def _mga_incipit_cstrs_ctor(self,
seq=[gtoc6('io'),
gtoc6('io'),
gtoc6('europa')],
t0=[epoch(7305.0), epoch(11323.0)],
tof=[[100, 200], [3, 200], [4, 100]],
Tmax=300.00,
Dmin=2.0):
"""
USAGE: mga_incipit_cstrs(seq = [gtoc6('io'),gtoc6('io'),gtoc6('europa')], t0 = [epoch(6905.0),epoch(11323.0)], tof = [[100,200],[3,200],[4,100]], Tmax = 365.25, Dmin = 0.2)
* seq: list of jupiter moons defining the trajectory incipit
* t0: list of two epochs defining the launch window
* tof: list of n lists containing the lower and upper bounds for the legs flight times (days)
"""
# We construct the arg list for the original constructor exposed by
# boost_python
arg_list = []
arg_list.append(seq)
arg_list.append(t0[0])
arg_list.append(t0[1])
arg_list.append(tof)
arg_list.append(Tmax)
arg_list.append(Dmin)
self._orig_init(*arg_list)
def _mga_incipit_cstrs_ctor(
self, seq=[
gtoc6('io'), gtoc6('io'), gtoc6('europa')], t0=[
epoch(7305.0), epoch(11323.0)], tof=[
[
100, 200], [
3, 200], [
4, 100]], Tmax=300.00, Dmin=2.0):
"""
USAGE: mga_incipit_cstrs(seq = [gtoc6('io'),gtoc6('io'),gtoc6('europa')], t0 = [epoch(6905.0),epoch(11323.0)], tof = [[100,200],[3,200],[4,100]], Tmax = 365.25, Dmin = 0.2)
* seq: list of jupiter moons defining the trajectory incipit
* t0: list of two epochs defining the launch window
* tof: list of n lists containing the lower and upper bounds for the legs flight times (days)
"""
# We construct the arg list for the original constructor exposed by
# boost_python
arg_list = []
arg_list.append(seq)
arg_list.append(t0[0])
arg_list.append(t0[1])
arg_list.append(tof)
arg_list.append(Tmax)
arg_list.append(Dmin)
self._orig_init(*arg_list)
def _mga_part_ctor(self,
seq=[gtoc6('europa'),
gtoc6('europa'),
gtoc6('europa')],
tof=[[5, 50], [5, 50]],
t0=epoch(11000),
v_inf_in=[1500.0, 350.0, 145.0]):
"""
USAGE: mga_part(seq = [gtoc6('europa'),gtoc6('europa'),gtoc6('europa')], tof = [[5,50],[5,50]], t0 = epoch(11000), v_inf_in[1500.0,350.0,145.0])
* seq: list of jupiter moons defining the trajectory incipit
* tof: list of n lists containing the lower and upper bounds for the legs flight times (days)
* t0: starting epoch
* v_inf_in: Incoming spacecraft relative velocity
"""
# We construct the arg list for the original constructor exposed by
# boost_python
arg_list = []
arg_list.append(seq)
arg_list.append(tof)
arg_list.append(t0)
arg_list.append(v_inf_in)
self._orig_init(*arg_list)
def _mga_part_ctor(
self, seq=[
gtoc6('europa'), gtoc6('europa'), gtoc6('europa')], tof=[
[
5, 50], [
5, 50]], t0=epoch(11000), v_inf_in=[
1500.0, 350.0, 145.0]):
"""
USAGE: mga_part(seq = [gtoc6('europa'),gtoc6('europa'),gtoc6('europa')], tof = [[5,50],[5,50]], t0 = epoch(11000), v_inf_in[1500.0,350.0,145.0])
* seq: list of jupiter moons defining the trajectory incipit
* tof: list of n lists containing the lower and upper bounds for the legs flight times (days)
* t0: starting epoch
* v_inf_in: Incoming spacecraft relative velocity
"""
# We construct the arg list for the original constructor exposed by
# boost_python
arg_list = []
arg_list.append(seq)
arg_list.append(tof)
arg_list.append(t0)
arg_list.append(v_inf_in)
self._orig_init(*arg_list)
