Improved Ignition Devices for 90% Hydrogen Peroxide/Polyethylene Hybrid Rocket Engine

2007 ◽  
Author(s):  
Nobuo Tsujikado ◽  
Atsushi Ishihara
Keyword(s):  
Hydrogen Peroxide ◽  
Rocket Engine ◽  
Hybrid Rocket ◽  
Hybrid Rocket Engine

90% Hydrogen Peroxide/Polyethylene Solid Fuel Hybrid Rocket Engine

2005 ◽  
Author(s):  
Nobuo Tsujikado ◽  
Masatoshi Koshimae ◽  
Rikiya Ishikawa ◽  
Kazuki Kitahara ◽  
Atsushi Ishihara
Keyword(s):  
Hydrogen Peroxide ◽  
Solid Fuel ◽  
Rocket Engine ◽  
Hybrid Rocket ◽  
Hybrid Rocket Engine

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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