On payload insertion to the given point

Consideration was given to the problem of optimal program control of the launcher vehicle of the “Soyuz-2” class for insertion the maximal mass to the given neighborhood of a point on the near-earth elliptical orbit, as well as the problem of estimating the set of reachable orbit points. Two kinds of numerical algorithms were developed and realized. The results of numerical modeling and, in particular, determination of the points by two methods were presented.

Presented by the member of Editorial Board: A. I. Kibzun