Numerical Simulation of Fuel Regression Rate Behavior of Hybrid Rocket Motors

Hu, Jie; Xia, Zhang; Wang, Dequan; Huang, Liya

doi:10.2322/tjsass.56.351

Cited by 2 publications

(1 citation statement)

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“…A recent study by Coronetti and Sirignano (2013) predicts the regression rate of the hydroxyl-terminated polybutadiene (HTPB)/gaseous oxygen formulation and its sensitivities to some operating parameters, such as combustion chamber pressure, oxygen inlet temperature, and mass flow rate. Hu et al (2013) et al (2012) attempts to research and predict the effect of the aluminum particle additives on the performance of the HTPB/98HP hybrid rocket motor with a numerical approach. Despite the large amount of research (mostly qualitative) ongoing in the field, the computational fluid dynamics (CFD) models of hybrid rocket engines need to be improved (Kuo and Houim, 2011).…”

Section: Introductionmentioning

confidence: 99%

Numerical Modeling of Combustion Processes in Hybrid Rocket Engines

Mazzetti¹,

Barbante

2016

Int J Energetic Materials Chem Prop

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Nowadays, numerical simulations of combustion processes in hybrid rockets are generally considered as a qualitative tool used mainly to describe the flow field inside the rocket engine. A research effort is of major importance in order to change this trend. It can be done by obtaining results that are quan-titatively accurate, to be used as a support for experimental research, reducing costs, and increasing efficiency in the development of better fuel formulations. The importance of such an effort relies on the fact that hybrid rockets are one of the most promising technologies in the aerospace propulsion field, with applications in hypersonic atmospheric flight, launch vehicles' upper stages, and space tourism, which is seen as a prelude for an economically feasible mass access to space. This is possible because of hybrid propulsion's low cost, intrinsic safety, and operational flexibility with potentially high per-formances. This research contribution aims to develop an accurate combustion model for traditional rubber-based hybrid rocket fuels (hydroxyl-terminated polybutadiene). Results of the simulations are presented as temperature distribution, axial velocity, and the products' mass fractions. A discussion about local and average fuel regression rates is presented, with particular attention to the effects on both the local and average regression rate, due to an increase in oxidizer mass flux and in pressure. Results of the present work suggest that an increase in oxidizer mass flux gives an increase in the average regression rate, while an increase in pressure gives a reduction in the average regression rate.

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Section: Introductionmentioning

confidence: 99%