ИСТИНА

The spacecraft interplanetary space flight trajectory is optimized. Rendezvous condition is considered at one bound point and rigid conditions of phasing are supposed at another end. The spacecraft docks to/undocks from the existing station or lands on/flies up from the natural satellite of the planet. The control of the spacecraft is realized by a large limited jet engine thrust. The start, the finish, the moments of inclusion and switching off the thrust are optimized. Weight losses are minimized. The original problem is multiextremal. Global optimization based on Lambert’s problem and Lagrange principle is made to find out initial parameter values.