• Transactions of the Korean Society of Pressure Vessels and Piping
• /
• v.4 no.2
• /
• pp.20-28
• /
• 2008

According to IAEA regulations, a transportation package of radioactive material should perform its intended function of containing the radioactive contents after the drop test, which is one of hypothetical accident conditions. Impact limiters attached to a transport cask absorb the most of impact energy. So, it is appreciated to determine properly the shape, size and material of impact limiters. A material data needed in this determination is a dynamic one. In this study, several materials considered as those of impact limiters were tested by a drop weight facility to acquire dynamic material characteristics data. Impact absorbing volume of the impact limiter was derived mathematically for each drop condition. A size optimization of impact limiter was conducted. The derived impact absorbing volumes were applied as constraints. These volumes should be less than critical volumes generated based on the dynamic material characteristics. The derived procedure to decide the shape of impact limiter can be useful at the preliminary design stage when the transportation package's outline is roughly determined and applied as input value.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.13 no.4
• /
• pp.55-62
• /
• 2009

Fracture behavior of ceramic dome port cover on air breathing engine using liquid and solid fuel propulsion system was carried out in this study. Fracture characteristics was tested and estimated using scaled model of ceramic dome port cover by Shock tube. Fracture behavior was obtained by the fracture pressure from pressure sensor and observed the scattering phenomena of fracture specimen using high speed camera. Results obtained from this study can be used in the base data of dome port cover design for an air breathing engine.

• Proceedings of the Korean Nuclear Society Conference
• /
• 1995.05a
• /
• pp.753-758
• /
• 1995

중수로 압력관용 Zr신합금을 개발하기 위하여 Batch 1(63종), Batch 2(33종), 및 Batch 3(33종)의 지르코늄합금을 설계, 제조하여 이들 합금에 대한 특성평가를 실시하였다. 설계합금은 고진공 전자빔 용해(Electron Beam Remelting), 단조(95$0^{\circ}C$), $\beta$열처리, 중간열처리, 냉간압연 및 진공열처리의 일관된 제조공정을 거쳐서 판상으로 제조되었다. 설계합금의 특성평가로 성분분석, 인장시험, 부식시험, 충격에너지시험 및 미세조직분석이 수행되었으며, Batchl-Batch3의 120여종의 지르코늄합금에 대한 특성을 종합적으로 평가하여 내부식성 및 고강도 특성의 7종 지르코늄합금을 선정하였다.

• Aerospace Engineering and Technology
• /
• v.1 no.1
• /
• pp.163-172
• /
• 2002

The turbine system composed of a nozzle and a rotor is used to drive turbopumps while gas passes through the nozzle, potential energy is converted to kinematic energy, which forces the rotor blades to spin. In this study, an aerodynamic design of a turbine system is investigated using compressible fluid dynamic theories with some pre-determined design requirements (i.e.,pressure ratio, rotational speed, required power etc.) obtained from a liquid rocket engine (L.R.E.) system design. For simplicity of a turbine system, impulse-type rotor blades for open type L.R.E. have been chosen. Usually, the open-type turbine system requires low mass flow rate compared to the close-type system. In this study, a partial admission nozzle is adopted to maximize the efficiency of the close-type turbine system. A design methodology of the a turbine system has been introduced. Especially, a partial admission nozzle has been designed by means of simple empirical correlations between efficiency and configuration of the nozzle. Finally, a turbine system design for a 10 ton thrust level of L.R.E is presented.

• Composites Research
• /
• v.37 no.1
• /
• pp.21-31
• /
• 2024

This review paper investigates the use of shockwave attenuating materials within composite structures to enhance personnel protection against blast-induced traumatic brain injury (bTBI). This paper also introduces experimental methodologies exploited in the generation and measurement of shockwaves to evaluate the performance of the shock dissipating composites. The generation of shockwaves is elucidated through diverse approaches such as high-energy explosives, shock tubes, lasers, and laser-flyer techniques. Evaluation of shockwave propagation and attenuation involves the utilization of cutting-edge techniques, including piezoelectric, interferometer, electromagnetic induction, and streak camera methods. This paper investigates phase-separated materials, including polyurea and ionic liquids, and provides insight into composite structures in the quest for shockwave pressure attenuation. By synthesizing and analyzing the findings from these experimental approaches, this review aims to contribute valuable insights to the advancement of protective measures against blast-induced traumatic brain injuries.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2012.05a
• /
• pp.520-526
• /
• 2012

The appearance of the negative differential pressure(NDP), in which the shot base pressure is higher than the breech pressure, indicates that a potential damage on the gun system is increased. In order to safeguard the gun system, the igniter must be designed to minimize the NDP during the firing process. From this reason, the effect of igniter's burning rate on the NDP of the interior ballistics has been investigated through the numerical simulations. The NDP has been increased with increment of the coefficient in the burning rate of the igniter. A sudden change of the chamber pressure has been shown in case of using a singular coefficient.

