ЧИСЛЕННОЕ ИССЛЕДОВАНИЕ ДИНАМИКИ ВНУТРИКАМЕРНЫХ ПРОЦЕССОВ В МАРШЕВОМ РАКЕТНОМ ДВИГАТЕЛЕ НА ТВЕРДОМ ТОПЛИВЕ С УЧЕТОМ ПОЛЕТНЫХ ПЕРЕГРУЗОК. ЧАСТЬ 2. РЕЗУЛЬТАТЫ РАСЧЕТА

Abstract

The article presents the results of numerical calculations of the dynamics of in-chamber processes in the cruise missile's second-stage cruise missile propulsion system, taking into account the distributed space-three-dimensional and time-varying flight overloads, obtained using the previously developed calculation method and the application software package created on its basis. The value of the flight overload of a cruise missile, in projections along the coordinate axes, is determined depending on the mass, speed and trajectory of the rocket, mass flow and thrust of the rocket engine. The external aerodynamic effect on the in-chamber process in the SRM is neglected. The results of the calculations are given in comparison-without taking into account and taking into account the effect of flight overload. Two main stages of the rocket engine operation are considered: entering the operating mode and the main operating mode. At the stage of entering the SRM operation mode, the overload affects the redistribution of the temperature of the gas phase of the combustion products in the area of the front bottom of the combustion chamber. On the March operation of the SRB as a result of the flight of an overload, an increase of the particle density (liquid drops) small and large diameter of the solid phase of the combustion products in the wall of the back plate and pre-exhaust gas flue, and the degree of change in the distribution density of the particles (liquid droplets) that are larger than large. The results of the numerical study are in good agreement with the experimental data – the results of bench tests of the rocket engine and the results of flight tests of the cruise missile, which includes the considered SRM.