def run(self):
try:
K = 5 #sample density and decay rate
N = 1 #how many solutions to keep
ITERS = 2 #for descent minimization
tE, tL = self.earliest, self.latest
GM = self.sun.Gmass[0]
F = lambda t0, T: direct_transfer_cost(self.departure, self.
arrival, t0, T, GM)[0]
C = lambda t0, T: t0 + T < tL
#sample for initial conditions
inits = []
for i in range(K):
for j in range(K):
t0_ = tE + (tL - tE) * i / K
T_ = (tL - t0_) * j / K
dV = F(t0_, T_)
if dV: inits.append([dV, t0_, T_])
inits = sorted(inits, key=lambda x: x[0])
#descend to local minima
ranges = [[tE, tL], [timedelta(days=0), tL - tE]]
steps = [(tL - tE) / K / K, (tL - tE) / K / K]
solutions = []
for initial in inits[:N]:
pinit = initial[1:]
res = decaying_descent(F,
ranges,
steps,
pinit,
condition=C,
iters=ITERS,
decay_factor=K)
dV, solution = direct_transfer_cost(self.departure,
self.arrival, res[0],
res[1], GM)
solutions.append([dV, res[0], res[1], solution])
solutions = sorted(solutions, key=lambda x: x[0])
global results
results = [
path(t0, dV, T, [t0], [
trajectory(
self.sun, t0,
np.concatenate(
(self.departure.state(t0)[:3], sol['v1'])), t0 + T)
]) for dV, t0, T, sol in solutions
]
except Exception as e:
print('error:', e)
self.signals.error.emit(69)
traceback.print_last()
except Warning as e:
print('error:', e)
self.signals.error.emit(420)
traceback.print_last()
else:
self.signals.finished.emit()
def paintGL(self):
global drawables
global window
window.status.showMessage("drawing")
global viewTime
global selectedSolution
#all the planets
for i in vis.planets:
if i == 'SUN':
up = [0, 0, 1]
traj = None
else:
#up = np.cross(vis.planets[i].body.state(viewTime)[0:3], vis.planets[i].body.state(viewTime)[4:6])
#up /= np.linalg.norm(up)
global ephem
traj = trajectory(vis.planets['SUN'].body, viewTime,
vis.planets[i].body.state(viewTime))
up = traj.up
global defaultTrajColor
#color, foc, ecc, matrix, a, angleIn=0, angleOut=0
trajDraw = vis.orbit(defaultTrajColor, [0, 0, 0], traj.rMtrx,
traj.elements['A'], traj.elements['ECC'])
drawables.append(vis.drawable(trajDraw))
"""
#for demo purpose (of prediction error):
if not selectedSolution == None:
traj0 = trajectory(vis.planets['SUN'].body, selectedSolution.launch, vis.planets[i].body.state(selectedSolution.launch))
T = (viewTime - selectedSolution.launch).total_seconds()
drawables.append(vis.drawable(vis.probe(), traj0.relPosition(T)))"""
# position upwards direction
drawables.append(
vis.drawable(vis.planets[i],
vis.planets[i].body.state(viewTime)[0:3], up))
"""
#all other trajectories
if not selectedSolution == None:
index = 0
global trajColors
for i, tr in enumerate(selectedSolution.trajectories):
global flightPathColor
iOrbit = vis.orbit(flightPathColor, tr.body.state(selectedSolution.entranceTimes[i])[0:3], tr.rMtrx, tr.elements['A'], tr.elements['ECC'], tr.angleIn, tr.angleOut)
drawables.append(vis.drawable(iOrbit))
deltaT = (viewTime - selectedSolution.launch).total_seconds()
#print('launch at ',selectedSolution.launch,', viewing at ',viewTime)
