• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2011.11a
• /
• pp.218-222
• /
• 2011

During the development of the iridium catalyst for domestic production, the catalyst failure, loss, sintering phenomena are observed by high pressure and temperature. By these abnormal failure of catalyst bed, the performance of thruster is degraded. To figure out the detail phenomena on the damaged catalyst bed, a numerical analysis code is developed by assuming the catalyst bed as an one dimensional porous media. The numerical analysis code is validated with experiment data. Thereby, resulting physical phenomena are examined by considering the variation of catalyst bed characteristics incurred by catalyst granule failure. Through these numerical analyses we figure out the effect of the catalyst loss on the decomposition of hydrazine and ammonia.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 2009.05a
• /
• pp.61-64
• /
• 2009

A study on the variation of combustion performance by oxidizer/fuel ratio was conducted. Shower head type injector was used. Injector propelled by liquid kerosene and liquid hydrogen peroxide. The designed operation condition for thrust and combustion pressure were 200N and 10bar. It is found that optimum oxidizer/fuel ratio.

• 보일러설비
• /
• s.81
• /
• pp.101-102
• /
• 2000

• Proceedings of the Korea Society for Energy Engineering kosee Conference
• /
• 2000.04a
• /
• pp.299-302
• /
• 2000

• 한국연소학회:학술대회논문집
• /
• 2001.11a
• /
• pp.73-82
• /
• 2001

The characteristics of the catalytically supported thermal combustion with Pd-based catalyst using the bench scale high pressure combustor has been investigated up to 7 atm. The emission of $NO_{\chi}$ depends on the preheating temperature and the excess air ratio. Most $NO_{\chi}$ emission seems to come from the pre-burner for the preheating of the inlet gas. Decreasing excess air ratio in the inlet gas below 1.5 results in the stable catalytically supported thermal combustion in the post combustion region while the $NO_{\chi}$ emission increased up to 15 ppm. Further, the increase of the pressure shows the dramatic increase of the emission CO and THC. However, the $NO_{\chi}$ emission decreased slightly due to the lower combustion temperature at the high pressure.

• Journal of Institute of Convergence Technology
• /
• v.10 no.1
• /
• pp.19-24
• /
• 2020

The purpose of the study is to investigate the thermal durability characteristics of the Pt catalyst and additives used in a catalytic combustor. The catalyst used in the experiment was based on Pt (3 wt%), and a total of 12 types were prepared using a combination of additives (Ni, La, Ce, Fe, and Co). From the results, In the fresh state, the two types of combination catalysts with the highest C₃H₈ conversion were Pt_Ce (79.9%) at 500℃, and in the three types of combination catalysts, Pt_La_Ni (93.4%) at 500℃ had the best performance. Among aged catalysts at 850℃ and 8 hours, Pt-La-Ni and Pt-Ni-Ce catalysts showed the highest C₃H₈ conversion of about 71% at 500℃.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.18 no.6
• /
• pp.59-67
• /
• 2014

Acceptance level random vibration and life firing test for development model of 1 N-class monopropellant thruster have been performed. From the results of random vibration, the natural frequency of the dual thurst module composed of 1 N-class development model thrusters was higher than the part level requirement(>100 Hz) and the structural robustness was verified. Thrust decrease of steady sate was below 7% and thrust instability was within ${\pm}5%$ in the life firing test using over 20 kg propellant throughput. The computerized tomography for catalyst bed showed a less than 7% of catalyst loss and it revealed the design appropriateness of the current thruster development model.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.11 no.4
• /
• pp.67-73
• /
• 2007

In recent years hydrogen peroxide has become considerably more attractive as a green rocket propellant so a laboratory model of hydrogen peroxide thruster adopted silver catalyst and a test facility has been developed to research a hydrogen peroxide propulsion. The design scheme of thruster and the test data are presented including ignition delay, efficiency of characteristic exhaust velocity. As a result, 95% of efficiency of characteristic exhaust velocity was obtained at steady state operation condition.

• Proceedings of the Korean Society of Propulsion Engineers Conference
• /
• 1997.04a
• /
• pp.205-211
• /
• 1997

최근 유도무기 분야에서 많이 사용되고 있는 가스발생기는 온도가 낮고, 독성이나 부식성이 없는 연소 가스를 요구하고 있기 때문에 산화제로 Ammonium Nitrate(AN)를 주로 사용하고 있다. 그러나 순수한 AN은 온도에 따라 상이 변하는 단점이 있기 때문에 Phase Stabilized Ammonium Nitrate(PSAN)을 사용하고 있으며, 일반적으로 PSAN은 AN과는 다른 연소특성을 갖는다. 본 연구에서는 가스발생기용 추진제의 조성을 연구하면서, 상안정제로 $KNO_3$와 $KCIO_4$을 사용하여 자체적으로 제조한 PSAN들과 ZnO=3%인 PSAN을 사용하여 얻은 추진제의 연소특성을 고찰하였고, 연소촉매를 사용하거나 RDX나 소량의 AP를 사용하여 보다 다양한 연소속도를 갖는 추진제를 제조할 수 있었다.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.17 no.6
• /
• pp.30-37
• /
• 2013

A ground hot-firing test was conducted to take out the optimal design configurations for the catalyst bed of liquid-monopropellant hydrazine thruster which could be used for primary engine or attitude control thruster of space vehicles. Performance characteristics with the variation of thrust-chamber length are investigated in terms of thrust, specific impulse, chamber pressure, characteristic velocity, and hydrazine decomposition rate. Additionally, the correlations between propellant-supply pressure and performance parameters are given. As results, increase of catalyst-bed length leads to performance degradation in this test condition, and also decreases propellant consumption efficiency with the supply pressure variation.