Hybrid Rocket Engine Performance Assessment Using Plume Luminosity Oscillations

2021 ◽  
pp. 1-8
Author(s):  
Troy L. Messinger ◽  
Colin D. Hill ◽  
Declan T. Quinn ◽  
Craig T. Johansen
Keyword(s):  
Performance Assessment ◽  
Rocket Engine ◽  
Engine Performance ◽  
Hybrid Rocket ◽  
Hybrid Rocket Engine

scholarly journals Scale effects on hybrid rocket engine performance

2021 ◽  
Author(s):  
Alexander Velliaris
Keyword(s):  
Computer Program ◽  
Scale Effects ◽  
Rocket Engine ◽  
Engine Performance ◽  
Scaling Up ◽  
Rate Model ◽  
Hybrid Rocket ◽  
Injection Temperature ◽  
Hybrid Rocket Engine ◽  
Burn Rate

In the current study, the effects of scaling up a hybrid rocket engine (HRE) in size has on its performance is investigated. A HRE design from a past RU study is selected as the base model to be progressively increased in size while geometric scale is maintained, up to ten times the original’s size. A computer program employing a quasi-steady convective heat feedback burn rate model is used to conduct simulated engine firings. One finding from this study is that the drop- off in performance for this engine, in going up in size, is not as much as expected. This can be attributed to a conservative oxidizer injection temperature setting in the model, and an oxidizer-fuel ratio mixture influence for this engine that is more impactful. The results presented here however do, to some degree, concur with established trends, with respect to thrust prediction, as the reference HRE is scaled up in size.

scholarly journals Scale effects on hybrid rocket engine performance

2021 ◽  
Author(s):  
Alexander Velliaris
Keyword(s):  
Computer Program ◽  
Scale Effects ◽  
Rocket Engine ◽  
Engine Performance ◽  
Scaling Up ◽  
Rate Model ◽  
Hybrid Rocket ◽  
Injection Temperature ◽  
Hybrid Rocket Engine ◽  
Burn Rate

In the current study, the effects of scaling up a hybrid rocket engine (HRE) in size has on its performance is investigated. A HRE design from a past RU study is selected as the base model to be progressively increased in size while geometric scale is maintained, up to ten times the original’s size. A computer program employing a quasi-steady convective heat feedback burn rate model is used to conduct simulated engine firings. One finding from this study is that the drop- off in performance for this engine, in going up in size, is not as much as expected. This can be attributed to a conservative oxidizer injection temperature setting in the model, and an oxidizer-fuel ratio mixture influence for this engine that is more impactful. The results presented here however do, to some degree, concur with established trends, with respect to thrust prediction, as the reference HRE is scaled up in size.

Rotational and Quasiviscous Cold Flow Models for Axisymmetric Hybrid Propellant Chambers

2010 ◽  
Vol 132 (10) ◽  
Author(s):  
Joseph Majdalani ◽  
Michel Akiki
Keyword(s):  
Rocket Engine ◽  
Navier Stokes ◽  
Mathematical Treatment ◽  
Hybrid Rocket ◽  
Mean Flow ◽  
Viscous Effects ◽  
Navier Stokes Equation ◽  
Flow Models ◽  
Hybrid Rocket Engine ◽  
Wall Injection

In this work, we present two simple mean flow solutions that mimic the bulk gas motion inside a full-length, cylindrical hybrid rocket engine. Two distinct methods are used. The first is based on steady, axisymmetric, rotational, and incompressible flow conditions. It leads to an Eulerian solution that observes the normal sidewall mass injection condition while assuming a sinusoidal injection profile at the head end wall. The second approach constitutes a slight improvement over the first in its inclusion of viscous effects. At the outset, a first order viscous approximation is constructed using regular perturbations in the reciprocal of the wall injection Reynolds number. The asymptotic approximation is derived from a general similarity reduced Navier–Stokes equation for a viscous tube with regressing porous walls. It is then compared and shown to agree remarkably well with two existing solutions. The resulting formulations enable us to model the streamtubes observed in conventional hybrid engines in which the parallel motion of gaseous oxidizer is coupled with the cross-streamwise (i.e., sidewall) addition of solid fuel. Furthermore, estimates for pressure, velocity, and vorticity distributions in the simulated engine are provided in closed form. Our idealized hybrid engine is modeled as a porous circular-port chamber with head end injection. The mathematical treatment is based on a standard similarity approach that is tailored to permit sinusoidal injection at the head end.

Optimization of a H2O2 Gas Generator for a Hybrid Rocket Engine

2013 ◽  
Author(s):  
Martina Faenza ◽  
Federico Moretto ◽  
Alberto Bettella ◽  
Daniele Pavarin
Keyword(s):  
Rocket Engine ◽  
Hybrid Rocket ◽  
Gas Generator ◽  
Hybrid Rocket Engine
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