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

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.18-18
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• 1999

추진제의 비추력 및 밀도 등을 효과적으로 증진시키기 위해 알루미늄 분말의 함량을 높인 고 알루미늄 추진제가 로켓모터에 널리 사용되고 있다. 추진제 내 알루미늄 성분은 연소과정의 이상유동으로 인하여 로켓의 성능 및 내열설계에 많은 영향을 미칠 수 있다. 즉, 산화알루미늄 입자가 노즐 벽면에 달라붙어 추력의 손실을 가져오기도 하고 노즐 입구에 침적되어 내열재의 삭마가 과다해져 최악의 경우 모터의 파손을 일으켜 임무수행에 실패를 초래할 수도 있다.

• Journal of Aerospace System Engineering
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• v.11 no.6
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• pp.56-63
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• 2017

Thrust force induced by the dielectric barrier discharge inside of cylinder pipes is measured for various conditions. The input peak-to-peak voltage and frequency are varied from 2 to 9 kVpp and from 5 to 15 kHz, respectively. The height of cylinder is varied from 50 to 100 mm. The results of the measurements show that the magnitude of the generated thrusts increases as the voltage and the frequencies increase. It also shows that the generated thrusts are decreased according to the increase in the height of the cylinder. The cause of the thrust decrease is discussed in terms of energy losses due to the frictions on the wall surface.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.5
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• pp.456-465
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• 2015

Dual-bell nozzle can overcome the performance losses of the conventional bell-shaped nozzles which induced by off-design operations with either over-expanded or under-expanded exhaust flow and minimize the losses of the specific impulse. In United States, Rocketdyne analyzed thrust characteristics according to the shape of the expansion nozzle and NASA conducted hot firing tests with various altitudes. DLR, which is one of the research institute of the Europe, is carrying out research for the different cases of inflection angle, nozzle length and expansion ratio. MAI of Russia applied the slot nozzle to the expansion region in order to reduce the performance losses. In Asia, both the Japan and the India are researching on the dual-bell nozzle and Mitsubishi cooperation of the Japan registered its patent. In this paper, concepts and performance of dual-bell nozzle, which can compensate altitude, are investigated and trends of current research are summarized. It is necessary for Korea to research on the dual-bell nozzle for lucrative space development.

• Journal of the Korean Society of Propulsion Engineers
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• v.5 no.4
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• pp.57-66
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• 2001

The precise prediction of the performance is essential to develope the system at the development of propulsion system since no experimental data are available. The accuracy of 1on the total system's performance as well as itself, which depends on how the correction fac $I_{sp}$, and so on, are determined in accurate. However some of the design factors are dete engineer's experience or the similar test data if they are available, so far. This study was the method of the determination of correction factors of both $I_{sp}$ and thrust in direct. The bas is to define the detail performance loss mechanism of solid rocket motors, might be occurre and to calculate in quantitative those correction factors from the performance loss mechanism the test results, the model of this study can predict those factors less than 1% error, in additi physical variances of each loss mechanism.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.2
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• pp.34-41
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• 2012

Thrust vector control system is a control device which is mounted on the exit of the nozzle to generate pitch, yaw and roll directional force by deflecting flow direction of the supersonic jet from the nozzle. Thermal and aerodynamic loads are acting on the surface of jet vane when it is exposed to the jet flow. Axial thrust loss and side thrust loss are affected by shock patterns and interactions between jet-vanes which varies with jet-vane geometry and turning angle. In this research, the performance estimation using the numerical simulation analysis of the nozzle is given and the investigation of the flow visualization and aerodynamic performance with the enforced power to the vane is taken.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2009.05a
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• pp.49-52
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• 2009

The response times of monopropellant thrusters at a pulse mode were investigated experimentally as design parameters and feed pressure conditions. Five different model thrusters as injection direction/uniformity, aspect ratio of reactor, volumes of manifold and chamber were designed. As a results, two parameters, aspect ratio and manifold volume, were directly related to response characteristics. Additionally, chugging instability at reaction chamber was observed when pressure drop across the catalyst bed was increased due to high aspect ratio or when low pressure was built at reaction chamber.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.11a
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• pp.30-30
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• 2000

일반적인 소형 고체로켓의 모터 내에는 연료 첨가제로써 알루미늄이 함유되는데, 연소 시 산화된 이 성분은 액적 상태로 이동하여 노즐부내에 이상유동장을 형성시킨다. 이러한 산화알루미늄입자는 노즐벽면에 충돌, 점착하여 기계적, 열적 에너지전달을 일으키며 노즐벽면의 삭마를 유발시키는 한편, 가스유동과의 속도 차, 온도차로 인해 저항요소로 작용하면서 노즐의 추력 성능 손실에 간접, 직접적인 원인이 된다.(중략)

• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.2
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• pp.24-30
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• 2016

An experimental study for the characteristics of the thrust-vectoring of a sonic jet utilizing the coanda flap installed at a rectangular nozzle exit is performed. Two side plates are installed at both sides of the flap to decrease the three dimensional effects of the jet on the flap surface. Schlieren flow visualizations and quantitative measurements of the deflection angle of thrusting vector show that the side plates are able to delay the separation of the jet at the downstream of the flap surface. Substantial increase in the deflection angle of the jet as high as $72^{\circ}$ and small thrust loss as low as 7% are obtained by the present thrust-vectoring technique using the side plates.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.3
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• pp.77-81
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• 2012

In a cryogenic propellant tank the pressurant is contracted due to heat loss and the propellant itself evaporates. On a restartable propulsion system such phenomena are more intensive because the propellant contacts with the pressurant on the larger surface during the coast flight. Such heat and mass transfer phenomena should be considered for estimating the amount of pressurant. On the hypothesis that the heat and mass transfer quasi-equilibrium is achieved during the coast flight, the calculation process of the equilibrium pressure is presented. On the process the amount of loaded helium on the Falcon-1 second stage is calculated.