| Abstract: | ![]()
Analysis of the results indicates that:| a) | all the optimal trajectories may be divided into two sections: the phased section, corresponding to motion over a trajectory close to the initial one with a small change in initial energy (amounting to around two-thirds of the total journey time); and the orbital transfer, with considerable change in orbital energy, as a result of active control of the solar-sail orientation (around one-third of the total journey time). In the second section, the spacecraft first moves closer to the Sun and then makes the transfer to Mars orbit; | | b) | the duration of orbital transfer is 581 dyas according to the optimal plan, which includes sections of deceleration and movement from the initial orbit over a distance of 0.2 dimensional length units toward the Sun; with the constraint   /2, the deceleration is eliminated, and the distance toward the Sun is reduced (to 0.1 dimensionless units), with a corresponding increase in journey time; | | c) | taking account of the nonideal reflecting surface ( =0.85 rather than =1) increases the journey time to 615 days without change in the other characteristics of the orbital transfer. |
Scientific-Research Institute of Structural Mechanics, Kiev. Kiev Structural-Engineering Institute. Translated from Prikladnaya Mekhanika, Vol. 30, No. 9, pp. 82–87, September, 1994. |
