Porkchop Plot of a Direct Earth-Mercury Trajectory using Lambert's Problem

Numerous space missions have minimal
energy requirements, which are calculated and stated as
rocket vehicle velocity requirements. This provides a
quick opportunity for an impression of the ideal vehicle
or an estimate of the payload capacity of a particular
vehicle. As we move closer to the inner planets of the
solar system, solar radiation's effects worsen and so do
the energy requirements. This energy need can be
reduced using flyby missions. A porkchop plot used in
orbital mechanics displays contours of even
characteristic energy based on numerous permutations
of the date of launch and the date of arrival for a precise
interplanetary voyage. The porkchop plot solutions,
decide the endurance of a launch window for a
particular spacecraft. In this study, the porkchop plots
for the Earth-Mercury direct transfer are plotted by
using the departure date, arrival date, and flight
duration as fixed values in the orbital components of the
solution, generally known as Lambert’s problem. For
this study, non – coplanar, non – circular orbits of the
planets are considered. The patched conic method is
used to create mission prospects. For the years 2021-
2030, porkchop plots are produced. The simulation
results utilizing Free flyer for this window are included.