• Title, Summary, Keyword: Propulsion control device

Search Result 71, Processing Time 0.04 seconds

The effects of the Control of Combustion Instabilities in accordance with various Acoustic Cavities (음향공 형상에 따른 연소 불안정 제어 효과)

  • Cha Jung-Phil;Yang Jea-Jun;Seo Ju-Hyoung;Kim Hong-Jip;Ko Young-Sung
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • /
    • pp.73-76
    • /
    • 2006
  • Acoustic cavity as a stabilization device to control high-frequency combustion instabilities in liquid rocket engine is adopted and its damping capacity is verified in atmospheric temperature. Geometric effects of acoustic cavity on damping characteristics are analyzed and compared quantitatively. Satisfactory agreements have been achieved with linear acoustic analysis and experimental approach. Results show that the acoustic cavity of the largest orifice area or the shortest orifice length was the most effective in acoustic damping of the harmful resonant frequency finally, it is proved that an optimal design process is indispensable for the effective control of combustion instabilities.

  • PDF

Flow Analysis in Precision Control Valve for Satellite Attitude Control (인공위성 자세제어를 위한 Direct Acting 정밀 유량 제어 밸브내의 유동해석)

  • Bae Young-Woo;Oh Ju-Young;Lee Jae-Woo;Lee Sung-Taek;Byun Yung-Hwan
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • v.y2005m4
    • /
    • pp.427-430
    • /
    • 2005
  • The precision control valve flow of satellite attitude control device was analyzed in this paper, Then, force of flow in valve was calculated for plunger surface. We made an offer about basic data for optimal plunger design.

  • PDF

Visualization device of solid fuel combustion in hybrid rocket (하이브리드 로켓에서의 고체 연료 연소 가시화 장치)

  • Moon, Keun-Hwan;Cho, Jung-Tae;Kim, Soo-Jong;Lee, Jung-Pyo;Kim, Hak-Chul;Oh, Ji-Sung;Moon, Hee-Jang;Sung, Hong-Gye;Kim, Jin-Kon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • /
    • pp.206-209
    • /
    • 2010
  • The visualization device for hybrid rocket is fabricated to investigate the combustion phenomena. Visualization device were composed with ignition system, oxidizer supply system, control system and data acquisition system, combustion visualization system. GOX as oxidizer and HDPE, Paraffin-LDPE Blending, Paraffin sd were used. As results, combustion phenomena and fuel droplet entrainment were observed.

  • PDF

Development of Propulsion Subsystem for KOMPSAST (다목적 실용위성의 추진시스템 개발)

  • 최진철;윤효철
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.2 no.3
    • /
    • pp.80-89
    • /
    • 1998
  • Propulsion subsystem transfers KOMPSAT into mission orbit and controls its attitude. Design factor consists of structure safety, electrical circuit design, consumable power estimation of thermal hardwares, damping device design of fuel transient pressure, and system configuration design by considering plume effect from thruster firing. System level analysis should be performed for verification of system design under launch vehicle and orbital environment. Electrical functional test of thermal control hardware, proof pressure test, cleanliness verification test, and internal/external leakage test of fuel feeding system should be carried out for performance estimation of propulsion system. Design and assembly process of propulsion subsystem was depicted and reliability of system was verified by test analysis in this paper.

  • PDF

Brief Summary of KSLV-I Upper Stage Kick Motor Development (KSLV-I 상단 킥모터 개발 개요)

  • Lee, Hanju;Lee, Jung Ho;Oh, Seung Hyub
    • Journal of the Korean Society of Propulsion Engineers
    • /
    • v.18 no.1
    • /
    • pp.91-96
    • /
    • 2014
  • KSLV-I (Korea Space Launch Vehicle-I) upper stage KM (Kick Motor) is a solid propulsion system which consists of igniter, SAD (Safety Arming Device), composite case, and submerged nozzle capable of TVC (Thrust Vector Control) actuation. Each subsystem of KM fulfilled development requirements for achieving a flight mission successfully. We confirmed the successful development of KM from the $3^{rd}$ flight test results of NARO on January 30, 2013. This article deals with the requirements of KM and the results on configuration management, mass variation, thrust axis alignment, and major test results and so on.

Design of Test Device for Quantitative Observation of Performances of Thrust-Vectoring Nozzle (추력편향 노즐의 정량적 성능특성 관찰을 위한 시험장치 설계)

  • Song, Myung-Jun;Yoon, Sang-Hun;Cho, Yong-Ho;Lee, Yeol
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • /
    • pp.404-407
    • /
    • 2011
  • The fluidic thrust vector control using co-flowing coanda effect of secondary jet at the nozzle exit is a new concept for efficient thrust vectoring of supersonic jet exhausts. Flow visualization of the flow fields in previous studies have shown some pros and cons of the technique, however, most of the observations were somewhat limited as qualitative data. The present study was designed to evaluate the quantitative performance-characteristics of the thrust-vectoring technique utilizing coanda effects of the secondary jet. Details of design of the test device and calibration/data reduction procedure are provided.

