• Title, Summary, Keyword: Propulsion control device

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The study of aerodynamic characteristics to design of optimum jetvane (제트베인 최적 설계를 위한 공기역학 특성 연구)

  • 신완순;길경섭;이택상;박종호;김윤곤
    • Journal of the Korean Society of Propulsion Engineers
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    • v.5 no.1
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    • pp.26-33
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    • 2001
  • Thrust vector control system is control device which is mounted exit of the nozzle to generate pitch, yaw and roll directional force by deflecting flow direction of the supersonic jet from the nozzle. By obtaining control force, jetvane which is exposed in jet flow is working thermal and aerodynamic load. Axial thrust loss and side thrust is affected by shock patterns and interactions between jetvanes according to jetvane geometry and turning angle. In this study, we designed 6 types of jetvane to evaluate pitch, yaw and roll characteristics of ietvane in supersonic flow, and perform the cold flow test in range of turning angles of jetvanes between $0^{\cire}$ and $25^{\cire}$ by $5^{\cire}$ respectively. Also, calculation is going side by side to analyse flow interaction. Results show that there is no interactions between jetvanes upto turning angle 20$^{\circ}$, chord and lead length ratio is very important parameter to aerodynamic performance and maximum thrust loss is appeard to 17% of axial thrust in roll directional control.

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Control of the Pressure Oscillation in a Supersonic Cavity Flow Using a Sub-cavity (Sub-cavity를 이용한 초음속 공동유동의 압력진동 제어)

  • Lee Young-Ki;Jung Sung-Jae;Kim Heuy-Dong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.310-313
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    • 2006
  • The present study aims at investigating the effectiveness of a new passive cavity flow control technique, sub-cavity. The characteristics of cavity flow oscillation with the device are compared with those with other control techniques tested previously, including a triangular bump and blowing jet. In the computation, the three-dimensional, unsteady Navier-Stokes equations governing the supersonic cavity flow are solved based on an implicit finite volume scheme spatially and multi-stage Runge-Kutta scheme temporally. Large eddy simulation (LES) is carried out to properly predict the turbulent features of cavity flow. The present results show that the pressure oscillation near the downstream edge dominates overall time-dependent cavity pressure variations, and the amplitude of the pressure oscillation can be reduced in the presence of a sub-cavity.

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Analysis of Performance and Combustion Characteristics in KSR-III Liquid Rocket Engine with Combustion Instability Passive Control Device(Baffle) (연소 불안정 수동제어 기구(배플)를 장착한 KSR-III 액체 로켓엔진의 성능 및 연소특성 해석)

  • 문윤완;류철성;설우석;김영목;이수용
    • Journal of the Korean Society of Propulsion Engineers
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    • v.7 no.4
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    • pp.63-72
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    • 2003
  • The combustion characteristics of the KSR-III engine were investigated numerically from the viewpoint of performance and combustion field. For numerical analysis of KSR-III engine with hub-and-spoke baffle, 3-D calculation was performed about $30^{\cire}$ section and the prediction of performance was in a good agreement with hot-firing test result. As a result of baffle installed, the performance of KSR-III engine was reduced in comparison with no baffle case and local high temperature region appeared on injector plate, combustion wall and baffle wall, This calculation was used practically as basic data for designing injector plate with film cooling holes and predicting the performance of KSR-III final flight test.

Review of POGO and PSD (POGO와 PSD의 소개)

  • 고광웅;이한주;정동운;이상용
    • Journal of the Korean Society of Propulsion Engineers
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    • v.7 no.4
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    • pp.1-9
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    • 2003
  • To reduce the possibility of longitudinal dynamic instability, called "POGO", in the liquid rocket system due to the feedback effect of a main structure and a fuel-feeding system, several different types of PSD(POGO Suppression Device) systems have been studied. In the present study, several different types of PSD were reviewed. Basically, all PSD systems can be categorized into two groups; a passive PSD or an active PSD. We can classify the passive PSD's into more detailed groups according to their compliance methods; localized compliance methods or distributed compliance methods. As a result of our intensive review on various PSD's, the gas-filled accumulator with a level control system is considered to be the most suitable one to suppress the POGO instability without mal-effects to the performance of a fuel-feeding system.ng system.