#print("t = ", deltaT, "s, at ", selectedSolution.getPosition(deltaT), " on orbit around ", selectedSolution.getTrajectory(deltaT).body.name)
#print('------')"""
#the probe itself
if not selectedSolution == None:
deltaT = (viewTime - selectedSolution.launch).total_seconds()
position = selectedSolution.getPosition(deltaT)
global probePositions
drawables.append(
vis.drawable(vis.probePath(probePathColor, probePositions)))
drawables.append(vis.drawable(vis.probe(), pos=position))
vis.draw(drawables)
drawables = []
window.status.showMessage("solar system at: " +
viewTime.strftime("%Y-%m-%d"))
def voyager2_original(ephem):
earth = ephem.get_body('EARTH')
jupiter = ephem.get_body('JUPITER')
saturn = ephem.get_body('SATURN')
uranus = ephem.get_body('URANUS')
neptune = ephem.get_body('NEPTUNE')
sun = ephem.get_body('SUN')
def convert(dateObj):
return sp.str2et(dateObj.strftime("%Y %b %d %H:%M:%S").lower())
voyst2 = lambda t: sp.spkezr('VOYAGER 2', convert(t), 'J2000', 'LT+S',
'SOLAR SYSTEM BARYCENTER')[0]
D = 10
tfE = datetime(1977, 8, 21, 16, 40)
t0J = datetime(1979, 5, 6, 15, 33)
tfJ = datetime(1979, 9, 12, 22, 19)
t0S = datetime(1981, 6, 29, 17, 20)
tfS = datetime(1981, 10, 22, 18, 26)
t0U = datetime(1985, 12, 15, 5, 6)
tfU = datetime(1986, 3, 6, 13, 52)
t0N = datetime(1989, 6, 26, 12, 6)
tfN = datetime(1989, 10, 24, 7, 6)
timesE2J = []
trajE2J = []
for i in range(D):
tE2J = (t0J - tfE) * i / D + tfE
state = voyst2(tE2J)
timesE2J.append(tE2J)
trajE2J.append(trajectory(sun, tE2J, state, tE2J + (t0J - tfE) / D))
#swingby at jupiter
trajByJ = trajectory(jupiter, t0J, voyst2(t0J) - jupiter.state(t0J), tfJ)
#jupiter to saturn
timesJ2S = []
trajJ2S = []
for i in range(D):
tJ2S = (t0S - tfJ) * i / D + tfJ
state = voyst2(tJ2S)
timesJ2S.append(tJ2S)
trajJ2S.append(trajectory(sun, tJ2S, state, tJ2S + (t0S - tfJ) / D))
#swingby at saturn
trajByS = trajectory(saturn, t0S, voyst2(t0S) - saturn.state(t0S), tfS)
#saturn to uranus
timesS2U = []
trajS2U = []
for i in range(D):
tS2U = (t0U - tfS) * i / D + tfS
state = voyst2(tS2U)
timesS2U.append(tS2U)
trajS2U.append(trajectory(sun, tS2U, state, tS2U + (t0U - tfS) / D))
#swingby at uranus
trajByU = trajectory(uranus, t0U, voyst2(t0U) - uranus.state(t0U), tfU)
#uranus to neptune
timesU2N = []
trajU2N = []
for i in range(D):
tU2N = (t0N - tfU) * i / D + tfU
state = voyst2(tU2N)
timesU2N.append(tU2N)
trajU2N.append(trajectory(sun, tU2N, state, tU2N + (t0N - tfU) / D))
#swingby at neptune
trajByN = trajectory(neptune, t0N, voyst2(t0N) - neptune.state(t0N), tfN)
#after neptune
after = timedelta(days=1500)
trajAftN = trajectory(sun, tfN, voyst2(tfN), tfN + after)
entranceTimes = []
entranceTimes.extend(timesE2J)
entranceTimes.append(t0J)
entranceTimes.extend(timesJ2S)
entranceTimes.append(t0S)
entranceTimes.extend(timesS2U)
entranceTimes.append(t0U)
entranceTimes.extend(timesU2N)
entranceTimes.append(t0N)
entranceTimes.append(tfN)
trajs = []
trajs.extend(trajE2J)
trajs.append(trajByJ)
trajs.extend(trajJ2S)
trajs.append(trajByS)
trajs.extend(trajS2U)
trajs.append(trajByU)
trajs.extend(trajU2N)
trajs.append(trajByN)
