A physics based mathematical model to predict the regression rate in an ablating hybrid rocket solid fuel

Akyuzlu, K. M.; Kagoo, R.; Antoniou, A.

doi:10.2514/6.2001-3242

Cited by 7 publications

(4 citation statements)

References 2 publications

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“…III.B. Other authors [12,31,35,36] in the domain of HRE modeling have already employed this method to solve numerically the physical problem in the combustion chamber. We have then discretized along the axial direction in a structured grid with uniform spatial steps, evaluating the system of equations at each point (see Fig.…”

Section: Numerical Methods Resolutionmentioning

confidence: 99%

“…The Gas-Surface Interaction model (GSI) for pyrolizable fuels constitues the boundary condition at the solid / gaseous flow interface. It has been used by several researchers [31][32][33][34] to model fuel consumption in CFD and to describe the physics in the vicinity of the wall. In this apporach we apply mass and energy balances at the fuel surface.…”

Section: Boundary Conditions: Gas-surface Interaction Modelmentioning

confidence: 99%

“…( 34)]; and the displacement thickness and the momentum thickness variables in the BL [Eq. (31)]. In the next equations, Re x = ρ e u e x ν .…”

Section: Appendixmentioning

confidence: 99%

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Development and Validation of a 1.5-D Combustion Chamber Model for a Hybrid Rocket Engine Applied to a Cylindrical HDPE Chamber

Granado¹,

Hijlkema²,

Lestrade³

et al. 2021

AIAA Propulsion and Energy 2021 Forum

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A 1.5-D model for the cylindrical combustion chamber of a hybrid rocket is developed in this article with the purpose of its integration in a design system tool allowing to estimate the rocket performances. A compromise of simplicity and accuracy is then required in the formulation of the model. Transient boundary layer equations are included through an integral approach and are coupled with the mass and energy balances performed at the fuel surface. Fuel pyrolysis is described by way of an Arrhenius law. Several studies to assess the impact of the geometry of the fuel port, the oxidizer mass flux, and the motor size on the computed fuel regression rate are accomplished. A final validation phase of this model is executed by the comparison with experimental tests realized at ONERA's HYCAT test bench with a Hydrogen Peroxide / High-Density Polyethylene couple.

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Section: Numerical Methods Resolutionmentioning

confidence: 99%

Section: Boundary Conditions: Gas-surface Interaction Modelmentioning

confidence: 99%

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Development and Validation of a 1.5-D Combustion Chamber Model for a Hybrid Rocket Engine Applied to a Cylindrical HDPE Chamber

Granado¹,

Hijlkema²,

Lestrade³

et al. 2021

AIAA Propulsion and Energy 2021 Forum

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show abstract

“…Merkle and Venkateswaran [22] were able to develop a comprehensive model that included the full time-dependent Navier-Stokes equations, coupled with physical submodels and their relative transport equations which span finite rate chemistry, Fire 2023, 6, 100 turbulence, gas phase radiation and fluid-solid coupling. In 2001, Akyuzlu et al [23] published an article on a mathematical model predicting regression rate in an ablating hybrid rocket solid fuel. Serin and Gogus [24] carried out CFD simulations with a commercial package on HTPB-based hybrid rockets using O 2 as oxidizer and studied the reacting flow field and the corresponding heat transfer to the solid fuel.…”

Section: Introductionmentioning

confidence: 99%

Modeling and CFD Simulation of Regression Rate in Hybrid Rocket Motors

Rampazzo

Barato

2023

Fire

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As the research on hybrid rocket motors advances, more accurate tools are needed to estimate the performance of the system by determining its fundamental parameters. One of them is certainly the regression rate of the solid fuel. Unfortunately, it depends on many complex physical phenomena and interactions which vary with time, space and scale, making the task of predicting its evolution very difficult. To address this issue, Computational Fluid Dynamics (CFD) was employed to investigate the inner workings of a hybrid rocket motor and develop a useful tool to help the design process and contribute to the physical understanding of the problem. By implementing a User-Defined Function (UDF) in a commercial CFD software, it has been possible to simulate the regression rate as a function of heat flux at the fuel surface. The calculation is performed by solving the energy balance at the solid–fluid interface coupled with the pyrolysis Arrhenius equation. Validation has been performed using literature data from Carmicino and Sorge. The results generally agree with the experimental regression rates within 10% of error for HDPE and 20% for HTPB. A significant discrepancy in the regression rates of these two fuels not accounted for by the classical theory was exposed.

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Two-phase flow effect on hybrid rocket combustion

Lin

2009

Acta Astronautica

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A physics based mathematical model to predict the regression rate in an ablating hybrid rocket solid fuel

Cited by 7 publications

References 2 publications

Development and Validation of a 1.5-D Combustion Chamber Model for a Hybrid Rocket Engine Applied to a Cylindrical HDPE Chamber

Development and Validation of a 1.5-D Combustion Chamber Model for a Hybrid Rocket Engine Applied to a Cylindrical HDPE Chamber

Modeling and CFD Simulation of Regression Rate in Hybrid Rocket Motors

Two-phase flow effect on hybrid rocket combustion

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