• Journal of Energy Engineering
• /
• v.3 no.1
• /
• pp.54-61
• /
• 1994

계단형태의 고온발생장치로서, 고온의 흐름을 형성하고 난류유동이 없이 일정한 혼합기류를 만들 수 있는 2단격막구조 충격파관 장치를 이용하여, 혼합을 동반하지 않는 분무의 착화과정에 관한 실험을 수행하였다. 본 실험에서는 충격파관 속에 하향으로 설치된 초음파 분무기에 의해 자유낙하 상태에 있는 예혼합 분무주를 만들어서 반사충격파에 의해 순간적으로 단열압축시켜서 착화 현상을 관찰하였다. 고온영역과 저온영역에서 얻어진 활성화에너지는 큰 차이가 나며 본 연구에서 얻은 착화지연의 실험결과는 통상의 분무착화 실험인 전기로법, 급속압축기법, 고온기류속에 연료를 분사하는 방법과 다른 현상을 보였다. 그 대표적인 결과에 대한 예로는 착화지연에 대한 압력 의존성과 연료분사율의 영향이 일반적인 분무의 결과에 비해 적게 나타났다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.10 no.1
• /
• pp.54-63
• /
• 2006

Ejector system are used to transport a low momentum flow to the higher pressure flow by the momentum change between high and low momentum flows. This system is used to simulate the high altitude and Mach number condition over altitude 20 km and Mach 4 of the supersonic test facility. We applied the design and the performance analysis technique(EISIMP code) of the Ramjet Test Facility(RJTF) air system in JAXA to the ejector system of the ramjet test facility in KARI. After preliminary design of the ejector system, we performed a computational study using FLUENT and investigated shock structures and flow characteristics of the ejector system.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2002.04a
• /
• pp.57-58
• /
• 2002

램제트는 다른 여러 추진시스템에 비하여 획기적으로 증가된 사거리를 가지므로 가용범위의 확대는 물론, 목표물 타격 시 높은 명중률과 낮은 격추율을 가지는 효과적인 추진 시스템이다. 램제트 엔진을 장착한 미사일로는 프랑스의 Griffon, ASMP, 미국의 Bomarc, Talos, 영국의 Bloodhound, Sea dart, 소련의 SA4, SA6 등을 비롯하여 많은 종류가 개발되어 실전 배치되었다. 근래 들어 램제트는 군사전략과 전술적인 목적 이외에도 민간용으로도 그 실용성이 강조되고 있어 그 중요성은 날로 더할 것으로 예측된다. 램제트는 일반적인 공기흡입식 엔진과는 달리 엔진 내부에 기계적으로 구동되는 부분이 없이 충격파를 통과하면서 공기의 압력이 높아지는 현상인 램압축 현상을 이용하여 공기를 압축하게 되므로 엔진의 구조가 간단하고, 상대적으로 높은 비추력과 추력/중량비를 가진다. 램제트는 정지 상태에서는 작동되지 않으며 사용 가능한 최소의 압력비를 줄 수 있는 비행 마하수에 도달해야 램제트가 작동하게 된다. 따라서 이러한 비행속도를 줄 수 있는 별도의 추진장치가 필요하게 되는데 이와 같은 보조 추진장치로 부스터를 사용한다. 부스터가 엔진의 내부에 장착된 램제트를 일제형 램제트 (IRR: integral Rocket Ramjet)라 부르며, 현대의 전략미사일과 민간용 초음속 항공기의 엔진에 도입되어 활발한 연구가 진행 중이다. 램압력을 이용하여 압축하므로 램제트의 설계시 설계점 비행 속도에서 전압력 손실이 최소가 되도록 설계되어야 하며, 이를 실험이나 수치해석을 통해 확인하여야 한다.

• Journal of Navigation and Port Research
• /
• v.26 no.1
• /
• pp.101-105
• /
• 2002

Many malfunction take place in container crane spreader due to impact. So we designed a 2 DOF hydraulic impact absorbing equipment to absorb the impact and we studied the change of damping coefficient with respect to the variation of dimensions of oil-Cylinder wail. When we design the dimension of hydraulic cylinder wall considering the displacement on the wall, the value of it over 20m didn't affect the damping coefficient.