trajs.append(trajAftN)
voyager = path(launchTime=tfE,
deltaV='Original',
duration=tfN - tfE + after,
entranceTimes=entranceTimes,
trajectories=trajs)
return voyager
def voyager2_recreated(ephem):
earth = ephem.get_body('EARTH')
jupiter = ephem.get_body('JUPITER')
saturn = ephem.get_body('SATURN')
uranus = ephem.get_body('URANUS')
neptune = ephem.get_body('NEPTUNE')
sun = ephem.get_body('SUN')
def convert(dateObj):
return sp.str2et(dateObj.strftime("%Y %b %d %H:%M:%S").lower())
voyst2 = lambda t: sp.spkezr('VOYAGER 2', convert(t), 'J2000', 'LT+S',
'SOLAR SYSTEM BARYCENTER')[0]
D = 10
tfE = datetime(1977, 8, 21, 16, 40)
t0J = datetime(1979, 5, 6, 15, 33)
tfJ = datetime(1979, 9, 12, 22, 19)
t0S = datetime(1981, 6, 29, 17, 20)
tfS = datetime(1981, 10, 22, 18, 26)
t0U = datetime(1985, 12, 15, 5, 6)
tfU = datetime(1986, 3, 6, 13, 52)
t0N = datetime(1989, 6, 26, 12, 6)
tfN = datetime(1989, 10, 24, 7, 6)
timesE2J = []
trajE2J = []
for i in range(D):
tE2J = (t0J - tfE) * i / D + tfE
state = voyst2(tE2J)
timesE2J.append(tE2J)
trajE2J.append(trajectory(sun, tE2J, state, tE2J + (t0J - tfE) / D))
#swingby at jupiter
st0J = voyst2(t0J) - jupiter.state(t0J)
stfJ = voyst2(tfJ) - jupiter.state(tfJ)
GMJ = jupiter.const('GM', 1)[0]
def dVJ(th1, th2):
enpt = entrance(Rsoi['JUPITER'], st0J[3:], th1, th2)
exst = swingby(Rsoi['JUPITER'], np.concatenate((enpt, st0J[3:])), GMJ)
return np.linalg.norm(stfJ[3:] - exst[3:])
th1J, th2J = decaying_descent(dVJ, [[-np.pi, np.pi], [-np.pi, np.pi]],
[0.2, 0.2], [np.pi / 20, 0],
None,
iters=5,
decay_factor=5)
enptJ = entrance(Rsoi['JUPITER'], st0J[3:], th1J, th2J)
sIntoJ = np.concatenate((enptJ, st0J[3:]))
trajByJ = trajectory(jupiter, t0J, sIntoJ, tfJ)
#jupiter to saturn
timesJ2S = []
trajJ2S = []
for i in range(D):
tJ2S = (t0S - tfJ) * i / D + tfJ
state = voyst2(tJ2S)
timesJ2S.append(tJ2S)
trajJ2S.append(trajectory(sun, tJ2S, state, tJ2S + (t0S - tfJ) / D))
#swingby at saturn
st0S = voyst2(t0S) - saturn.state(t0S)
stfS = voyst2(tfS) - saturn.state(tfS)
GMS = saturn.const('GM', 1)[0]
def dVS(th1, th2):
enpt = entrance(Rsoi['SATURN'], st0S[3:], th1, th2)
exst = swingby(Rsoi['SATURN'], np.concatenate((enpt, st0S[3:])), GMS)
return np.linalg.norm(stfS[3:] - exst[3:])
th1S, th2S = decaying_descent(dVS, [[-np.pi, np.pi], [-np.pi, np.pi]],
[0.2, 0.2], [np.pi / 20, 0],
None,
iters=5,
decay_factor=5)
enptS = entrance(Rsoi['SATURN'], st0S[3:], th1S, th2S)
sIntoS = np.concatenate((enptS, st0S[3:]))
trajByS = trajectory(saturn, t0S, sIntoS, tfS)
#saturn to uranus
timesS2U = []
trajS2U = []
for i in range(D):
tS2U = (t0U - tfS) * i / D + tfS
state = voyst2(tS2U)
timesS2U.append(tS2U)
trajS2U.append(trajectory(sun, tS2U, state, tS2U + (t0U - tfS) / D))
#swingby at uranus
st0U = voyst2(t0U) - uranus.state(t0U)
stfU = voyst2(tfU) - uranus.state(tfU)
GMU = uranus.const('GM', 1)[0]
def dVU(th1, th2):
enpt = entrance(Rsoi['URANUS'], st0U[3:], th1, th2)
exst = swingby(Rsoi['URANUS'], np.concatenate((enpt, st0U[3:])), GMU)
return np.linalg.norm(stfU[3:] - exst[3:])
