Abstract
Low-thrust flights from high-elliptic orbits are of considerable interest, since they allow one to decrease (compared to high-thrust flights) the propulsion consumption and to reduce the flight duration. At the same time, in comparison with the spiral unwinding flights from low near-circular orbits, this scheme minimizes the harmful effect of the radiation belts. Based on the maximum principle, the problem of optimization is reduced to a two-point boundary value problem, which is solved numerically using the modified Newton method. A method is suggested to obtain the initial approximation for solving the boundary value problem. The method takes advantage of the idea of transition from an approximately optimal trajectory to the optimal one. Two problems, which have different low-thrust models, are considered: one with permanently acting low thrust and the other with the possibility of turning it on/off. In both cases no restrictions are imposed on the thrust direction. A comparison of these problems is made. We investigated (i) what gain in the final mass can be attained when passing from the first to the second problem, (ii) at the cost of what loss in flight duration this can be achieved, and (iii) what changes in the optimal program of control must be done in this case.
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.