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?