• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.8
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• pp.744-749
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• 2011

In this study, determination method of initial optimal nozzle expansion in pintle rocket was investigated. The initial optimal initial nozzle expansion was decided by maximizing the mass-averaged thrust coefficient that is calculated from thrust coefficient of minimum and maximum chamber pressure. The determination of initial optimal initial nozzle expansion was equivalent to that of the minimum propellant mass which was required for obtaining the desired mission performance. The highest pressure, thrust turndown ratio and total impulse ratio effected on the initial optimal nozzle expansion. Among them, total impulse ratio had great influence on the initial optimal nozzle expansion.

• Proceedings of the Korean Society of Marine Engineers Conference
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• 2006.06a
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• pp.221-222
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• 2006

안벽 시운전시 Tug Boat의 지원 없이도 프로펠러의 추력을 감당할 수 있는 Mooring Line의 양을 정하기 위해 선형별 프로펠러의 추력을 추정 계산함.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.58-62
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• 2012

In this study, the hybrid rocket was developed that has a thrust of 1000 kgf level. The static fire test was shown that the thrust was 700 kgf level and trajectory was predicted by the maximum altitude of 12.5 km. The L/D ratio of KHyRoc-I has 28, but the KHyRoc-II were designed the small L/D ratio(18.3) using the seamless aluminium tube(Diameter : 250 mm). And KHyRoc-II has a thrust of 900 kgf level, that is designed with internal ballistics and trajectory was predicted by the maximum altitude of 7.4 km.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.6
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• pp.581-586
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• 2008

The MEMS solid propellant thrusters have very low thrust level for applying to the propulsion system of micro/nano satellites or the side jet thruster of smart bombs. In this research, the fabrication possibility of planar type MEMS solid propellant thrusters that have enlarged burning surface area was examined and the safety of the structure of thruster during the firing test was confirmed. The performance of a micro igniter which is the key component of the MEMS solid propellant thruster was estimated by the ANSYS Icepak and evaluated by the experiment. Finally, the thrust was measured by the micro force sensor. The levels of thrust were 300, 600 mN in the case of K=15, 20.

• 한국가시화정보학회:학술대회논문집
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• 2004.04a
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• pp.9-18
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• 2004

초음속 유동하에서 측추력기 주위의 유동 현상을 실험 및 수치해석을 이용하여 해석하였다. 실험은 버지니아공대의 초음속 풍동과 건국대의 초음속 풍동을 사용하였으며 계산 코드는 Aerosoft 사의 GASP(ver.4.0)과 건국대의 AADL3D를 사용하였다. 실험결과는 Schlieren, Shadow graph 등의 가시화 장치와 압력 센서와 PSP(Pressure Sensitive Paint)를 이용하여 유동장 특성과 압력분포를 구하여 실제 작용되는 힘과 모멘트를 구하였다. 실험조건은 자유류의 흐름이 마하수 4 이고 측추력기와 자유류의 압력비가 532 이었다. 성능향상 방안으로 측추력기 후방에 램프를 설치하는 것을 제안하였으며 이에 대한 실험을 수행하여 수직력에 대한 변화는 없지만 피칭다운 모멘트가 약 $70\%$ 감소함을 보여주어 실제로 성능이 향상되었음을 입증하였다. 또한 측추력기의 성능에 영향을 주는 여러 가지 인자들에 대한 가시화실험을 수행하여 그 이해를 돕고자 하였으며, 현재 건국대에서 보유하고 있는 고속유동 관련 실험장치의 소개와 이를 이용한 연구들을 소개하므로써 압축성 유동장 연구에 이러한 실험장치의 필요성에 대한 이해를 구하고자 한다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.11a
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• pp.215-218
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• 2007

Internal Ballistic modeling and performance prediction for solid propellant micro thruster was performed with heat loss to the chamber wall as an important factor of miniaturization. Simple l-D end-burner type thruster and general HTPB-AP type composite propellant were selected for computation model. The results showed that the performance loss with the heat loss to the surroundings becomes larger as the surface-to-volume ratio is increased. In this case, the total impulse was reduced about 3% of the case in adiabatic condition.

• KSCE Journal of Civil and Environmental Engineering Research
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• v.39 no.1
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• pp.175-181
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• 2019

The hydrostatic pressure, thrust, and wall reflection by a step were studied as the flow resistance due to the discontinuous topography by using the Hwang's scheme in calculating fluxes with an approximate Riemann solver. Compared with the broad-crested weir experiments, the result simulated by using the thrust was the best among them. Hwang's scheme with the thrust by a step was applied to the side weir experiment. The results of simulation agreed well with those of the experiment. Compared to the existing depth-integrated model, the accuracy was slightly lowered, but the running time was reduced to about 20 %.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.11a
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• pp.613-617
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• 2011

Korea Aerospace Research Institute has been designed and manufactured various thurst nozzles of the scramjet engine for optimized configuration. The test campaign for thurst nozzle characteristics was performed at T4 free-piston shock tunnel in University of Queensland, Australia. Total 8 kinds of thrust nozzles and 2 kinds of side walls were manufactured for this campaign. In this paper, the design and specification of thrust nozzles was reported. Based on the static pressure distribution of the engine and pitot pressure distributions at nozzle exit, The positive net thurst was observed with baseline case of the test campaign.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.48 no.8
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• pp.611-620
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• 2020

The effect of discharge voltage on electron mean energy, electric potential, ionization rate, neutral and ion density of Hall thruster was analyzed using a two-dimensional axisymmetric hybrid model. The results of the code developed for this study such as discharge current, thrust, and plasma distribution according to discharge voltage of SPT-100ML Hall thruster were compared by experiments and calculations of other researchers for validation. The results show that the electron mean energy, the ionization rate, and the ion density are increased while the neutral density is decreased as the discharge voltage is increased. The thrust and the discharge current are proportional to the discharge voltage.

• Aerospace Engineering and Technology
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• v.1 no.2
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• pp.51-56
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• 2002

Satellite propulsion system is employed for orbit transfer, orbit correction, and attitude control. The monopropellant feeding system in the low-earth-orbit satellite blowdowns fuel to the thrust chamber. The thrust produced by the thruster depends on fuel amount flowed into the combustion chamber. If the thruster valve be given on-off signal from on-board commander in the satellite, valve will be opened or closed. When the thrusters fire fuel flows through opened thruster valve, instantaneous stoppage of flow in according to valve actuation produces transient pressure due to pressure wave. This paper describes transient pressure predictions of the KOMPSAT-2 propulsion system resulting from latching valve and thrust control valve operations. The time-dependent set of the fluid mass and momentum equations are calculated by MOC.