Method of injection of subminiature satellites with the aid of flying space launch facility based on An-124-100 and An-225 airplanes

Abstract

In paper the task solution for multicriterion optimization by control launch into orbit of multimode aerospace system in given terminal conditions is considered. The mathematical apparatus of differential-and-taylor transformations of functions and method of scalar convolution on nonlinear scheme of compromises are applied. The offered approach does not require numerical integration of equations of object trajectory motion and allows analytic solution of problem. Comparison of simulation results of aerospace system launch into orbit with multicriterion and terminal control is conducted.