• Title, Summary, Keyword: Propulsion control device

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A Parametric Study on Double-Slit-Type Rupture Disc of Pulse Separation Device (펄스분리장치의 이중 슬릿형 파열판 매개변수 연구)

  • Han, Houk-Seop;Cho, Won-Man;Lee, Won-Bok;Koo, Song-Hoe;Lee, Bang-Eop
    • Journal of the Korean Society of Propulsion Engineers
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    • v.14 no.5
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    • pp.101-110
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    • 2010
  • Dual pulse rocket motor is a solid motor with two grains separated by a bulkhead and rupture disc. The elasto-plastic explicit dynamic analysis for the rupture disc was conducted by finite element method. The effect of the slit geometry of a rupture disc was parametrically analyzed in terms of rupture time and shape. The results can be used to control the rupture pressure by changing the slit geometry of rupture disc.

A Parametric Sturdy on Double Slit Type Rupture Disc of Pulse Separation Device (펄스분리장치의 이중 슬릿형 파열판 매개변수 연구)

  • Han, Houk-Seop;Cho, Won-Man;Koo, Song-Hoe;Lee, Bang-Eop
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.105-112
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    • 2010
  • Dual Pulse Rocket Motor is a solid rocket motor with two grains separated by a bulkhead and rupture disc. The elasto-plastic explicit dynamic analysis of rupture disc was conducted by finite element method. The effect of the slit geometry of a rupture disc was analyzed for rupture time and shape by the parametric study. The results can be used to control the rupture pressure by the change the slit geometry of a rupture disc.

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A Parametric Study on Rupture Disc with Radial Slit of Pulse Separation Device (원주방향 슬릿을 가진 파열판의 매개변수 연구)

  • Han, Houk-Seop;Cho, Won-Man;Lee, Won-Bok;Koo, Song-Hoe;Lee, Bang-Eop
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.261-264
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    • 2010
  • Dual Pulse Rocket Motor is a solid rocket motor with two grains separated by a bulkhead and rupture disc. The elasto-plastic explicit dynamic analysis of rupture disc was conducted by the finite element method. The effect of the slit geometry of rupture disc with radial slit was parametrically analyzed in terms of rupture time and shape. The results can be used to control the rupture pressure by changing the slit geometry of rupture disc.

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Mechanical Isolation Method for an Air Intake Duct with Vertical Temperature Gradient (수직 온도구배를 갖는 공기 흡입 덕트의 기계적 격리기법)

  • Jung, Chihoon
    • Journal of the Korean Society of Propulsion Engineers
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    • v.20 no.4
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    • pp.87-93
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    • 2016
  • In a Direct Connect(DC) mode altitude engine test, a labyrinth seal is set up between an air intake duct and an engine. The labyrinth seal plays a key role in mechanically isolating them, which contributes to the accurate measurement of thrust and the other component forces. However, when high vertical temperature gradient is generated in the supplied air in the duct, the isolation breaks down. In this paper, a labyrinth seal control device is designed and installed in an effort to eliminate the issue. Test result shows the device successfully gets rid of the contact problem even when high vertical temperature gradient is produced.

Localization development study of KTX On-Board Computer System (KTX 차량컴퓨터제어장치(OBCS) 국산화 개발 연구)

  • Jung, Do-Won;Kim, Hyun-Sik;Kang, Ki-Seok;Kim, Hyeong-In;Jung, Sung-Youn
    • Proceedings of the KSR Conference
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    • pp.518-523
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    • 2008
  • Using network communication, KTX OBCS is KTX's core device which inspects operation status of various electric equipments and supports driving command, train control, train's maintenance, train crew's driving. Since this device is manufactured as specialized system, being dependent on TGV manufacture specification and France's high speed train operation method, actual technic transfer is difficult. Therefore, there are many difficulties, since most of interface signals are connected with OBCS when function improvement, maintenance, various electric equipments(propulsion control device, auxiliary power supply device, door control device etc.) are replaced with localized ones, which are required in operational view after introduction of KTX. Ergo, this study would like to contribute to function improvement and maintenance's efficiency, furthermore to realize technical independence, escaping from dependency of developed foreign technology in high speed train and electric equipments, through KTX OBCS' function analysis and mutual interface information analysis with peripheral device(driver console, PID system, fault display device, various electric equipments).

