Regression rates of nonmetalized hybrid fuel systems

Price, C. F.; Smoot, L.D.

doi:10.2514/3.3160

Cited by 73 publications

(7 citation statements)

References 3 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The combustion takes place inside the boundary layer and it is the result of various processes such as: The result is the development of a flame which is located in a thin zone of about 10% of the boundary layer thickness (flame sheet theory) [50][51][52][53][54][55][56][57][58][59].…”

Section: Theoretical Modelmentioning

confidence: 99%

Modeling and CFD Simulation of Regression Rate in Hybrid Rocket Motors

Rampazzo

Barato

2023

Fire

View full text Add to dashboard Cite

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.

show abstract

Section: Theoretical Modelmentioning

confidence: 99%

Modeling and CFD Simulation of Regression Rate in Hybrid Rocket Motors

Rampazzo

Barato

2023

Fire

View full text Add to dashboard Cite

show abstract

“…Several researchers have already reported the influence of motor size on the experimental regression rate [39,45,52,[57][58][59]. For the same mass flux, when increasing the port diameter, the flame moves furher away from the fuel surface, therefore reducing the temperature gradient and the convective heat transfer to the wall.…”

Section: Scale-up Effectsmentioning

confidence: 99%

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

View full text Add to dashboard Cite

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.

show abstract

“…This effort entailed the development of an analytical expression for the regression rate as a function of several kinetic parameters and length-scales. Miller [20] developed a model that incorporated both the fuel diffusion rate and the chemical reaction rates, which he used to successfully correlate data taken by Smoot and Price [21][22][23]. Kosdon and Williams [24] later noted that Miller's analysis was only applicable to systems with low pressure and moderate oxidizer fluxes and derived a new expression that incorporated a flame zone of finite thickness.…”

Section: Kinetics-limited Modelsmentioning

confidence: 99%

“…Another group of researchers focused more on heterogeneous surface reactions as the source of kinetics dependence. Smoot and Price [21][22][23] performed numerous tests using a slab burner and found that, above a threshold value of G, the regression rate became nearly independent of G and instead varied with P and the oxidizer composition. These researchers defined a low mass flux regime where the normal G 0.8 dependence held, an intermediate mass flux regime where both P and G played a role, and a third regime at very high mass fluxes where the regression rate varied with pressure, as in the case of a solid rocket propellant; namely,ṙ ∝ P n .…”

Section: Kinetics-limited Modelsmentioning

confidence: 99%

Review of Classical Diffusion-Limited Regression Rate Models in Hybrid Rockets

Marquardt

Majdalani

2019

Aerospace

View full text Add to dashboard Cite

In this article, we undertake a concise review of several milestone developments in classical regression rate models of hybrid rocket motors. After a brief description of the physical processes entailed in hybrid rocket combustion, Marxman's diffusion-limited theory is re-constructed and discussed. Considerations beyond the scope of basic convection-driven models, which address disparate forms of the blowing correction, variable fluid properties, and pressure and radiation effects, are also given. Finally, a selection of kinetically-limited models is presented, with the aim of comparing the characteristics of several competing theories that become applicable under particular circumstances.

show abstract

Regression rates of nonmetalized hybrid fuel systems

Cited by 73 publications

References 3 publications

Modeling and CFD Simulation of Regression Rate in Hybrid Rocket Motors

Modeling and CFD Simulation of Regression Rate in Hybrid Rocket Motors

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

Review of Classical Diffusion-Limited Regression Rate Models in Hybrid Rockets

Contact Info

Product

Resources

About