Аналіз шляхів підвищення енергетичних характеристик ракетних двигунів верхніх ступенів
The article is devoted to the analysis of the efficiency of turbine exhaust gas use in the upper rocket engines, which are built on an open circuit. The exhaust variants of the turbine generator gas into a separate nozzle, its afterburning in deflagration and detonation modes are considered. There have defined the basic parameters of the engine installations using these devices, in comparison with the existing engine variant. The combustion of the exhaust gas produced on the turbine in a detonation mode has been found to increase the energy characteristics of the rocket engine built on an open circuit and increase the payload that is put into orbit.