CFD analysis of the 24-inch JIRAD hybrid rocket motor

Liang, P. Y.; Ungewitter, Ronald; Claflin, Scott

doi:10.2514/6.1995-2692

Cited by 4 publications

(2 citation statements)

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“…With making develop in concepts of the boundary layer related to combustion mechanism of hybrid combustion by Marxman, other researchers such as Altman [3], Smoot [4], Muzzy [5] and Chiaverini [6], developed modified relations based on experiments to determine the regression rate of solid fuel. As well, a few various numerical studies were carried out for modeling the combustive flow in hybrid rocket motors so far [7][8][9][10][11]. However, there is no research worthy of being mentioned in the field of modeling the combustive gaseous flow on the solid fuel in atmospheric conditions, and in most of the studies only boundary layer of combustive flow has been analyzed.…”

Section: Introductionmentioning

confidence: 98%

An investigation on the effect of chemical kinetics in the modeling of combustive gaseous oxidizer flow on a solid fuel surface

Ahangar

Yaghmaei

Ebrahimi

2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

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In this study, the combustion process of gaseous Oxygen on the surface of HTPB (Hydroxyl-Terminated Polybutadiene) solid fuel has been investigated. To simulate the chemically reactive flow, Navier-Stokes equations and species transport equations were solved using LU-SW implicit scheme. Modeling this kind of combustion process demands a deep understanding of the pyrolysis phenomenon on the solid fuel surface. Experimental studies conducted in this field show that the main gaseous product of the pyrolysis process is C 4 H 6 . An experimental equation which is dependent to the temperature of the fuel surface is used to determine the gas production rate during pyrolysis process. The temperature of the fuel surface can be obtained by applying energy equation in gas-solid interface. The combustion process of gaseous Oxygen and C 4 H 6 has been described by two quasi-global chemical kinetics models. According to the obtained results, the main characteristic parameters of combustive flow such as the flame temperature and mass fraction of chemical species are strongly affiliated to the applied chemical kinetics model. Finally, the results of modeling based on two different models of chemical kinetics are presented and solid fuel surface regression rate is compared with other numerical results.

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Section: Introductionmentioning

confidence: 98%

An investigation on the effect of chemical kinetics in the modeling of combustive gaseous oxidizer flow on a solid fuel surface

Ahangar

Yaghmaei

Ebrahimi

2011

Proceedings of 5th International Conference on Recent Advances in Space Technologies - RAST2011

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“…An enthalpy-balance model, in which fuel-grain ablation heat is balanced by convective heat transfer from the combustion flame, compares well with the experimental data 42 . A preliminary step towards computational fluid dynamics studies were undertaken for the 24" JIRAD hybrid rocket motor to understand flow field characteristics by applying multi-phase, multi-species combustion modelling 43 . Yang 44 , et.…”

Section: Combustion Instabilities In Hybrid Rocketsmentioning

confidence: 99%

Hybrid Rocket Technology

Venugopal¹,

Rajesh²,

Ramanujachari³

2011

DSJ

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With their unique operational characteristics, hybrid rockets can potentially provide safer, lower-cost avenues for spacecraft and missiles than the current solid propellant and liquid propellant systems. Classical hybrids can be throttled for thrust tailoring, perform in-flight motor shutdown and restart. In classical hybrids, the fuel is stored in the form of a solid grain, requiring only half the feed system hardware of liquid bipropellant engines. The commonly used fuels are benign, nontoxic, and not hazardous to store and transport. Solid fuel grains are not highly susceptible to cracks, imperfections, and environmental temperature and are therefore safer to manufacture, store, transport, and use for launch. The status of development based on the experience of the last few decades indicating the maturity of the hybrid rocket technology is given in brief.

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Numerical Simulation of Fuel Regression Rate Behavior of Hybrid Rocket Motors

Xia

Wang

et al. 2013

Trans. Japan Soc. Aero. S Sci.

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CFD analysis of the 24-inch JIRAD hybrid rocket motor

Cited by 4 publications

References 0 publications

An investigation on the effect of chemical kinetics in the modeling of combustive gaseous oxidizer flow on a solid fuel surface

An investigation on the effect of chemical kinetics in the modeling of combustive gaseous oxidizer flow on a solid fuel surface

Hybrid Rocket Technology

Numerical Simulation of Fuel Regression Rate Behavior of Hybrid Rocket Motors

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