scholarly journals Optimization of the design of pulse solid-propellant rocket engines with metal bodies by their association in the monoblock compartment made of high-strength plastic

2019 ◽  
Vol 25 (6) ◽  
pp. 33-38
Author(s):  
E. Mahdin ◽  
◽  
Y. Dmytrenko ◽  
H. Tolochyants ◽  
M. Mikhaylov ◽  
...  
Keyword(s):  
Solid Propellant ◽  
High Strength ◽  
Rocket Engines ◽  
Solid Propellant Rocket ◽  
Propellant Rocket

ACOUSTIC CAVITIES DESIGN PROCEDURES

2007 ◽  
Vol 6 (2) ◽  
pp. 27
Author(s):  
A. Santana Jr. ◽  
M. S. Silva ◽  
P. T. Lacava ◽  
L. C. S. Góes
Keyword(s):  
Solid Propellant ◽  
Rocket Engines ◽  
Combustion Chambers ◽  
High Frequencies ◽  
Design Procedures ◽  
Solid Propellant Rocket ◽  
Acoustic Cavities ◽  
The Stability ◽  
Propellant Rocket ◽  
Damping Systems

Combustion instability is recognized as one of the major problems frequently faced by engineers during the development of either liquid or solid propellant rocket engines. The performance of the engine can be highly affected by these high frequencies instabilities, possibly leading the rocket to an explosion. The main goal while studying combustion chambers instability, either by means of baffles or acoustic absorbers, is to achieve the stability needed using the simplest possible manner. This paper has the purpose of studying combustion chambers instabilities, as well as the design of acoustic absorbers capable of reducing their eigenfrequencies. Damping systems act on the chamber eigenfrequency, which has to be, therefore, previously known.

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.

Regularities of Physical Processes in Hybrid Solid-Propellant Rocket Engines

2015 ◽  
Vol 57 (12) ◽  
pp. 1796-1799 ◽  
Author(s):  
S. S. Bondarchuk ◽  
A. B. Vorozhtsov ◽  
A. S. Zhukov ◽  
B. V. Borisov
Keyword(s):  
Solid Propellant ◽  
Rocket Engines ◽  
Physical Processes ◽  
Solid Propellant Rocket ◽  
Propellant Rocket
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