The Problem of Determination of Solutions of Motion Equations of Spacecraft with Low Thrust on Trajectories Close to Optimal, Obtained by the Averaging Method

• DOI: 10.1615/jautomatinfscien.v35.i12.30
• Publication Date: 2005-04-28T08:46:44Z
• Authors: Boris N. Kiforenko; Sergey V. Vasilenko; Zoya V. Pasechnik
• Keywords: Eccentricity (behavior); Orbital maneuver; Orbit (dynamics); Payload (computing)

We investigate the problem of construction exact numerical solutions motion equations a spacecraft with low thrust engine, which realizes transfer between distant orbits in Newton central gravity field. Approximate solution classical mechanics space flight about maximal payload under given launching mass is constructed by averaging method. discussed variants determination on trajectories, move away not too much from trajectory averaged solution. One suggested shown for example interorbital simultaneous changing major semiaxis, eccentricity and angle orbit inclination.