Решение задач оптимального управления аэрокосмическим самолетом

Abstract

The paper overviews works on methods for solving problems of aerospace aircraft control and aims to solve the remaining problems. The purpose of the study was to obtain reference optimal control and its approximation in the guidance functions. When stating the problem, we took into account all essential physical factors; we selected the solution techniques and computational coordinate system, developed a mathematical model, methods and automated procedures for end-to-end optimization relying on the maximum principle, the formation and optimization of guidance functions. In addition to the well-known methods for solving boundary value problems, methods of analytical calculation of the initial approximation and the search for the convergence region were developed. The results of numerical studies contain nominal and perturbed optimal trajectories in which an aerospace aircraft is boosted by an accelerator, performs global spatial maneuvers, and enters orbit. Having analyzed extremals, compared and evaluated the effectiveness of the guidance functions, we drew certain conclusions taking into account the perturbations.