# Tools for low-thrust trajectory optimization

I'm performing a transfer between Near-Earth orbits considering J2 perturbation with the low-thrust engine. Orbital parameters:

1st orbit:

• Apogee altitude - 300 km
• Perigee altitude - 200 km
• Inclination - 63 deg
• Argument of perigee - 300 deg
• RAAN is free

2nd orbit:

• Apogee altitude - 8000 km
• Perigee altitude - 600 km
• Inclination - 63 deg
• Argument of perigee - 270 deg
• RAAN is free

Considering 2 scenarios of optimization: minimum transfer time and minimum propellant usage.

Spacecraft parameters:

• Fuel mass: 500 kg
• Dry mass: 1000 kg
• Engine: constant thrust (0.3 N) and Isp (1000 s).

Which open source tools may be implemented to calculate the mentioned scenarios? Expected outputs are transfer duration and revolutions number, total dV, propellant consumption, and different graphs, representing the transfer.

I've implemented MIPELEC by CNES, however, it performs only minimum-time scenario and doesn't take into account perturbations. Also, I've checked pykep and MOLTO-IT, but couldn't implement them for this problem.

• What is it, you're trying to achieve? Is this about actual rocketry or simulations? I feel like this post lacks some clarity... Sep 14, 2020 at 18:37
• @finnmglas the question seeks software in order to achieve "...a transfer between 2 coplanar Earth orbits considering J2, Moon and Sun perturbations with the low-thrust engine" using "open source software, which would find the optimal solution for this case" A reasonable bit of software would allow for an optimization criteria to be specified at run time with limits on delta-v and total time and allow for constraints on maximum thrust, Isp and $\Delta m$. The question is absolutely clear about this!
– uhoh
Sep 15, 2020 at 0:24
• @Leeloo have a look at poliastro, referenced in [How does the poliastro python package “Going to Mars with Python” example work? What's it really doing? ](space.stackexchange.com/q/28228/12102) I think it may address low thrust optimization, but I'm not sure.
– uhoh
Sep 15, 2020 at 0:31
• @uhoh Unfortunately, poliastro doesn't have low-thrust optimization, but I've used it's Lambert solver for impulsive solution. Sep 15, 2020 at 7:49
• @finnmglas No, I don't have a real satellite on a orbit ))) I'm working on a mathematical problem. Sep 15, 2020 at 7:50