Burn Time Correction of Start-Up Transients for CAMUI Type Hybrid Rocket Engine

Burn time errors caused by various start-up transient effects have a significant influence on the regression modelling of hybrid rockets. Their influence is especially pronounced in the simulation model of the Cascaded Multi Impinging Jet (CAMUI) hybrid rocket engine. This paper analyses these transient burn time errors and their effect on the regression simulations for short burn time engines. To address these errors, the equivalent burn time is introduced and is defined as the time the engine would burn if it were burning at its steady-state level throughout the burn time to achieve the measured total impulse. The accuracy of the regression simulation with and without the use of equivalent burn time is then finally compared. Equivalent burn time is shown to address the burn time issue successfully for port regression and, therefore, also for other types of cylindrical port hybrid rocket engines. For the CAMUI-specific impinging jet fore-end and back-end surfaces, though, the results are inconclusive.

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DEVELOPMENT OF TEST FACILITIES FOR 5 KN-THRUST HYBRID ROCKET ENGINES AND A SWIRLING-OXIDIZER-FLOW-TYPE HYBRID ROCKET ENGINE FOR TECHNOLOGY DEMONSTRATION

International Journal of Energetic Materials and Chemical Propulsion ◽

10.1615/intjenergeticmaterialschemprop.2017011994 ◽

2016 ◽

Vol 15 (6) ◽

pp. 435-451 ◽

Cited By ~ 1

Author(s):

Koki Kitagawa ◽

Saburo Yuasa ◽

Takashi Sakurai ◽

S. Hatagaki ◽

N. Shiraishi ◽

...

Keyword(s):

Rocket Engine ◽

Rocket Engines ◽

Hybrid Rocket ◽

Flow Type ◽

Technology Demonstration ◽

Hybrid Rocket Engine

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Design, Production and Evaluation of 3D-Printed Mold Geometries for a Hybrid Rocket Engine

Aerospace ◽

10.3390/aerospace8080220 ◽

2021 ◽

Vol 8 (8) ◽

pp. 220

Author(s):

Benedict Grefen ◽

Johannes Becker ◽

Stefan Linke ◽

Enrico Stoll

Keyword(s):

Solid Fuel ◽

Degrees Of Freedom ◽

Rocket Engine ◽

Mold Material ◽

Rocket Engines ◽

Test Bed ◽

Hybrid Rocket ◽

Design Production ◽

3D Printed ◽

Hybrid Rocket Engine

The feasibility of 3D-printed molds for complex solid fuel block geometries of hybrid rocket engines is investigated. Additively produced molds offer more degrees of freedom in designing an optimized but easy to manufacture mold. The solid fuel used for this demonstration was hydroxyl-terminated polybutadiene (HTPB). Polyvinyl alcohol (PVA) was chosen as the mold material due to its good dissolving characteristics. It is shown that conventional and complex geometries can be produced reliably with the presented methods. In addition to the manufacturing process, this article presents several engine tests with different fuel grain geometries, including a short overview of the test bed, the engine and first tests.

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Experimental and numerical analysis of an aft-injected hybrid rocket engine

10.22215/etd/2009-13024 ◽

2009 ◽

Author(s):

Nick Grondin

Keyword(s):

Numerical Analysis ◽

Rocket Engine ◽

Hybrid Rocket ◽

Hybrid Rocket Engine

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Numerical modelling of the hybrid rocket engine performance

Propulsion and Power Research ◽

10.1016/j.jppr.2021.03.001 ◽

2021 ◽

Author(s):

Marian Gieras ◽

Aleksander Gorgeri

Keyword(s):

Numerical Modelling ◽

Rocket Engine ◽

Engine Performance ◽

Hybrid Rocket ◽

Hybrid Rocket Engine

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Rotational and Quasiviscous Cold Flow Models for Axisymmetric Hybrid Propellant Chambers

Journal of Fluids Engineering ◽

10.1115/1.4002397 ◽

2010 ◽

Vol 132 (10) ◽

Cited By ~ 17

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.

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