Abstract:
We consider a method for finding partial solutions for the optimal motion problem of a space vehicle in a central Newtonian field on intermediate thrust arcs. This is the Lehmann-Filhés method based on knowing an incomplete integral of the Hamilton–Jacobi equations. With this method, we obtain a number of partial solutions that can be applied to solving practical problems of space flight mechanics. As an example, we solve the problem of rotating the axis of an elliptical orbit. We compare characteristic velocities necessary to rotate the axis of an elliptical orbit.
Keywords:Lehmann-Filhés method, optimal trajectory, optimal motion, intermediate thrust segment, active segment of a trajectory, space flight mechanics.
Presented by the member of Editorial Board:I. V. Roublev