A Parametric Analysis of Hybrid Rocket Motors for Sounding Rockets

2008 ◽  
Author(s):  
Lorenzo Casalino ◽  
Dario Pastrone
Keyword(s):  
Parametric Analysis ◽  
Hybrid Rocket ◽  
Sounding Rockets ◽  
Rocket Motors

Testing and CFD Simulation of Diaphragm Hybrid Rocket Motors

2011 ◽  
Author(s):  
Alberto Bettella ◽  
Marta Lazzarin ◽  
Nicolas Bellomo ◽  
Francesco Barato ◽  
Daniele Pavarin ◽  
...  
Keyword(s):  
Cfd Simulation ◽  
Hybrid Rocket ◽  
Rocket Motors

Visualization of Flow Development in Hybrid Rocket Motors with High Regression Rates

2005 ◽  
Vol 21 (4) ◽  
pp. 613-619 ◽  
Author(s):  
Venelin Stamatov ◽  
Damon R. Honnery ◽  
Julio Soria
Keyword(s):  
Hybrid Rocket ◽  
Rocket Motors ◽  
Flow Development

Numerical Model to Analyze Transient Behavior and Instabilities on Hybrid Rocket Motors

2015 ◽  
Vol 31 (2) ◽  
pp. 643-653 ◽  
Author(s):  
F. Barato ◽  
N. Bellomo ◽  
M. Faenza ◽  
M. Lazzarin ◽  
A. Bettella ◽  
...  
Keyword(s):  
Numerical Model ◽  
Transient Behavior ◽  
Hybrid Rocket ◽  
Rocket Motors

A parametric study of flame propagation in hybrid rocket motors

1998 ◽  
Author(s):  
K. Akyuzlu ◽  
K. Nguyen ◽  
J. Arves ◽  
H. Jones
Keyword(s):  
Flame Propagation ◽  
Parametric Study ◽  
Hybrid Rocket ◽  
Rocket Motors

Design and Testing of a Lab-Scale Hybrid Rocket Motor to Evaluate Swirl Injection Characteristics

2018 ◽  
pp. 185-210
Author(s):  
Susane R. Gomes ◽  
Leopoldo J. Rocco
Keyword(s):  
Swirling Flow ◽  
Specific Impulse ◽  
Operating Conditions ◽  
Geometrical Parameters ◽  
Operating Pressure ◽  
Hybrid Rocket ◽  
Rocket Motors ◽  
Mathematical Background ◽  
Design And Testing ◽  
Firing Tests

This research aims to provide a methodology for the project of labscale hybrid motors. This development began with the thermal analysis of the fuel grain using the Flynn, Wall and Ozawa method, generating simulation entry data to maximize the motor performance. The simulation was performed with the Chemical Equilibrium Specific Impulse Code. Based on the optimum oxidizer to fuel ratio, the literature was used to supply the mathematical background to calculate the motor geometrical parameters whose operating conditions were determined throughout the simulation. Finally, firing tests were conducted to verify the reliability of the project methodology. The firing tests were performed with three injectors: two swirling and one axial. The tests showed that the higher the operating pressure the more suitable is the project, meaning the methodology developed works best in hybrid rocket motors with high operating pressures. Additionally, it was shown that the swirling flow injectors produce higher efficiency.

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