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And just as a demonstration, here is a link to a YouTube video demonstrating the basic scheme (contains spoilers!): https://www.youtube.com/watch?v=m4FDrcEbO7s&feature=youtu.be Sadly, I fluffed the step back to real time upon Earth approach and ended up scooting by Earth with a ~ 70 km...

Here (below) is a simple challenge designed to test your thinking about ways of making transfers from low lunar orbit to the Earth. The scenario set out in the attached .scn file is as follows: A Delta Glider starts in a 20 x 20 km lunar orbit with a total 700 m/s of main fuel and 10 m/s of...

Just as a bit of an afterthought re the above post: The above post sets out a simple method for calculating the semi-major axis and orbital eccentricity given the start-point and end-point of a trajectory and one other piece of information - e.g., either the apoapsis radius or periapsis radius...

In the opening post, dgatsoulis has posed the following problem: This problem is a variant of the classic Lambert's Problem which, according to Wikipedia, can be phrased as: Whereas the classic Lambert's Problem formulation specifies a 'time-of-flight', dgatsoulis' variation specifies an...