• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.1
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• pp.68-75
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• 2015

In this paper, unsteady characteristics of pressure in solid rocket motor were analyzed by using response of pintle actuation, pressure and thrust data from ground test. Pressure and thrust in solid rocket motor can be controlled in real time by varying nozzle throat area with pintle, installed in the valve. Unsteady characteristics of pressure can be observed in this system occurred by various reasons. Two critical reasons, error of pintle actuation and ablation of center tube, are found and effects of each reason can be analyzed individually by re-prediction of pressure with response of pintle actuation and analyzing thrust to pressure ratio.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.201-212
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• 2012

In general solid propulsion offers cost effective, large thrust capabilities comparing to the liquid propulsion which offers high specific impulse and restart capabilities. Therefore solid propulsion is well fitted for the first stage and boosters. BBL approach has been studied for the launch vehicle because of cost effectiveness, limited development time and low risk. Using of the carbon fiber epoxy resin in the solid rocket motor case is expanded, and specially high strength fibers are more attracted since its inert mass reduction.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.1
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• pp.76-81
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• 2009

A nonlinear pressure controller to actively regulate the thrust of a solid propulsion system is presented. To compensate for the parametric uncertainties with respect to the chamber pressure induced by changing nozzle throat area, Lyapunov-based parameter adaptation method has been applied. In order to verify the effectiveness of the proposed control method, the experiments were carried out using the cold gas test equipment that can simulate the operating environment of variable thrust solid propulsion system. The experiment results show that the nonlinear pressure controller has better performance than conventional P and PI controller.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.181-184
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• 2009

In this study, flow visualization method to simulate internal flows of solid rocket motor in a water tunnel is introduced. The tunnel provides excellent visualization of vortex flows and has been used to propellant grain design of the solid rocket motor. A water tunnel is suggested for the research and the visualization test using dye, hydrogen bubble generator and PIV has been studied and discussed.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.189-192
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• 2010

In this study, insensitive munitions(IM) policies and technologies of advanced countries for solid rocket motor were investigated. Development trends and caseworks of each part such as propellant and motor case of rocket motor for IM were also studied. Based on these investigation and analysis for IM rocket motor, directions of the development for IM rocket motor in our country were suggested.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.555-558
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• 2010

This paper presents a design of solid rocket motor with high length to diameter applied composite propellant. Solid rocket motor with high L/D ratio can be generated erosive burning and combustion instability on longitudinal mode. Especially, Erosive burning can effectively prolong the initial pressure spike in some star grain motors. That is, the study shows design of grain, internal ballistics and structural analysis in order to perform system requirements.

• 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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• 2011.04a
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• pp.228-231
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• 2011

Burning rate of a propellent is an essential factor when designing a propulsion system. In order to come up with burning rate, first we need to design and build propellent grain to get neutral pressure curve. Then check the pressure with ground test and calculate the burning rate using burning rate equation. This burning rate is then compared to the burning rate of a propellent which was resulted from making a standardized specimen and combusting it using a strand burner. An accurate burning rate is calculated after comparing those two burning rates. For this study, compact propulsion system was designed, produced, tested and analyzed in order to get burning rates, an essential factor in propulsion system design, in an effective way.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.24-25
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• 2000

실제 추진기관에서 비추력 성능에 미치는 열/유동현상은 이상 유동(ideal flow)과는 달리, 추진기관의 특성에 따라 다양한 열/유동손실이 나타나며, 연소시험 시에는 이러한 성능 손실 인자들이 복합적으로 작용하여 나타나는 추력이 측정된다. 따라서 임의의 추진기관을 새롭게 성능 설계할 때에 부딪히는 문제중의 하나는 추력 손실 양을 정량화 시키는 일이다. 그런데 고체 추진기관은 복잡한 물리적인 현상들이 복합되어 작동되기 때문에 lump parameter로 간단히 추력 손실을 예측하는 것은 매우 어려운 일이다.(중략)

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.460-463
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• 2011

Different kinds of solid rocket motors manufactured for various aim have their own shelf life. So they must be done away if not used. In general, ammonium perchlorate(AP) has used in the process of solid rocket motors, which is environmental pollutant. Out-burning and out-detonation were usual in the past, but they polluted the surrounding environment and raised safety issues. As an alternative to resolve these, water-washout process to separate the propellant from rocket motors and an eco-friendly way for recovering AP are studied in this paper.