  The three Laser Interferometer Space Antenna (LISA) spacecraft are going to
be placed in a triangular formation in an Earth-trailing or Earth-leading
orbit. They will be launched together on a single rocket and transferred to
that science orbit using Solar Electric Propulsion. Since the transfer $\Delta
v$ depends on the chosen science orbit, both transfer and science orbit have
been optimised together. For a thrust level of 90 mN, an allocation of 1092 m/s
per spacecraft is sufficient for an all-year launch in 2034. For every launch
month a dedicated science orbit is designed with a corner angle variation of
close to $60^\circ \pm 1.0^\circ$ and an arm length rate of maximum 10 m/s.
Moreover, a detailed navigation analysis of the science orbit insertion and the
impact on insertion errors on the constellation stability has been conducted.
The analysis shows that Range/Doppler measurements together with a series of
correction manoeuvres at the beginning of the science orbit phase can reduce
insertion dispersions to a level where corner angle variations remain at about
$60^\circ \pm 1.1^\circ$ at $99\%$ C.L.. However, the situation can become
significantly worse if the self-gravity accelerations acting during the science
orbit phase are not sufficiently characterised prior to science orbit
insertion.
