The user can identify a mid course correction, or thrust, to be applied at some value between 0 and 2.0 km/sec. In addition, the actual design parameters of the flight path can be specified in a popup menu. These parameters describe the geometry of the trajectory near Earth and Mars, respectively, and - as you will see - have a significant affect upon the success of the mission!
Outputs
The program has an eleborate output scheme. There is a full written report that details all the critical milestones of the optimized trajectory - the coordinates of each thrust, when the spacecraft leaves Earth's gravitational field and enters a heliocentric ellipse centered at the Sun; and then when it enter's Mars' gravity.
There are also a total of eight plots that are generated for each flight path, detailing how the integrator works, and how the trajectory behaves near Earth or near Mars. On this particular plot, the "nominal" trajectory is shown in yellow. This same line is drawn on all the plots so you can see more clearly how drastically the flight path changes as the mission design inputs are varied.
Finally, the exact data for each plot are accessible, as described in "the code" tab.
