Selection of control laws for trajectory and angular motion of spacecraft with a nuclear electric propulsion engine during non-coplanar interorbital flights

The problem of choice of control laws for the trajectory and the angular motion of a spacecraft and the electric propulsion and nuclear energy source for non-coplanar flights. The technique of solving a dynamic problem ( the selection of paths and laws of motion control ), based on an iterative scheme with a consistent pattern of movement complexity. In the initial iteration spacecraft represented by a point of variable mass. In subsequent iterations are used more sophisticated models that take into account the angular motion of the spacecraft, the restrictions on the trajectory and control modes, the perturbing forces and moments. At the final iteration of the terminal control law formed an orbital period of standing and longitude in geostationary orbit. Taking into account the main disturbance implementation errors and execution errors traction control program. An algorithm for solving the control problem, which is formulated as a minimax problem with integro - functional terminal. The results of mathematical modeling of the process of transfer of the spacecraft at a given point of the geostationary orbit, taking into account the disturbing factors.