Development of the Condition Monitoring Test Cell Using the Micro Gas Turbine Engine (초소형 가스터빈을 이용한 상태감시 시험장치 개발)

  • Kho, Seong-Hee;Ki, Ja-Young;Koo, Young-Ju;Kong, Chang-Duk;Lee, Eun-Woo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.345-349
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    • 2009
  • This test cell is developed to the institutes or laboratories research and study gas turbine engine for academic purpose with this test data to provide the fundamentals of operational mechanism and structural configuration, and further to verify thermodynamic calculation The test cell is installed to monitor and compare real-time data with reference engine model performance simulation data. using by NI DAQ(Data acquisition)device and LabVIEW program based on 30lbf-micro turbojet engine.

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Development of the Performance Test Cell Using the Small Gas Turbine Engine of 80 lbf-Thrust (80lbf급 소형 가스터빈 엔진의 성능 시험장치 개발)

  • Jin, Hak-Su;Kho, Seong-Hee;Ki, Ja-Young;Yong, Seong-Ju;Kang, Myoung-Cheol;Lee, Eun-Woo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.495-498
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    • 2010
  • This test cell is developed to the institutes or laboratories research and study gas turbine engine for academic purpose with this test data to provide the fundamentals of operational mechanism and structural configuration, and further to verify thermodynamic calculation The test cell is installed to monitor and compare real-time data with reference engine model performance simulation data. using by NI DAQ(Data acquisition)device and LabVIEW program based on 80 lbf-micro turbojet engine.

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Experimental approach for catalyst bed sizing of liquid propellant thruster (50 Newton 급 액체 추력기의 촉매베드 사이징)

  • An, Sung-Yong;Kwon, Se-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.145-148
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    • 2008
  • A 50 Newton monopropellant thruster being developed for attitude control in a variety of aerospace application systems is described in this paper. A scaled down thruster with platinum on aluminum oxide in the reaction chamber was tested to determine the catalyst capacity. A scaled up thruster, was designed and fabricated using data obtained on small scale device, was evaluated by decomposition efficiency based on temperature, efficiency of characteristic velocity, and measurement of thrust. The performance of a scaled up thruster was 42 Newton in thrust, 98 % in efficiency of characteristic velocity, and 123 sec in specific impulse at sea level.

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Development of the Educational Micro Gas Turbine Engine Performance Test System (교육용 마이크로 가스터빈 엔진 성능 시험장치 개발)

  • Kho, Seong-Hee;Ki, Ja-Young;Park, Mi-Young;Kong, Chang-Duk;Lee, Kyung-Jae
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.31-35
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    • 2008
  • This test cell is developed to provide the fundamentals of operational mechanism and structural configuration, and further to verify thermodynamic calculation with this test data to the institutes or laboratories research and study gas turbine engine for academic purpose. The test cell is installed to monitor and collect real-time data as to temperature, pressure, thrust, fuel flow, and air flow etc. using by NI DAQ(Data acquisition)device and LabVIEW program based on 30lbf-micro turbojet engine.

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Experimental approach for catalyst bed sizing of liquid propellant thruster (액체추력기 촉매베드 크기 결정을 위한 실험적 방법)

  • An, Sung-Yong;Kwon, Se-Jin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.3
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    • pp.24-33
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    • 2008
  • A 50 Newton monopropellant thruster being developed for attitude control in a variety of aerospace application systems is described in this paper. A scaled down thruster with platinum on aluminum oxide in the reaction chamber was tested to determine the catalyst capacity. A scaled up thruster which was designed and fabricated using data obtained from a small scale device was evaluated by its decomposition efficiency based on the temperature, the efficiency of characteristic velocity, and the measurement of thrust. The performance of a scaled up thruster was marked by a measured thrust of 42 Newton, 98 % efficiency of the characteristic velocity, a specific impulse of 123 sec at sea level.

The State of the Art and Application of Actuator in Aerospace (항공우주용 구동장치 개발 동향)

  • Yoon, Gi-Jun;Park, Ho-Youl;Jang, Ki-Won
    • Journal of the Korean Society of Propulsion Engineers
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    • v.14 no.6
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    • pp.89-102
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    • 2010
  • In this paper, a study on the future-oriented actuator introduces the future technology and future direction in aerospace and several industry fields. In particular, the mechanical linkage or hydraulic and pneumatic actuators which have the higher output-to-weight ratio have been used a lot in the past as the aircraft's flight control device. Most recently, Fly-By-Wire system has been used in aircraft and the flight control system has been changed in more electric and all electric systems. Electrohydraulic actuators and electric actuators have been developed continually, because they have better efficiency, safety and lower cost for the flight control system of aircraft. Also, to improve the weight condition, accuracy and response of actuator, new field actuators using new materials have been developed. In this paper we clearly proposed the actuator design and detailed technology development trend for next generation actuation system in aerospace and new field.