• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.196-199
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• 2009

The most important thing is to analyze the Fast Cook Off problem of the solid motor case exposed to direct flame is a heat transfer analysis. Heat causes degradation and ignition of the propellant. To archive an acceptable reaction level in Fast Cook Off, the rocket motor case generally must fail structurally prior to propellant ignition. We investigate the responses of the solid motor case exposed to Fast Cook Off by using finite element method for the thermal analysis.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.181-184
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• 2009

A development of a composite solid propellant is carried out for an application to gas generators as an energy source of rocket system. With HTPB as a propellant binder which has 80% of particle loading ratio, a favorable rheology, and moderate curing properties at the range of $-50^{\circ}C{\sim}70^{\circ}C$, AN is selected as the first kind of oxidizer having the characteristics of a low flame temperature, minimal particle residual as well as nontoxic products. AP is the second oxidant for ballistic property control. A series of experiments for the improvement of physical properties were conducted and resulted in the propellant formulation having 30% of strain rate at 8 bar of max. stress.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.221-224
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• 2010

Recently, due to the enormous cost for sending a satellite into an orbit, small and more reliable satellites have been more demanded. An introduction of new binders(HTPB, GAP) and new oxidizers made great improvements of the large thrust modulation. In order to make cost reduction, one prefers to the low melting temperature thermoplastic propellant reforming the manufacturing process dramatically. Solid propellant rockets have been had a problem of the injection accuracy into orbit, but PBS(Post Boost Stage) using a liquid mono-propellant improves the injection accuracy. This paper also gives the direction of the advanced nozzle materials and the motor case.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.31-35
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• 2008

Various types of solid rocket motors which manufactured by each aim have their own shelf life. So they must be done away if not used. And inferior goods during manufacturing must be done away too. In the past, out burning and out detonation is usual but now, environmental pollution should be concerned so that there are related technologies and commercial plants in other countries already from 1970's. Hence in this paper, we will talk about foreign state and domestic development of solid rocket motor demilitarization using wash out.

• Journal of the Korean Society of Propulsion Engineers
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• v.15 no.4
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• pp.48-56
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• 2011

A Possibility of combustion instability on longitudinal mode has a high level at large scale of L/D. Solid propellant has a metal particle and a grain of control to pressure oscillation. Solid rocket motor in slotted-tube grain controls pressure oscillation of longitudinal mode. Slotted-tube grain restrains longitudinal 1st pressure oscillation. But cavity volume of aft. insulation ablation amplifies 2nd pressure o scillation by vortext shedding. A study has suppressed combustion instability and vortex shedding by modified 4 slotted tube solid rocket motor design.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.211-214
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• 2007

Solid rocket motor that includes AL powder in propellant gets slag during static firing test. Slag is piled up to weak area in motor case and causes dangerous phenomena like explosion of motor. In this paper, It is shown that boots gap liner casting process was developed and static firing test was performed with better results.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.886-898
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• 2008

A survey is offered of the present status of microaluminized propellants industrially used worldwide in most space applications, but new directions are also pointed out making profitable use of the nanoaluminized propellants currently tested in many laboratories. Different industrial- and research-type of solid rocket propellants, mainly but not only, of the well-known family oxidizer/Al/HTPB(oxidizer being AP, AN or a mixture of the two) were experimentally analyzed at the Space Propulsion Laboratory of Politecnico di Milano. In general, they feature the same nominal composition but implement different grain size distributions of the oxidizer or metal fuel. The basic properties of all formulations were compared to that of a standard propellant already certified for flight.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.221-226
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• 2008

A typical unsteady internal ballistic analysis model was proposed to take account the erosive burning with the variance of local velocity and pressure along grain surface to the axis of a solid rocket combustor. The model introduced in this study showed good agreements with the results of previous research. It was investigated that the combustion pressure, grain length, initial temperature, and vaporization temperature of propellant affect on the erosive burning.

• Journal of the Korean Society of Propulsion Engineers
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• v.13 no.2
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• pp.17-25
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• 2009

A typical unsteady internal ballistic analysis model was proposed to take account of the erosive burning with the variance of local velocity and pressure along the grain surface of a solid rocket combustor. To validate the model of concern in the study, both cases of non-erosive and erosive burning were compared with the previous researches with marginal accuracy. It was quantitatively investigated that the combustion pressure, grain length, initial temperature, and vaporization temperature of propellant affect the erosive burning characteristics.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• v.y2005m4
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• pp.39-43
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• 2005

In this paper, we describe the contents of the achievement of basic experiments for manufacturing and evaluating a micro-rocket using solid propellant, as the device of the micro thrust generator which can be used for attitude control of satellites. We try to analyze performance of the rocket through visualization of the motor jet, and adopt various ignition methods to obtain confidence in ignition problem. For this purpose, we develop and test two different types of thrust measurement system.