Methods are proposed for determination of optimum injection trajectories for a case when a launch vehicle (LV) moves in Newtonian gravitational field. Those methods allow to take into account the limitations for LV motion parameters with a shutdown engine, a number of startings and time of operation of LV stages' engines which are characteristic for Launch Vehicles of the type reviewed. It is shown that application of obtained conditions of optimum thrust of LV engines permits to reduce a numerical solution of a task to a sequential solution of one-parametric boundary-value problems at evaluation of LV power characteristics.
power characteristics, injection diagram, optimum flight modes, conjugated system, transversality conditions
"Otsenka эnerhetycheskykh kharakterystyk raket-nosytelei pry odnokratnom y dvukhkratnom vkliuchenyy dvyhatelia dopolnytelnoi stupeny" ,
Systems of Arms and Military Equipment,