th1U, th2U = decaying_descent(dVU, [[-np.pi, np.pi], [-np.pi, np.pi]],
[0.2, 0.2], [np.pi / 20, 0],
None,
iters=5,
decay_factor=5)
enptU = entrance(Rsoi['URANUS'], st0U[3:], th1U, th2U)
sIntoU = np.concatenate((enptU, st0U[3:]))
trajByU = trajectory(uranus, t0U, sIntoU, tfU)
#uranus to neptune
timesU2N = []
trajU2N = []
for i in range(D):
tU2N = (t0N - tfU) * i / D + tfU
state = voyst2(tU2N)
timesU2N.append(tU2N)
trajU2N.append(trajectory(sun, tU2N, state, tU2N + (t0N - tfU) / D))
#swingby at neptune
st0N = voyst2(t0N) - neptune.state(t0N)
stfN = voyst2(tfN) - neptune.state(tfN)
GMN = neptune.const('GM', 1)[0]
def dVN(th1, th2):
enpt = entrance(Rsoi['NEPTUNE'], st0N[3:], th1, th2)
exst = swingby(Rsoi['NEPTUNE'], np.concatenate((enpt, st0N[3:])), GMN)
return np.linalg.norm(stfN[3:] - exst[3:])
th1N, th2N = decaying_descent(dVN, [[-np.pi, np.pi], [-np.pi, np.pi]],
[0.2, 0.2], [np.pi / 20, 0],
None,
iters=5,
decay_factor=5)
enptN = entrance(Rsoi['NEPTUNE'], st0N[3:], th1N, th2N)
sIntoN = np.concatenate((enptN, st0N[3:]))
trajByN = trajectory(neptune, t0N, sIntoN, tfN)
#after neptune
after = timedelta(days=1500)
trajAftN = trajectory(sun, tfN, voyst2(tfN), tfN + after)
entranceTimes = []
entranceTimes.extend(timesE2J)
entranceTimes.append(t0J)
entranceTimes.extend(timesJ2S)
entranceTimes.append(t0S)
entranceTimes.extend(timesS2U)
entranceTimes.append(t0U)
entranceTimes.extend(timesU2N)
entranceTimes.append(t0N)
entranceTimes.append(tfN)
trajs = []
trajs.extend(trajE2J)
trajs.append(trajByJ)
trajs.extend(trajJ2S)
trajs.append(trajByS)
trajs.extend(trajS2U)
trajs.append(trajByU)
trajs.extend(trajU2N)
trajs.append(trajByN)
trajs.append(trajAftN)
voyager = path(launchTime=tfE,
deltaV='Recreated',
duration=tfN - tfE + after,
entranceTimes=entranceTimes,
trajectories=trajs)
return voyager
def voyager1_recreated(ephem):
earth = ephem.get_body('EARTH')
jupiter = ephem.get_body('JUPITER')
saturn = ephem.get_body('SATURN')
sun = ephem.get_body('SUN')
def convert(dateObj):
return sp.str2et(dateObj.strftime("%Y %b %d %H:%M:%S").lower())
voyst = lambda t: sp.spkezr('VOYAGER 1', convert(t), 'J2000', 'LT+S',
'SOLAR SYSTEM BARYCENTER')[0]
#earth to jupiter
D = 10
tfE = datetime(1977, 9, 6, 14, 54)
t0J = datetime(1979, 1, 16, 13, 54)
tfJ = datetime(1979, 4, 22, 11, 7)
t0S = datetime(1980, 10, 3, 1, 32)
tfS = datetime(1980, 12, 24, 4, 35)
timesE2J = []
trajE2J = []
for i in range(D):
tE2J = (t0J - tfE) * i / D + tfE
state = voyst(tE2J)
timesE2J.append(tE2J)
trajE2J.append(trajectory(sun, tE2J, state, tE2J + (t0J - tfE) / D))
#swingby at jupiter
st0J = voyst(t0J) - jupiter.state(t0J)
stfJ = voyst(tfJ) - jupiter.state(tfJ)
GMJ = jupiter.const('GM', 1)[0]
def dVJ(th1, th2):
enpt = entrance(Rsoi['JUPITER'], st0J[3:], th1, th2)
exst = swingby(Rsoi['JUPITER'], np.concatenate((enpt, st0J[3:])), GMJ)
return np.linalg.norm(stfJ[3:] - exst[3:])
th1J, th2J = decaying_descent(dVJ, [[-np.pi, np.pi], [-np.pi, np.pi]],
[0.2, 0.2], [np.pi / 20, 0],
None,
iters=5,
decay_factor=5)
enptJ = entrance(Rsoi['JUPITER'], st0J[3:], th1J, th2J)
