I am interested in knowing whether GMAT is able to compute finite burn low-thrust trajectories. The trajectory may either be feasible (e.g. computed via differential correction) or optimal (e.g., uses optimal control theory and minimizes or maximizes a performance index).

In particular, I am wondering whether I can specify an initial spacecraft state, a time of flight, a final spacecraft state, and thruster parameters (e.g., Isp, max. thrust) and have GMAT then compute the time history of thrust direction and magnitude that will take the spacecraft from the initial to final state whilst respecting all other constraints -or- tell me that a feasible solution does not exist for the states and constraints I specified. I am primarily interested in interplanetary trajectories (heliocentric inertial frame, J2000 ecliptic coordinates). Also, the force model can be as simple as restricted two-body gravitation with the Sun as the central body.