scholarly journals NUMERICAL INVESTIGATION OF UNSTEADY GASDYNAMIC PROCESSES AT THE LAUNCH OF SOLID-PROPELLANT ROCKETS

2020 ◽  
pp. 127-143
Author(s):  
Kirill V. KOSTYUSHIN ◽  
Keyword(s):  
Solid Propellant ◽  
Rocket Engine ◽  
Supersonic Jet ◽  
Rocket Engines ◽  
Computational Domain ◽  
Engine Operation ◽  
Solid Propellant Rocket ◽  
Unsteady Force ◽  
Solid Propellant Rocket Engine ◽  
Force Components

The paper presents the results of the methodology developed for calculating unsteady gasdynamic processes occurring at the launch of missiles, in the gas-dynamic paths of rocket engines, and in the external regions. The method accounts for the variation in the geometry of the solidpropellant charge in the course of solid-propellant rocket engine operation and in the geometry of the computational domain at the rocket launch. The analysis of the unsteady force impact of the supersonic jet on the launch surface is carried out. It is shown that the maximum force action is located in the vicinity of the Mach disks of the unperturbed jet. Numerical studies of gasdynamic processes at the launch of a model solid-propellant booster rocket are implemented including the case when the nozzle plug opening is taken into account. The contribution of the thrust force components at the stage of bootstrap operation is assessed. The presence of the plug at the initial stage of the engine start leads to an abrupt change in the thrust and minor fluctuations, which are damped as the pressure in the combustion chamber rises.

scholarly journals On the question of solid-propellant rocket engine design preventing unstable operation in the combustion chamber

2017 ◽  
pp. 63-72
Author(s):  
G. A. Glebov ◽  
S. A. Vysotskaya
Keyword(s):  
Combustion Chamber ◽  
Solid Propellant ◽  
Rocket Engine ◽  
Rocket Engines ◽  
Pressure Oscillations ◽  
Engine Design ◽  
Solid Propellant Rocket ◽  
Solid Propellant Rocket Engine ◽  
Flow Duct ◽  
Propellant Rocket

The paper presents results of a numerical investigation concerning the effect that the flow duct shape and combustion rate equation have on the gas dynamic vortex flow pattern and self-excited pressure oscillations in the combustion chamber of a solid-propellant rocket engine. We provide guidelines on upgrading solid-propellant rocket engines in order to decrease the magnitude of pressure pulses in the case of pulsating combustion.

scholarly journals Analysis of the existing igniter devices and the development of a promising igniter design for the launching booster of modern solid-propellant ramjets

2019 ◽  
Author(s):  
V.A. Sorokin ◽  
O.V. Mokretsova ◽  
P.V. Valuy ◽  
D.Yu. Fedorov ◽  
A.N. Molodtsov ◽  
...  
Keyword(s):  
Solid Propellant ◽  
Rocket Engine ◽  
Combustion Products ◽  
Rocket Engines ◽  
Additional Energy ◽  
Ramjet Engine ◽  
Structure Reliability ◽  
Solid Propellant Rocket ◽  
Solid Propellant Rocket Engine ◽  
Propellant Rocket

The article briefly reviews the existing designs and technical solutions for solid propellant igniters in rocket engines. The technical and design solutions in the development of solid-propellant rocket engine igniters are analyzed. The results of the development of a promising igniter design with gunpowder filler axially located in the internal channel of a propellant grain of a launching free-flowing booster of a rocket-ramjet engine are presented. Ensuring the required level of structure reliability and durability in the launch mode of the solid propellant rocket-ramjet engine, the igniter will improve the engine traction characteristics due to the combustion of the igniter aluminum shell as an additional energy source and using its combustion products in the stream of solid propellant combustion products.

Numerical Computation of Specific Impulse and Internal Flow Parameters in Solid Fuel Rocket Motors with Two-Phase Сombustion Products

2021 ◽  
pp. 98-107
Author(s):  
T.S. Sultanov ◽  
G.A. Glebov
Keyword(s):  
Combustion Chamber ◽  
Condensed Phase ◽  
Solid Fuel ◽  
Solid Propellant ◽  
Rocket Engine ◽  
Specific Impulse ◽  
Two Phase ◽  
Solid Propellant Rocket ◽  
Solid Propellant Rocket Engine ◽  
Propellant Rocket

Eulerian --- Lagrangian method was used in the Fluent computational fluid dynamics system to calculate motion of the two-phase combustion products in the solid fuel rocket motor combustion chamber and nozzle. Condensed phase is assumed to consist of spherical particles with the same diameter, which dimensions are not changing along the motion trajectory. Flows with particle diameters of 3, 5, 7, 9, and 11 μm were investigated. Four versions of the engine combustion chamber configuration were examined: with slotted and smooth cylindrical charge channels, each with external and submerged nozzles. Gas flow and particle trajectories were calculated starting from the solid fuel surface and to the nozzle exit. Volumetric fields of particle concentrations, condensed phase velocities and temperatures, as well as turbulence degree in the solid propellant rocket engine flow duct were obtained. Values of particles velocity and temperature lag from the gas phase along the nozzle length were received. Influence of the charge channel shape, degree of the nozzle submersion and of the condensate particles size on the solid propellant rocket engine specific impulse were determined, and losses were estimated in comparison with the case of ideal flow

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