=man['dv'],
elv=man['elv'], phi=man['phi'])
self.orbit.setCurrentCart(self.jd*common.secofday, self.pos,
self.vel)
self.onflight = True
status[0] = self.jd
status[1:4] = self.pos.copy()
status[4:] = self.vel.copy()
self.get_epssstatus(cman)
self.trj_record.append([cman, status])
return True, ''
elif man['type'] == 'CP':
dv = man['dv']
elv = math.radians(man['elv'])
phi = math.radians(man['phi'])
ldv = np.array([ \
dv * np.cos(elv) * np.cos(phi), \
dv * np.cos(elv) * np.sin(phi), \
dv * np.sin(elv) \
])
sunpos, sunvel = common.SPKposvel(10, self.jd)
self.vel += common.ldv2ecldv(ldv, self.pos, self.vel, sunpos,
sunvel)
self.orbit.setCurrentCart(self.jd*common.secofday, self.pos,
self.vel)
status[0] = self.jd
status[1:4] = self.pos.copy()
status[4:] = self.vel.copy()
self.get_epssstatus(cman)
self.trj_record.append([cman, status])
self.accumdv['CP'] += dv
return True, ''
elif man['type'] == 'EP_ON':
dv = man['dvpd'] / common.secofday
phi = math.radians(man['phi'])
elv = math.radians(man['elv'])
self.orbit.set_epstatus(True, dv, phi, elv, man['tvmode'],
common.SPKkernel)
status[0] = self.jd
status[1:4] = self.pos.copy()
status[4:] = self.vel.copy()
self.get_epssstatus(cman)
self.trj_record.append([cman, status])
return True, ''
elif man['type'] == 'EP_OFF':
self.orbit.set_epstatus(False, 0.0, 0.0, 0.0)
status[0] = self.jd
status[1:4] = self.pos.copy()
status[4:] = self.vel.copy()
self.get_epssstatus(cman)
self.trj_record.append([cman, status])
return True, ''
elif man['type'] == 'SS_ON':
area = man['area']
theta = math.radians(man['theta'])
elv = math.radians(man['elv'])
self.orbit.set_ssstatus(True, area, theta, elv, man['tvmode'],
common.SPKkernel)
status[0] = self.jd
status[1:4] = self.pos.copy()
status[4:] = self.vel.copy()
self.get_epssstatus(cman)
self.trj_record.append([cman, status])
return True, ''
elif man['type'] == 'SS_OFF':
self.orbit.set_ssstatus(False, 0.0, 0.0, 0.0)
status[0] = self.jd
status[1:4] = self.pos.copy()
status[4:] = self.vel.copy()
self.get_epssstatus(cman)
self.trj_record.append([cman, status])
return True, ''
elif man['type'] == 'FLYTO':
jdto = man['time']
if jdto < self.jd:
return False, self.errormes01
if jdto >= tejd:
return False, self.errormes02
duration = jdto - self.jd
if pbar is not None:
pbar.setVisible(True)
pbar.setValue(0)
plabel.setText(ptext)
inter = man['inter'] * common.secofday
secto = jdto * common.secofday
pt, px, py, pz, pxd, pyd, pzd, ssdvpd, runerror = self.orbit.trj(
secto, inter, common.SPKkernel, common.planets_grav,
common.planets_mu, common.integ_abs_tol, common.integ_rel_tol,
pbar)
if pbar is not None:
pbar.setVisible(False)
plabel.setText('')
if runerror:
lastsuccess = 0.0
length = len(pt)
for i in range(length):
if pt[i] < 1.0: break
lastsuccess = pt[i]
lastsuccess = lastsuccess / common.secofday
return False, self.errormes04.format(common.jd2isot(lastsuccess))
pt = pt / common.secofday
self.get_epssstatus(cman)
self.trj_record.append([cman, pt, px, py, pz, pxd, pyd, pzd,
ssdvpd])
self.jd = pt[-1]
self.pos = np.array([px[-1], py[-1], pz[-1]])
self.vel = np.array([pxd[-1], pyd[-1], pzd[-1]])
self.orbit.setCurrentCart(self.jd*common.secofday, self.pos,
self.vel)
if cman['epon']:
self.accumdv['EP'] += duration * cman['epdvpd']
if cman['sson']:
ssdv = man['inter'] * ssdvpd[0]
for i in range(1, len(pt)):
ssdv += (pt[i] -pt[i-1]) * ssdvpd[i]
self.accumdv['SS'] += ssdv
return True, ''
else:
return False, self.errormes03.format(man['type'])
def computefta(self):
norm = lambda x: x / np.sqrt(np.dot(x, x))
if g.showorbitcontrol is None:
QMessageBox.information(self, self.mbTtl07, self.mbMes07,
QMessageBox.Ok)
return
ftadialog = FTAsettingDialog(self)
