• Journal of the Korean Society of Propulsion Engineers
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• v.27 no.1
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• pp.9-16
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• 2023

This paper investigated the method to predict a thermal response of internal insulation in a solid rocket motor considering both thermal decomposition and ablation. Changes in properties due to the thermal decomposition, swelling of char layer and movement of decomposition gases inside the material were considered during a modeling. And radiative/convective heat flux from the exhaust gas were applied as boundary conditions, while the chemical ablation of the material surface is modeled with algebraic equations. Test SRM with thermocouples was solved for a validation purpose. The results showed that predicted temperatures have identical trends and values compared to the experimental values. And an error of predicted thermal destruction depth was around 0.1 mm.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.1
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• pp.36-44
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• 2012

Multi-injector rocket engine using high-concentrated hydrogen peroxide and kerosene was designed and manufactured. Design requirements of a rocket engine were determined and main geometrical parameters of rocket engine were determined on the basis of fundament. Six coaxial swirl injectors were mounted on the multi-injector engine. Flow analysis in the hydrogen peroxide manifold was performed to minimize stagnation and recirculation zones. Finally, the optimized hydrogen peroxide manifold was manufactured and cold flow test was carried out to confirm mass flow rate per uni-element, spray pattern and atomization characteristics. The results of cold flow test showed that the mixing head design process was successful and enough to use as a essential database for the development of a full-scale engine.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2017.05a
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• pp.131-136
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• 2017

High speed under water vehicle by using solid rocket motor, which is a natural cavitation type, was tested. The vehicle's speed and running distance was measured, and pressure sensors installed on the surface of the vehicle show pressure-time history of pressures according to the development of the supercavitation. Underwater cameras installed on the wall of the test pool recorded whole processes from the onset of the supercavitation to fully developed one. CNU-SuperCT based on 2-dimensional inviscid theoretical analysis was used to simulate the test result. In consideration of CNU-SuperCT does not include the control fins of the vehicle, simulation results agree with test results very well. Also, pictures from underwater cameras support the test results.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.1
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• pp.1-8
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• 2020

In this study, a configuration design of a CH₄/LOx small rocket engine was made and test system was established for the performance evaluation. A coaxial swirl injector was chosen because of its remarkable atomization performance and low combustion instability. Three aspect ratios for the combustion chamber configuration, i.e., 1.5, 1.8, and 2.1 were also set for the comparison of the combustion efficiency. The reliability of the thrust measurement rig was enhanced by pre-and post-calibration process. From the preliminary ground hot-firing test, the measured thrust and specific impulse values were 89.2 N and 181.8 s, respectively, which were 21.6% lower than the ideal values. In addition, the efficiency of characteristic velocity was measured as 84.2%.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.4
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• pp.12-17
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• 2018

A natural cavitation-type high-speed underwater vehicle with solid rocket motor is tested, and its speed and running distance are measured. The outputs from pressure sensors on the surface of the vehicle reveal a pressure-time history reflecting the development of supercavitation. Underwater cameras installed on the wall of the test pool record the entire process from the onset of supercavitation to its full development. CNU-SuperCT, based on two-dimensional inviscid theoretical analysis, is used to simulate test results. Considering CNU-SuperCT does not include the control fins of the vehicle, simulation results agree with test results very well. Additionally, pictures from underwater cameras support the test results.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.4
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• pp.55-65
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• 2020

In this paper, development and acceptance test results of 75-tonf class liquid rocket engine gas generators are described. Up to now, more than 330 times and cumulative time of 7,000 seconds gas generator autonomous tests have been carried out with 44 gas generator models. Through the tests it was verified that 75 tonf gas generator shows very reliable and reproducible characteristics in terms of chamber pressure, combustion efficiency, pressure loss, combustion stability, burnt gas temperature, and etc. 5 gas generators which are the last series of 75 tonf gas generator for the Korea Space Launch Vehicle II, will be manufactured until end of 2019 and their acceptance tests will be executed at the first half of 2020.

• Journal of the Korean Society of Propulsion Engineers
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• v.24 no.4
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• pp.73-78
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• 2020

The main reasons that ignite the propellant in the process of producing solid rocket motor are worker mistakes, wrong working process, mechanical defects, impact, friction, electrostatic and short circuits. In the past decades, many accidents have occurred in the process of producing solid rocket motor, accidents investigation have confirmed that the sensitivity of electrostatic is very high under specific condition. In this paper, we analyzed overseas accident cases and measured the sensitivity of electrostatic in the situation of confinement and pressure load by considering the manufacturing process. As a result of the test, the sensitivity of propellant was increased in the situation of confinement and pressure load and the propellant reacted more sensitively to electrostatic in the situation of confinement than pressure load.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.15-18
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• 2008

This study fulfilled analysis of startup characteristics of Turbo pump unit-Gas generator open loop test from the viewpoint of simulation. The test results were investigated and the calculated results were compared to test results. The curve for RPM developing predicted by simulation agreed well with test result. The slope of transient combustion pressure of gas generator correspond with test result.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.19-22
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• 2008

This study fulfilled analysis of startup characteristics of Turbo pump unit-Gas generator closed loop test from the viewpoint of simulation. The test results were investigated and the calculated results were compared to test results. The curve for RPM developing predicted by simulation agreed well with test result. The slope of transient combustion pressure of gas generator correspond with test result.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1998.10a
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• pp.29-29
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• 1998

실전 배치되어 운용 중인 무기체계는 여러 형태의 사고 위험이 항상 존재한다 이중에서도 특히 항공기나 함정에서 발생하는 사고는 그 피해가 막대하게 커질 수도 있어 항공기나 함정 자체에 위협을 줄 수도 있다. 이러한 사고위험으로부터 인적, 물적 자원을 보호하기 위하여 둔감탄약(Insensitive Munitions)에 대한 인식이 높아지고 있으며, 아울러 이러한 무기 체계를 효과적으로 시험 평가하는 규격들이 검토되기 시작하여 1991년에 "Hazards Assesment Tests for Non-Nuclear Ordnance, DoD-STD-2105"를 기초로 한 MIL-STD-2105B가 채택되었다. 본 논문에서는 MIL-STD-2105B의 해석과 그에 따른 둔감탄약 시험에 포함되는 Bullet Impact Test, Fast Cookoff Test, Slow Cookoff Test, Fragment Impact Test, Sympathetic Detonation Test 등의 시험들의 세부적인 시험방법과 그 결과에 대한 판정 기준을 서술하였다. 또한 유도무기의 추진기관을 모델로 하여 둔감탄약 시험의 기준을 제시하였고 이 시험을 통과하기 위하여 향후 연구, 개발하여야 할 분야를 서술하였다.