Ignition Transient Induced Loads Control Strategy for VEGA Launcher' Solid Rocket Motors: the "Zefiro9" Static Firing Test Predictions and Post Firing Analysis. Zefiro9 Static Firing Test Predictions and Post-firing Analysis

2006 ◽  
Author(s):  
B Favini ◽  
M Di Giacinto ◽  
A Attili ◽  
D Scoccimarro ◽  
M Biagioni ◽  
...  
Keyword(s):  
Control Strategy ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Firing Test ◽  
Solid Rocket

scholarly journals Effect of the fluid–structure interaction on solid rocket motors instabilities

2012 ◽  
Author(s):  
J. Richard ◽  
T. Morel ◽  
F. Nicoud
Keyword(s):  
Solid Propellant ◽  
Gas Flow ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Firing Test ◽  
Solid Propellant Rocket ◽  
Acoustic Instabilities ◽  
Solid Rocket ◽  
Coupling Algorithm ◽  
Propellant Rocket

Large solid propellant rocket motors may be subjected to aero-acoustic instabilities arising from a coupling between the burnt gas flow and the acoustic eigenmodes of the combustion chamber. Given the size and cost of any single firing test or launch, it is of first importance to predict and avoid these instabilities at the design level. The main purpose of this paper is to build a numerical tool in order to evaluate how the coupling of the fluid flow and the whole structure of the motor influences the amplitude of the aeroacoustic oscillations living inside of the rocket. A particular attention was paid to the coupling algorithm between the fluid and the solid solvers in order to ensure the best energy conservation through the interface. A computation of a subscaled version of the Ariane 5 solid propellant engine is presented as illustration.

Erosion Study of Silica Phenolic Nozzles with Graphite Inserts in Solid Rocket Motors

2015 ◽  
Vol 1095 ◽  
pp. 573-578 ◽  
Author(s):  
Xiong Chen ◽  
Rui Liu ◽  
Hong Ying Du
Keyword(s):  
Erosion Rate ◽  
Diffusion Rate ◽  
Diffusion Mechanism ◽  
Upward Trend ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Erosion Rates ◽  
Firing Test ◽  
Solid Rocket ◽  
Experimental And Theoretical Studies

Experimental and theoretical studies on the erosion of silica phenolic nozzles with graphite inserts in solid rocket motors were carried out. Two identical segmented nozzles, consisting of graphite inserts and silica phenolic insulation in the convergent and divergent sections, were tested at same operating condition. Due to the different thermal resistance ability, steps are formed at the interface of two materials. The erosion rates, following the distribution of Reynolds number, exhibit an upward trend in the convergent section and decrease in the divergent section for both silicon phenolic and graphite. At high temperature, the graphite erosion rate is limited by the diffusion rate of the oxidizing species,while the erosion rate is limited by the chemical kinetics at low temperature. For the graphite nozzle insert, a switch from kinetics mechanism to diffusion mechanism occurs in the convergent section during the firing test.

Predicting burning time variations in solid rocket motors

1992 ◽  
Vol 8 (3) ◽  
pp. 564-569 ◽  
Author(s):  
S. D. Heister ◽  
R. J. Davis
Keyword(s):  
Burning Time ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Time Variations ◽  
Solid Rocket

Simple modeling of particle trajectories in solid-rocket motors

1990 ◽  
Author(s):  
G. CARRIER ◽  
F. FENDELL ◽  
D. BRENT ◽  
C. KIMBROUGH ◽  
S. LOUCKS
Keyword(s):  
Particle Trajectories ◽  
Solid Rocket Motors ◽  
Rocket Motors ◽  
Solid Rocket ◽  
Simple Modeling
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