ans = ftadialog.exec_()
if ans == QDialog.Rejected:
return
jd = g.fta_parameters[0]
tpos, tvel = g.mytarget.posvel(jd)
sunpos, sunvel = common.SPKposvel(10, jd)
if g.fta_parameters[1] == 'OL':
sr = g.fta_parameters[2][1]
sphi = g.fta_parameters[2][2]
selv = g.fta_parameters[2][3]
vect = common.polar2rect(sr, sphi, selv)
delta_pos = common.ldv2ecldv(vect, tpos, tvel, sunpos, sunvel)
tepos = tpos + delta_pos
try:
dv, phi, elv = g.showorbitcontrol.tbpred.fta(jd, tepos)
except ValueError:
QMessageBox.information(self, self.mbTtl07, self.mbMes08,
QMessageBox.Ok)
return
dv = round(dv, 3)
phi = round(phi, 2)
elv = round(elv, 2)
mes = self.mbMes09.format(str(dv), str(phi), str(elv))
ans = QMessageBox.question(self, self.mbTtl09, mes,
QMessageBox.Ok | QMessageBox.Cancel,
QMessageBox.Cancel)
if ans == QMessageBox.Ok:
self.editman['dv'] = dv
self.editman['phi'] = phi
self.editman['elv'] = elv
self.dispman()
self.dispSysMes(self.sysMes02)
self.showorbit()
if g.options['log']:
logstring = []
logstring.append('apply FTA result: ' + nowtimestr() +
'\n')
logstring.append(' target: ' + g.mytarget.name + '\n')
logstring.append(' time to arrival: ' +
str(g.fta_parameters[2][0]) + '\n')
logstring.append(' Type of Precise Targeting: ' +
'OL coordinates or Center' + '\n')
logstring.append(' offset distance: ' +
str(g.fta_parameters[2][1] / 1000.0) +
'\n')
logstring.append(' phi: ' +
str(g.fta_parameters[2][2]) + '\n')
logstring.append(' elv: ' +
str(g.fta_parameters[2][3]) + '\n')
logstring.append(' result dv: ' + str(dv) + '\n')
logstring.append(' result phi: ' + str(phi) + '\n')
logstring.append(' result elv: ' + str(elv) + '\n')
g.logfile.writelines(logstring)
g.logfile.flush()
elif g.fta_parameters[1] == 'BP':
# compute terminal velocity at Target
tepos = tpos + np.zeros(3)
try:
dv, phi, elv, bc_ivel, bc_tvel \
= g.showorbitcontrol.tbpred.ftavel(jd, tepos)
except ValueError:
QMessageBox.information(self, self.mbTtl07, self.mbMes08,
QMessageBox.Ok)
return
# compute B-Plane Unit Vectors
uSvec = norm(bc_tvel - tvel)
ss_tpos = tpos - sunpos
ss_tvel = tvel - sunvel
hvec = np.cross(ss_tpos, ss_tvel)
uTvec = norm(np.cross(uSvec, hvec))
uRvec = norm(np.cross(uSvec, uTvec))
# get Precise Targeting Parameters
sr = g.fta_parameters[2][1]
sbeta = g.fta_parameters[2][2]
rbeta = math.radians(sbeta)
# compute delta_pos
delta_pos = sr * (np.cos(rbeta) * uTvec + np.sin(rbeta) * uRvec)
# FTA computing
tepos = tpos + delta_pos
try:
dv, phi, elv = g.showorbitcontrol.tbpred.fta(jd, tepos)
except ValueError:
QMessageBox.information(self, self.mbTtl07, self.mbMes08,
QMessageBox.Ok)
return
dv = round(dv, 3)
phi = round(phi, 2)
elv = round(elv, 2)
mes = self.mbMes09.format(str(dv), str(phi), str(elv))
ans = QMessageBox.question(self, self.mbTtl09, mes,
QMessageBox.Ok | QMessageBox.Cancel,
QMessageBox.Cancel)
if ans == QMessageBox.Ok:
self.editman['dv'] = dv
self.editman['phi'] = phi
self.editman['elv'] = elv
self.dispman()
self.dispSysMes(self.sysMes02)
self.showorbit()
if g.options['log']:
logstring = []
logstring.append('apply FTA result: ' + nowtimestr() +
'\n')
logstring.append(' target: ' + g.mytarget.name + '\n')
logstring.append(' time to arrival: ' +
str(g.fta_parameters[2][0]) + '\n')
logstring.append(' Type of Precise Targeting: ' +
'BP (B-plane coordinates)' + '\n')
logstring.append(' offset distance: ' +
str(g.fta_parameters[2][1] / 1000.0) +
'\n')
logstring.append(' beta: ' +
str(g.fta_parameters[2][2]) + '\n')
logstring.append(' result dv: ' + str(dv) + '\n')
logstring.append(' result phi: ' + str(phi) + '\n')
logstring.append(' result elv: ' + str(elv) + '\n')
g.logfile.writelines(logstring)
g.logfile.flush()