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The Study of Aerodynamic Characteristics of Jet-Vane Affected by the Shroud (Shroud의 영향에 따른 제트 베인의 공기역학적 특성 연구)

  • Park, Soon-Jong;Park, Jong-Ho
    • 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.

Study on Supersonic Jet Noise Reduction Using a Mesh Screen (메쉬 스크린을 이용한 초음속 제트소음 저감법에 관한 실험적 연구)

  • Kweon, Yong-Hun;Lim, Chae-Min;Kim, Heuy-Dong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.377-381
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    • 2006
  • This paper describes experimental work to control supersonic jet noise using a mesh screen that is placed at the nozzle exit plane. The mesh screen is a wire-gauze screen that is made of long stainless wires with a very small diameter. The nozzle pressure ratio is varied to obtain the supersonic jets which are operated in a wide range of over-expanded to moderately under-expanded jets. In order to perturb mainly the initial jet shear layer, the hole is perforated in the central part of the mesh screen. The hole size is varied to investigate the noise control effectiveness of the mesh screen. A schlieren optical system is used to visualize the flow fields of supersonic jet with and without the mesh screen device. Acoustic measurement is performed to obtain the OASPL and noise spectra. The results obtained show that the present mesh screen device leads to a substantial suppression of jet screech tones. The hole size is an important factor in reducing the supersonic jet noise. For over-expanded jets, the noise control effectiveness of the mesh screen appears more significant, compared to correctly and under-expanded jets

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Characteritic Analysis of Hybrid Levitation and Propulsion System for Super-Speed Maglev (초고속 자기부상열차를 위한 하이브리드형 부상 추진 시스템의 특성 해석)

  • Cho, Han-Wook;Lee, Jong-Min;Han, Hyung-Suk
    • Proceedings of the KIEE Conference
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    • pp.623_624
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    • 2009
  • This paper deals with the characteristic analysis of electro-magnet (EM)-permanent magnet (PM) hybrid levitation and propulsion device for magnetically levitated (maglev) vehicles. Several machine characteristics such as levitation force with/without control current and thrust are described. In order to verify the analysis results and feasibility of high-speed operation of the maglev vehicle, real-scale static test set is implemented and tested.

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Flow Control in the Vacuum-Ejector System (진공 이젝터 시스템의 유동 컨트롤)

  • Lijo, Vincent;Kim, Heuy-Dong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.321-325
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    • 2010
  • Supersonic ejectors are simple mechanical components, which generally perform mixing and/or recompression of two fluid streams. Ejectors have found many applications in engineering. In aerospace engineering, they are used for altitude testing of a propulsion system by reducing the pressure of a test chamber. It is composed of three major sections: a vacuum test chamber, a propulsive nozzle, and a supersonic exhaust diffuser. This paper aims at the improvement of ejector-diffuser performance by focusing attention on reducing exhaust back flow into the test chamber, since alteration of the backflow or recirculation pattern appears as one of the potential means of significantly improving low supersonic ejector-diffuser performance. The simplest backflow-reduction device was an orifice plate at the duct inlet, which would pass the jet and entrained fluid but impede the movement of fluid upstream along the wall. Results clearly showed that the performance of ejector-diffuser system was improved for certain a range of system pressure ratios, whereas the orifice plate was detrimental to the ejector performance for higher pressure ratios. It is also found that there is no change in the performance of diffuser with orifice at its inlet, in terms of its pressure recovery. Hence an appropriately sized orifice system should produce considerable improvement in the ejector-diffuser performance in the intended range of pressure ratios.

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Fundamental Experiment for Solid Propellant Micro-Propulsion devices (고체추진 마이크로 추진 장치에 대한 기초실험)

  • Kim Youn-ho;Jung Sung-chul;Oh Hwa-young;Huh Hwanil
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.39-43
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    • 2005
  • In this paper, we describe the contents of the achievement of basic experiments for manufacturing and evaluating a micro-rocket using solid propellant, as the device of the micro thrust generator which can be used for attitude control of satellites. We try to analyze performance of the rocket through visualization of the motor jet, and adopt various ignition methods to obtain confidence in ignition problem. For this purpose, we develop and test two different types of thrust measurement system.

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