The present investigation will focus on the formulation and analysis of possible abort modes during the Earth departure phase of manned Mars interplanetary transfers. Though of short duration, the departure phase encompasses a mission timeline where failures have frequently become manifest in historical manned spacecraft necessitating the inclusion of a departure phase abort capability. Investigated abort modes included aborts to atmospheric entry, and to Earth or Moon orbit. Considered interplanetary trajectory types included conjunction, opposition, and free-return trajectory classes. All abort modes were analyzed for aborts initiated at multiple points along each of these possible departure trajectories across all launch opportunities of the fifteen-year Earth-Mars inertial period. The consistently low departure velocities of the conjunction trajectories facilitated the greatest abort capability.
An analysis of Mars transportation architectures was performed to determine the amount of available delta V inherent in each candidate architecture for executing departure aborts. Results indicate that a delta V of at least 4 km/s is required to achieve a continuous departure phase entry abort capability with abort flights less than three weeks duration for all transfer opportunity years.
Author:- Dissel, Adam Frederik