• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.363-366
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• 2011

Mixing and combustion experiments with a vent slot mixer were performed in Mach 2 supersonic wind tunnel. Helium and hydrogen gases each were used for the mixing and the combustion experiment with a plasma jet (PJ) torch. The vent slot mixer holds plenty of fuel in the downstream mixing region, even though the fuel is transversely injected. In case of the combustion, the injected fuel is ignited by the PJ torch, and then unburned mixture is burned by shock-induced combustion downstream. Thermal choking in the combustor leads to shock trains in the isolator, causing the unstable combustion.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1996.11a
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• pp.83-93
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• 1996

• Journal of the Korean Chemical Society
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• v.48 no.1
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• pp.99-102
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• 2004

• Journal of the Korean Chemical Society
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• v.46 no.6
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• pp.595-598
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• 2002

• 한국연소학회:학술대회논문집
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• 2012.11a
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• pp.97-99
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• 2012

A pressure-based BOIK model considering Shock to Detonation Transition(SDT) and damage due to external fragment or bullet stimuli impact on energetic materials and analytical approach for determination of free parameters are proposed. The rate of product mass fraction(${\lambda}$) consists of ignition term that represents the initiation due to shock compression and growth term that describes propagation of detonation wave and strain term representing the morphological deformation induced by external impact.

• 한국연소학회:학술대회논문집
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• 2015.12a
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• pp.223-226
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• 2015

A pyrotechnic system that consists of donor/acceptor pair separated by a gap relies on shock attenuation characteristics of the gap material and shock sensitivity of the donor and acceptor charges. We apply a level-set based multimaterial hydrocode with reactive flow models for pentolite donor and heavily aluminized RDX as acceptor charge. The complex shock interaction, critical gap thickness, acoustic impedance, and go/no-go characteristics of the pyrotechnic system are quantitatively investigated.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.21-21
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• 2000

Thrust Cut-Off 시스템은 로켓 발사체의 분리시의 충격에 의한 비행방향오차 및 비행거리를 감소하고 Pay-Load 부에 추진력을 증가시키고 분리된 추진 기관부의 낙하위치 예측을 용이하게 한다. 이와 같이 중요한 역할을 하게되는 Thrust Cut-Off 시스템에서 스냅링은 핵심적인 역할을 하게 된다. 정상적인 추진체의 작동 시에는 고압의 연소가스를 지탱하고 분리 시에는 쉽게 분리되어 연소가스를 역 분사 시켜야한다.(중략)

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.1088-1092
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• 2017

In this study, a comparison of dynamic pressure data measured in hot-firing tests of liquid rocket engine gas generators with different types of dynamic pressure sensors is presented. The dynamic pressure sensors of different types and manufacturers have exhibited different dynamic pressure due to the influence of thermal shock. However, for the characteristic frequencies and RMS(root mean square) values which are important factors for the analysis of combustion instability, the differences between sensors have been found to be negligible.

• Journal of the Korea Society for Simulation
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• v.28 no.2
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• pp.1-14
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• 2019

A full scale hydrodynamic simulation that requires an accurate reproduction of shock-induced detonation was conducted for design of an energetic component system. A detailed hydrodynamic analysis SW was developed to validate the reactive flow model for predicting the shock propagation in a train configuration and to quantify the shock sensitivity of the energetic materials. The pyrotechnic device is composed of four main components, namely a donor unit (HNS+HMX), a bulkhead (STS), an acceptor explosive (RDX), and a propellant (BPN) for gas generation. The pressurized gases generated from the burning propellant were purged into a 10 cc release chamber for study of the inherent oscillatory flow induced by the interferences between shock and rarefaction waves. The pressure fluctuations measured from experiment and calculation were investigated to further validate the peculiar peak at specific characteristic frequency (${\omega}_c=8.3kHz$). In this paper, a step-by-step numerical description of detonation of high explosive components, deflagration of propellant component, and deformation of metal component is given in order to facilitate the proper implementation of the outlined formulation into a shock physics code for a full scale hydrodynamic simulation of the energetic component system.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2000.11a
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• pp.92-97
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• 2000

Low-velocity impact damage of a thick pressure vessel by composite materials was studied using the modified Herzian contact radius theory. Impactors of various masses and various tup shapes were dropped freely in the range of 20m to 200mm height. With acceleration gage and strain gage installed on the impactor, impact force and acceleration and Contact radius were measured. After a test, the samples were radiographed to scan the state of damage. Compared with hemispherical tup of 12.7mm diameter, the contact radius of hemispherical tup of 25.4mm diameter was bigger. And the experimental data and the theoretical data was different due to the mechanical properties difference. The acceleration value was changed linearly according to the height.