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Take a look at these two: http://esa.github.io/pykep/ by ESA Advanced Concepts Team licensed under the GNU General Public License v3.0. At the library core is the implementation of an efficient solver for the multiple revolutions Lambert’s problem, objects representing direct (Sims-Flanagan), indirect (Pontryagin) and hybrid methods to represent low-thrust ...


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You've fully described the first orbit (assuming 2D), and have fixed two of the three parameters of the second orbit, leaving the perigee to float. I assume you only care about hitting the apogee exactly at 60 degrees. The minimum impulsive thrust will occur will occur when the new orbit is tangential to the old orbit, so you are thrusting directly along ...


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Yes, this is not a full answer, but maybe my thoughts will help you to work out the solution by yourself. Or someone else will connect the loose threads: First of all I recommend another notation: "R" should be reserved for the distance between the object and the orbits focus so I recommend using "Alt" instead. "RA" is common ...


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The trouble with optimizing low-thrust trajectories is there are so many different possible maneuver profiles that it is very hard to tell whether there might be a better answer hiding behind a slightly different parameterization of the motion. You can find the best choice out of all the options you considered in your model (much easier in some cases than ...


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There are too many variables, some of them infinitely variable, to arrive at the optimal burn plan. And then you need to incorporate that burn plan into something that can be carried out with a reasonably priced computer (US $200K is "reasonably priced) than can handle high level radiation. This is not going to be a state of the art computer. What you ...


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