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.