propellant rocket 
Monte Carlo simulation algorithms are given which are intended for the calculation of the spectral emissivity of jets of combustion products of solidpropellant rocket motors (SRM).


The Outflow of a TwoPhase GasLiquid Mixture from the Mixing Head of a Gas Generator when Starting a LiquidPropellant Rocket E


This paper deals with the problems of mathematical simulation of the startup of a liquidpropellant rocket engine (LPRE), which are associated with twophase flows in the mixing heads (MH) of combustors and gas generators.


The instability of the working process in the combustion chamber of a solidpropellant rocket engine


Heat transfer in the thrust chamber is of great importance in the design of liquid propellant rocket engines.


This model can be applied to all kinds of liquid propellant rocket engines as well as similar constructions.


Numerical simulation of a liquid propellant rocket motor


This work presents a numerical simulation of the flow field in a liquid propellant rocket engine chamber and exit nozzle using techniques to allow the results to be taken as starting points for designing those propulsive systems.


Numerical computations have been carried out in an inert simulator of solid propellant rocket motor with the aid of a standard kω turbulence model.


Some features of designing seals for hydrogen pumps used in turbopump assemblies of liquidpropellant rocket engines are considered.


Study of working process instability in the twochamber solidpropellant rocket engine


The mechanism of lowfrequency acoustic instability generation in the twochamber tandem solidpropellant rocket engine is studied numerically using the Davydov method (the method of large particles).


The strainstress state of the solid propellant rocket engines (SPREs) is simulated under impact.


We present the results of designing the contours of supersonic parts of the solidpropellant rocket motor (solid motor) nozzles with high expansion ratios with the aid of direct variational methods.


These methods are applied in viscous twophase flow calculation of rocket nozzle and in the prediction of thrust and specific impulse for solid propellant rocket motor.


Comprehension of wallinjection flow in a channel in the presence of different geometric discontinuities is necessary as part of the general investigations concerning combustion instabilities of solid propellant rocket motors.


This sutdy concerns the prediction of the stability of segmented solid propellant rocket motors.


We have attempted in this study to analyse the potential unstable development occurring in solid propellant rocket motors.


A multilayered thick cylindrical shell under internal pressure and thermal loads applicable to solid propellant rocket motors


A solid propellant rocket motor can be considered to be made of various circumferential layers of different properties.

