• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 1998.04a
• /
• pp.24-24
• /
• 1998

미사일의 수직 발사 시스템은 수송 및 발사에 필요한 공간을 작게 차지하고 간편하여 각국이 선호하고 있다. 그러나 미사일이 수직발사 초기에는 매우 낮은 속도로 상승하므로 미사일의 방향조정용 Fin의 공력이 발생하지 않기 때문에 초기에 Jet Vane 등의 기계장치를 이용 추력의 방향을 제어하여 마사일의 방향을 목표로 향하도록 하는 Controller가 필요하게 된다. 본 Controller는 DC Motor와 감속기를 이용하여 Vane을 제어 할 수 있도록 설계되어 있으며 1차적으로는 지상 시험용 Controller를 개발 완료된 상태에 있다. 추후 실제 사용하기 위한 Controller를 만들기 위해서는 Main 유도장치와의 상호 Interface 관계를 고려하여 설계되어야 하며 소량 경량화 및 충분한 신뢰성을 갖춘 Controller를 개발하여야 한다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.16 no.5
• /
• pp.89-96
• /
• 2012

The rubber side could be contaminated using the existing pulse echo method because the ultrasonic wave was incident on the rubber side from the interior of the steel motor case, which could lead to the critical disbond defect. To develop the test method which can be replaced the existing method, the ultrasonic wave was incident on steel face of the steel/rubber adhesive test block. Rubber resonance frequencies measured from the steel/rubber adhesive test block were in good agreement with theoretically predicted rubber resonance frequencies. This paper was described about the ultrasonic resonance method to convert the rubber resonance frequency into the rubber thickness.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.16 no.2
• /
• pp.73-79
• /
• 2012

We developed the carbon fabric/EPDM chamber insulation in order to protect motor case with high intensity gas flow. A six-inch simulation motor connected with extension tube was designed to test ablation characteristic of insulation. High intensity gas flow was induced by a FRP disc with hole between motor and extension tube. After ground test, ablation depth of the carbon fabric/EPDM insulation was decreased compared to another insulations after ground static test.

• Journal of Advanced Marine Engineering and Technology
• /
• v.34 no.1
• /
• pp.195-201
• /
• 2010

In this paper, a cooling system of high-power propulsion motor with Energy Saving System(ESS) is described. Normally, the cooling system for ship consists of fresh water pump, sea water pump, 3-way valve and cooler. In the cooling system, F.W(Fresh Water) and S.W(Sea Water) pump is operated on rated rpm, and the 3-way valve is controlled for preventing over-cooling. So, the consumption power of pump's motor is changed according to a sea water temperature. In the proposed cooling system, F.W. pump and S.W pump is controlled by inverter, and it is can be reduced the consumption power. Also, it is proved with simulation.

• The Transactions of The Korean Institute of Electrical Engineers
• /
• v.63 no.8
• /
• pp.1164-1169
• /
• 2014

Recently, an interest in a hybrid system combining only the merits of the conventional wheel-rail system and Maglev propulsion system is growing as an alternative to high-speed maglev train. This hybrid-type system is based on wheel-rail method, but it enables to overcome the speed limitation by adhesion because it is operated by a non-contact method using a linear motor as a propulsion system and reduce the overall construction costs by its compatibility with the conventional railway systems. Therefore, the design and characteristic analysis of a coreless-type superconducting Linear Synchronous Motor (LSM) for 600km/h very high speed railway system are conducted in this paper. The designed coreless-type superconducting LSMs are the distributed winding model, the concentrated 1 layer winding model and the concentrated 2 layer winding model, respectively. In addition, the characteristic comparison studies on each LSM are conducted.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.369-374
• /
• 2011

To solve the combustion instability, especially chuffing phenomena, happened during development process of the drive-away motor that was required for cold launch system of missile, we tried various technical approaches and performed ground firing tests. The supplying content or method of ignition energy, generally that is deeply related with the chuffing phenomena, does not affect suppression of the chuffing, but the addition of 2% ZrC as a damping material is effective to suppress the chuffing. Therefore we could newly experience a special solution of the combustion instability in double base propellant.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.85-91
• /
• 2011

We developed carbon fabric/EPDM chamber insulation in order to protect motor case with high intensity gas flow. Six-inch simulation motor connected with extension tube was designed to test ablation characteristic of insulation. High intensity gas flow was induced by FRP disc with hole between motor and extension tube. After ground test, ablation depth of carbon fabric/EPDM insulation was decreased compared to another insulations after ground static test.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.31-37
• /
• 2011

Detail flow structure in a large solid rocket motor with two inhibitors has been investigated using 3D Large Eddy Simulation and Proper Orthogonal Decomposition(POD) analysis. Vortex shedding frequencies periodically occurred by inhibitors are coupled with flow acoustics induced by the impinging of vorticity on nozzle head. As a result of 3D analysis, it was observed that the nozzle exit flow causes roll-torques from the vortex being decomposed in unbalanced shape for the impinging of vorticity on the nozzle head.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.299-302
• /
• 2011

In the supersonic jet of a solid rocket motor, various noise is investigated. The purpose of this study is to attain and evaluating a design and manufacturing technique of the SRM noise reduction. In this study, the water is injected into the supersonic jet of the SRM to reduce the noise. Furthermore, the diffuser and stack are installed to suppress the SRM noise. Through the SRM ground tests, the noise is reduced approximately 20dBA with application of the diffuser/stack with water injection.

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