sIntoJ = np.concatenate((enptJ, st0J[3:]))
trajByJ = trajectory(jupiter, t0J, sIntoJ, tfJ)
#jupiter to saturn
timesJ2S = []
trajJ2S = []
for i in range(D):
tJ2S = (t0S - tfJ) * i / D + tfJ
state = voyst(tJ2S)
timesJ2S.append(tJ2S)
trajJ2S.append(trajectory(sun, tJ2S, state, tJ2S + (t0S - tfJ) / D))
#swingby at saturn
st0S = voyst(t0S) - saturn.state(t0S)
stfS = voyst(tfS) - saturn.state(tfS)
GMS = saturn.const('GM', 1)[0]
def dVS(th1, th2):
enpt = entrance(Rsoi['SATURN'], st0S[3:], th1, th2)
exst = swingby(Rsoi['SATURN'], np.concatenate((enpt, st0S[3:])), GMS)
return np.linalg.norm(stfS[3:] - exst[3:])
th1S, th2S = decaying_descent(dVS, [[-np.pi, np.pi], [-np.pi, np.pi]],
[0.2, 0.2], [np.pi / 20, 0],
None,
iters=5,
decay_factor=5)
enptS = entrance(Rsoi['SATURN'], st0S[3:], th1S, th2S)
sIntoS = np.concatenate((enptS, st0S[3:]))
trajByS = trajectory(saturn, t0S, sIntoS, tfS)
#after saturn
after = timedelta(days=1500)
trajAftS = trajectory(sun, tfS, voyst(tfS), tfS + after)
entranceTimes = []
entranceTimes.extend(timesE2J)
entranceTimes.append(t0J)
entranceTimes.extend(timesJ2S)
entranceTimes.append(t0S)
entranceTimes.append(tfS)
trajs = []
trajs.extend(trajE2J)
trajs.append(trajByJ)
trajs.extend(trajJ2S)
trajs.append(trajByS)
trajs.append(trajAftS)
voyager = path(launchTime=tfE,
deltaV='Recreated',
duration=tfS - tfE + after,
entranceTimes=entranceTimes,
trajectories=trajs)
return voyager
def voyager1_original(ephem):
earth = ephem.get_body('EARTH')
jupiter = ephem.get_body('JUPITER')
saturn = ephem.get_body('SATURN')
sun = ephem.get_body('SUN')
def convert(dateObj):
return sp.str2et(dateObj.strftime("%Y %b %d %H:%M:%S").lower())
voyst = lambda t: sp.spkezr('VOYAGER 1', convert(t), 'J2000', 'LT+S',
'SOLAR SYSTEM BARYCENTER')[0]
#earth to jupiter
D = 10
tfE = datetime(1977, 9, 6, 14, 54)
t0J = datetime(1979, 1, 16, 13, 54)
tfJ = datetime(1979, 4, 22, 11, 7)
t0S = datetime(1980, 10, 3, 1, 32)
tfS = datetime(1980, 12, 24, 4, 35)
timesE2J = []
trajE2J = []
for i in range(D):
tE2J = (t0J - tfE) * i / D + tfE
state = voyst(tE2J)
timesE2J.append(tE2J)
trajE2J.append(trajectory(sun, tE2J, state, tE2J + (t0J - tfE) / D))
#swingby at jupiter
trajByJ = trajectory(jupiter, t0J, voyst(t0J) - jupiter.state(t0J), tfJ)
#jupiter to saturn
timesJ2S = []
trajJ2S = []
for i in range(D):
tJ2S = (t0S - tfJ) * i / D + tfJ
state = voyst(tJ2S)
timesJ2S.append(tJ2S)
trajJ2S.append(trajectory(sun, tJ2S, state, tJ2S + (t0S - tfJ) / D))
#swingby at saturn
trajByS = trajectory(saturn, t0S, voyst(t0S) - saturn.state(t0S), tfS)
#after saturn
after = timedelta(days=1500)
trajAftS = trajectory(sun, tfS, voyst(tfS), tfS + after)
entranceTimes = []
entranceTimes.extend(timesE2J)
entranceTimes.append(t0J)
entranceTimes.extend(timesJ2S)
entranceTimes.append(t0S)
entranceTimes.append(tfS)
trajs = []
trajs.extend(trajE2J)
trajs.append(trajByJ)
trajs.extend(trajJ2S)
trajs.append(trajByS)
trajs.append(trajAftS)
voyager = path(launchTime=tfE,
deltaV='Original',
duration=tfS - tfE + after,
entranceTimes=entranceTimes,
trajectories=trajs)
return voyager