• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.11a
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• pp.185-188
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• 2009

The rocket motor of the space launch vehicle offers thrust for satellite to enter into the orbit. Characters of the solid propellant for rocket motors are affected by the space conditions such as vacuum and space radiation. The solid propellant used for such a purpose should not undergo physical, internal ballistic and energetic changes when exposed to vacuum and space radiation. This study describes the development of the solid propellant composition for the rocket motor of the space launch vehicle. Also, experimental study was conducted on supersonic diffuser in order to verify the performance of the solid propellant composition which was applied to standard motor on the ground in the vacuum condition.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1176-1179
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• 2017

In this study, internal ballistic analysis theories of dual-thrust solid rocket motor using two kinds of propellant are found, and the theories are applied to develop internal ballistic analysis model. Internal ballistic analysis which is dual-thrust solid rocket motor using two kinds of propellant is carried out an applying of the random figures of two kinds of propellant and an analyze of the test results. Through this analytical model was able to an applying internal ballistic analysis for dual-thrust solid rocket motor using two kinds of propellant.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.215-218
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• 2009

A design of a subscale solid propellant rocket motor was conducted to do the similitude experiments for the large scale rocket motor. One of the main factor to subscale was the mach number of the solid propellant flume through a nozzle exit The analysis of the flume flow was done to obtain the mach number for the large and subscale rocket motor. The flume shapes on the non dimensional axises by the nozzle exit diameter was matched each other. The propellant grain of a subscale solid rocket motor was designed by the profile of pressure vs time obtained by the mach number of the flume shape. Some analyses of the theoretical solution were compared with the results of the ground static test.

• Journal of the Korean Society of Propulsion Engineers
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• v.8 no.3
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• pp.61-67
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• 2004

The extinction characteristics of the solid propellant were studied experimentally in this paper. These characteristics are required for designing TCO (thrust cut off) system of the solid rocket motor Parameters to characterize solid propellant extinction were defined by physical observation. A device was designed (or acquiring these parameters and the firing tests were implemented to get the preliminary data for the extinction characteristics of HTBP propellant.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.05a
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• pp.175-178
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• 2008

A Numerical Simulation which uses preconditioning algorithm to examine unsteady combustion processes for the AP/HTPB propellant with a converging-diverging nozzle has been compared with experimental data for solid rocket motor. To analysis reacting flow of solid rocket motor, unsteady pressure, temperature contour was simulated by grid moving of propellant.

• Journal of the Korean Society of Safety
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• v.13 no.4
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• pp.137-141
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• 1998

The combustion instability of a rocket motor can be predicted by the linear stability analysis. The most important input data in this analysis is the combustion response function of the solid propellant. In many cases, it is very difficult to measure the function. But, in that case, the combustion response function can be theoretically evaluated by properties of the propellant. In this study, the theoretical values were compared with measured values by T-burner. Data are relatively so well agreed that theoretical values are enough to be used in linear stability analysis of the rocket motor using a newly developed propellant.

• 한국전산유체공학회:학술대회논문집
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• 2008.03b
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• pp.547-550
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• 2008

A solid rocket motor has quite complex physical condition such exothermal chemical reaction in subsonic area and supersonic ex pansion in a converging-diverging nozzle. To introduce a simulation tool for compressible flow in supersonic range as well as incompressible chemical reaction zone in a whole rocket nozzle is a essential demand. Since the flow vary subsonic to super sonic, the convergence in computation becomes very low and unstable in a whole domain of rocket motor. This paper reports the 2-D Axisymmetric and simple 3-D solid propellant combustion and flow of gases in rocket motor by using a precondi tioning, shear stress turbulence modeling, AUSM(p). To simulate the simplified combustion process, Double base solid propellant is used to calculate reaction of solid propellant.

• Journal of Aerospace System Engineering
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• v.7 no.4
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• pp.42-48
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• 2013

In this paper, a study of solid rocket propellant formulation is performed to suppress plume and reduce IR(infrared) signature which occurs in propellant combustion. The solid propellant to enhance the stealthy ability was formulated in terms of the kinds and the effects of afterburning suppressant on the ballistic performance and the amount of primary smoke. In addition, substantial decrease in plume and IR signature is confirmed by static firing test by a 4 inch standard motor.

• 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.

• Transactions of the Korean Society of Mechanical Engineers
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• v.18 no.11
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• pp.3032-3038
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• 1994

The paper discusses a combustion instability phenomena encountered in recent solid rocket motor development efforts at ADD(Agency for Defense Development). It has happened to occur as an irregular burning in development of smokeless propellant rocket motor. Through investigating the spectral analysis of accelerometer and strain gage signals which are recorded in static firing tests and acoustic modal analysis of motor inside cavity with ANSYS, the instability is found to be the second tangential mode.