GMAT for optimizing ballistic missiles trajectories

Is it possible ?

Let's say I have the following ballistic missile:

Stage 1

Propellant mass = 610 kg

Empty mass = 400 kg

Total mass = 1010 kg

Burn time min = 3.1 seconds

Thrust max = 350 kN

Stage 2

Propellant mass = 715 kg

Empty mass + Payload = 675 kg

Total mass = 1390 kg

Burn time min = 44.6 sec

Thrust max = 35 kN

Total mass 2400 kg

Drag coefficient as a function of Mach number Cd(M) is known for Stage 1+ Stage 2 and also for Stage 2 alone.

Question:

Supposing the rocket is launched from parallel 45 eastward, toward a point situated also on parallel 45, find Thrust(t) in such a way that the missile hits the ground as far as possible from where it starts. Can GMAT solve such a problem?