  • PDF

CFD Analysis of Marine Propeller-Hub Vortex Control Device Interaction (프로펠러와 허브 보오텍스 조절장치 상호작용 CFD 해석)

  • Park, Hyun-Jung;Kim, Ki-Sup;Suh, Sung_Bu;Park, Ill-Ryong
    • Journal of the Society of Naval Architects of Korea
    • /
    • v.53 no.4
    • /
    • pp.266-274
    • /
    • 2016
  • Many researchers have been trying to improve the propulsion efficiency of a propeller. In this study, the numerical analysis is carried out for the POW(Propeller Open Water test) performance of a propeller equipped with an energy saving device called PHVC(Propeller Hub Vortex Control). PHVC is aimed to control the propeller hub vortex behind the propeller so that the rotational kinetic energy loss can be reduced. The unsteady Reynolds Averaged Navier-Stokes(URANS) equations are assumed as the governing flow equations and are solved by using a commercial CFD(Computational Fluid Dynamics) software, where SST k-ω model is selected for turbulence closure. The computed characteristic values, thrust, torque and propulsion efficiency coefficients for the target propeller with and without PHVC and the local flows in the propeller wake region are validated by the model test results of KRISO LCT(Large Cavitation Tunnel). It is concluded from the present numerical results that CFD can be a good promising method in the assessment of the hydrodynamic performance of PHVC in the design stage.

Design of Hybrid Type Levitation and Propulsion System for High-Speed Maglev (초고속 자기부상열차를 위한 하이브리드형 부상 추진 시스템 설계)

  • Cho, Han-Wook;Han, Hyung-Suk;Lee, Jong-Min;Kim, Bong-Sup;Rho, Kyu-Suk;Kim, Dong-Sung
    • Proceedings of the KIEE Conference
    • /
    • /
    • pp.94-96
    • /
    • 2009
  • This paper deals with the design considerations of electro-magnet (EM)-permanent magnet (PM) hybrid levitation and propulsion device for magnetically levitated (maglev) vehicles. Several design considerations such as machine structure, manufacturing, and control strategy are described. In order to verify the design scheme and feasibility of control strategy, dynamic test set is implemented and tested.

  • PDF

Reduction of combustion instability using flame holder integrated injector (통합형 연료분사장치를 통한 연소불안정 저감)

  • Hwang, Yong-Seok;Lee, Jong-Guen;Park, Ik-Soo;Choi, Ho-Jin;Jin, Yu-In;Yoon, Hyun-Gull;Lim, Jin-Shik
    • Proceedings of the Korean Society of Propulsion Engineers Conference
    • /
    • /
    • pp.432-437
    • /
    • 2010
  • A new device injecting secondary fuel behind flameholder was invented and tested in order to reduce low frequency combustion instability of combustor using V-gutter flameholder. Specially designed combustion device could make large combustion instability up to 180 dB successfully, and newly invented device made a success to reduce 110~120Hz low frequency pressure pulsation up to 84%. It was found that the fuel flow rate of secondary fuel supplying behind flameholder was the only parameter which dominates reduction of instability. It is considered that stabilized flame with sufficient secondary fuel can lead to break the connection between combustion system and acoustic system due to independence of flame from fluctuation of main fuel resulted from synchronization with acoustic wave.

  • PDF

Contactless Suspension and Propulsion of Glass Panels by Electrostatic Forces

  • Jeon, Jong-Up;Park, Kyu-Yeol;Higuchi, Toshiro
    • 제어로봇시스템학회:학술대회논문집
    • /
    • /
    • pp.950-955
    • /
    • 2004
  • In the manufacture of liquid crystal display devices, there is a strong demand for contactless glass plate handling devices that can manipulate a glass plate without contaminating or damaging it. To fulfill this requirement, an electrostatic transportation device for glass plates is proposed. This device can directly drive a glass plate and simultaneously provide contactless suspension by electrostatic forces. To accomplish these two functions, a feedback control strategy and the operational principle of an electrostatic induction motor are utilized. The stator possesses electrodes which exert electrostatic forces on the glass plate and are divided into a part responsible for suspension and one for transportation. To accomplish dynamic stability and a relatively fast suspension initiation time, the structure of the electrode for suspension possesses many boundaries over which potential differences are formed. In this paper, an electrode pattern suitable for the suspension of glass plates is described, followed by the structure of the transportation device and its operational principle. Experimental results show that the glass plate has been transported with a speed of approximately 25.6 mm/s while being suspended stably at a gap length of 0.3 mm.

  • PDF