# Optimization of low-thrust in-plane maneuver

I have to build an optimal trajectory between two orbits, which are in one plane, but with different semi-major axis, argument of perigee and eccentricity.

I've read different articles regarding the low-thrust optimization techniques, and now I'm looking for an example solution.

I would appreciate for a link/paper describing an example solution of the above problem.

UPDATE

I have an impulsive solution of this problem. Is it possible to convert the impulsive solution to the low-thrust?

• I have not seen a conclusive proof even for the instantaneous variant: space.stackexchange.com/questions/16931/…, despite spending a lot of rep trying to attract a proof. Sep 1, 2020 at 16:02
• Also, the geometry of such orbits: math.stackexchange.com/questions/2168522/… Sep 1, 2020 at 16:04
• @SE-stopfiringthegoodguys - A bi-elliptical transfer to which you alluded involves three instantaneous burns, while a bi-tangential transfer involves only two. (A Hohmann transfer is a special case of a a bi-tangential transfer.) There are cases where a bi-elliptical transfer requires less delta V than a bi-tangential transfer, at the expense of taking more time, sometimes significantly more time. Sep 1, 2020 at 16:22
• @DavidHammen bi-elliptical transfers (with infinite apoapsis always minimizing delta-v), is in a sense also a bi-tangential transfer. It's just the "easy" solution. Sep 1, 2020 at 18:40
• @SE-stopfiringthegoodguys - A bi-elliptical transfer with infinite apoapsis is for all practical purposes a non-solution as it takes an infinite amount of time. Sep 2, 2020 at 3:47