Conceptual Overview on Development of Methodologies for Direct Interplanetary

Abstract

Highly effective electric propulsion systems can be employed in interplanetary missions to shorten the journey time or enhance the mass delivered to the destination compared to conventional chemical propulsion systems. Growing concerns about possible habitable environments and the possibility of Earthly species contaminating them are brought about by the rapid speed of scientific discovery of our solar system. Key approaches include gravity assist maneuvers, Hohmann Transfer Orbit, and Patched-Conic Approximation. Multiple gravity-assist trajectory preliminary design is formulated as a global optimization problem. Next, a trajectory model is described, which strikes a balance between the difficulty of the optimization problem and the completeness of the model. Investigating the final resolution space is carried out using a unique global search strategy. The spacecraft travels from the departure planet's parking orbit to the arrival planet's parking orbit during a direct interplanetary transfer. It is necessary to construct the transfer trajectory in a way that ensures the stated arrival parking orbit criteria are met. For a predetermined departure in a direct transfer, four different transfer trajectory design alternatives are depending on the period and flight time. These design choices are not identified by the most popular analytical trajectory design method, the standard patched pop method.