• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.13-21
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• 2005

I consider the structure of steady wave system which is admitted by the continuum equations for materials that undergo phase transformations with exothermic chemical reaction. In particular, the dynamic phase front structures between liquid and gas phases, and solid and liquid phases are computationally investigated. Based on the one-dimensional continuum shock structure analysis, the present approach can estimate the nano-width of waves that are present in combustion. For illustration purpose, n-heptane is used in the evaporation and condensation analysis and HMX is used in the melting and freezing analysis of energetic materials of interest. On-going effort includes extension of this idea to include broad range of liquid and solid fuels, such as rocket propellants.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.2
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• pp.16-26
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• 2014

T-Burner tests of an Al/HTPB propellant in conjunction with a Pulsed DB/AB Method were conducted to find an acoustic amplification factor. Aluminum-free and aluminum-heavy propellants were examined. Instant surface ignition was successfully made by the use of a supplementary propellant of fractionally higher reaction rate. With the presence of higher aluminum concentration in the propellants, the pressure perturbations were promptly damped down and the pressure fluctuations were no longer dispersive. Addition of aluminum particles into the propellant was advantageous for stabilizing pressure-coupled unstable waves.

• Journal of the Korean Society of Propulsion Engineers
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• v.2 no.1
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• pp.59-66
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• 1998

The combustion instability analysis of solid propellants is generally done by the simplified governing equations for chemically inert condensed phase region with QSHOD assumption. Since the gas phase and surface reaction layer can be more rapidly relaxed to the external perturbations than the condensed phase, these regions are treated as quasi-steady manner in the analysis. In this paper, the classical ZN(Zeldovic-Novozhilov)approach was re-examined with the presence of radiation augmented burning enhancement in the combustion. Also, the surface reaction was assumed to partially absorb the incident radiant heat fluxes and pass the remaining to the chemically inert condensed phase. As a result of the analysis, the burning rate response function was obtained which consists of a pressure response function and a radiation response function. The response function was shown to be able to predict the results of T-burner tests.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2005.11a
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• pp.5-8
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• 2005

In this report the developing trends of several clean and green propellants have been summarized. A low-acid clean propellant has been developed, which substantially reduced the content of hydrochloric acid(HCl) in the solid rocket exhaust. Although the chlorine-free approach is now preferred, this technology has not been proved yet. Another acid suppression effect of Magnalium(Mg-Al Alloy) was investigated. Reports says that the concentration of HCl could be reduced to approximately one-fifth of conventional propellant. Many 'green' propellants with low toxicity are being developed for next-generation post-boost propulsion systems, in which combustion research on the Al or Mg fine metal particles with hot steam in various stoichiometric conditions are being performed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.159-162
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• 2009

Using the numerical code for the interior ballistics, the performance of the interior ballistics with the characteristic of the configuration of the solid propellant has been investigated. In existing research, only ball type solid propellant is considered but at this research, cylinder and single slot type solid propellants are considered. Definite the change of performance of the interior ballistics according to specific surface area.

• Journal of Mechanical Science and Technology
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• v.19 no.10
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• pp.1939-1949
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• 2005

Many studies have been conducted to increase regression rate of solid fuel in hybrid rocket. One of them resorts to swirl flow since it can extend the residence time of oxidizer in the fuel grain. Also, metal wires may lead to increase the regression rate of solid fuel as shown in solid propellants. In this study, a series of experiments was designed to investigate the enhancement of regression rate of solid fuel by embedded metal wires and by fuel port grain. And fuel port was designed with a helical configuration to attempt to induce swirl flow. PMMA with gaseous oxygen is the solid fuel used for investigation. Test results showed that embedded metal wires turned out to be ineffective method because only $3-4\%$ increases in regression rate were observed. However, fuel port grain configuration yields higher burning performance of up to $50\%$ increase in regression rate. Also pitch number as well as total impulse was found to be a design variable.

• 한국연소학회:학술대회논문집
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• 2004.06a
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• pp.89-92
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• 2004

This work describes a model development and numerical simulation of detailed combustion mechanisms of RDX/GAP/BTIN propellants. The analysis is based on the conservation equations of mass, energy, and species concentrations for both the condensed and gas phases, and takes into account finite-rate chemical kinetics and variable thermophysical properties. The model has been applied to study the combustion wave structures and burning characteristics of RDX/GAP/BTIN propellants over a broad range of pressures. Reasonably good agreement is achieved between the calculated and measured burning rate at atmospheric pressure. But the model calculation does not result in dark zone experimentally observed.

• Journal of ILASS-Korea
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• v.15 no.3
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• pp.109-114
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• 2010

The implementation of gelled propellants systems offers high performance, energy management of liquid propulsion, storability, and high density impulse of solid propulsion. The present study focused on the macroscopic spray characteristics of liquid sheets formed by triplet impinging jets of non-Newtonian liquids which are mixed by Carbopol 941 0.5%wt. The results are compared to experiments conducted on spray images which formed by triplet impinging jets concerning with airassist effect at center orifice. When gel propellants are injected by doublet impinging jets at low pressure and high pressure, closed rim pattern shape appeared by polymeric effect from molecular force and showed inactive atomization characteristics, because of extensional viscosity related by restriction of atomization process and breakup time delay of turbulence transition. As increasing mass flow rate of the air(increasing GAR), spray breakup level is also increased.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.197-200
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• 2007

This paper presents solid propulsion manufacturing processes. Solid rocket motors propellants are made of several batches of propellant being mixed in mixers and made of continuous mixers. This paper discusses the technology of continuous mix process of Aerojet, US and SNPE Materiaux Energetiques, France.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.4
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• pp.359-367
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• 2015

This paper aims to design an educational science program based on rocket propulsion for high school students. Curriculum in high school physics and chemistry were evaluated to find out scientific match with basic principles in rocket propulsion. Also model rocketry was implemented as a part of the educational program. Solid propellants were prepared by the combination of sorbitol and candy after a selection process for solid propellant from several high caloric food candidates. Specially, this program was intended to give an opportunity to organize basic knowledge of high school science with model rocketry by measuring combustion temperature, thrust level of developed propellants. A pilot operation of the program was done with four high school students to evaluate the achievement of final goals of the program both in technical and educational aspect.