• Title, Summary, Keyword: Rocket nozzle

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The Variation of Thrust Distribution of the Rocket Nozzle Exit Plane with the Various Position of Secondary Injection (2차 분사의 위치 변화에 따른 로켓노즐 출구에서의 추력 분포 변화)

  • Kim, Sung-Joon;Lee, Jin-Young;Park, Myung-Ho
    • Journal of Industrial Technology
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    • v.20 no.B
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    • pp.45-53
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    • 2000
  • A numerical study is done on the thrust vector control using gaseous secondary injection in the rocket nozzle. A commercial code, PHOENICS, is used to simulate the rocket nozzle flow. A $45^{\circ}-15^{\circ}$ conical nozzle is adopted to do numerical experiments. The flow in a rocket nozzle is assumed a steady, compressible, viscous flow. The exhaust gas of the rocket motor is used as an injectant to control the thrust vector of rocket at the constant rate of secondary injection flow. The injection location which is on the wall of rocket is chosen as a primary numerical variable. Computational results say that if the injection position is too close to nozzle throat, the reflected shock occurs. On the other hand, the more mass flow rate of injection is needed to get enough side thrust when the injection position is moved too far from the throat.

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Analysis on Thermochemical Erosion Properties for Thermal Insulation Materials of Graphite Nozzle Throat (흑연 노즐목 내열재의 열화학적 침식 특성 분석)

  • Kim, Young-in;Lee, Soo-yong
    • Journal of Advanced Navigation Technology
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    • v.22 no.2
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    • pp.90-95
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    • 2018
  • In the solid rocket motor (SRM), a thrust of rocket is generated by a nozzle so it is very important device. The nozzle of SRM is a condition of high temperature and high pressure so occurs the erosion by combustion gas. The liquid rocket propulsion systems (LRPSs) cools the nozzle by the fuel and oxidizer but SRM does not cool the nozzle. This paper deal with the development of the oxy-acetylene torch tester and investigate the thermochemical erosion properties for the thermal insulation materials of the graphite rocket nozzle throat through the experiment. The results of experiments are compared with the results of Theoretical model and identify the key factors affecting of erosion. The results is in good agreement with the experimental data.

Numerical Simulation of Two-Phase Flow field and Performance Prediction for Solid Rocket Motor Nozzle

  • Wahab, Shafqat;Kan, Xie;Yu, Liu
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.275-282
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    • 2008
  • This paper presents numerical investigation of multi-phase flow in solid rocket motor nozzle and effect of multi-phases on the performance prediction of the Solid Rocket Motor. Aluminized propellants are frequently used in solid rocket motors to increase specific impulse. An Eulerian-Lagrangian description has been used to analyze the motion of the micrometer sized and discrete phase that consist of the larger particulates present in the Solid Rocket Motor. Uniform particles diameters and Rosin-Rammler diameter distribution method has been used for the simulation of different burning of aluminum droplets generating aluminum oxide smokes. Roe-FDS scheme has been used to simulate the effects of the multi-phase flow. The results obtained show the sensitivity of this distribution to the nozzle flow dynamics, primarily at the nozzle inlet and exit. The analysis also provides effect of two phases on performance prediction of Solid Rocket Motor.

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Enhancement of Performance for Solid Composite Propellant Motor using Teflon Nozzle (Teflon 노즐을 이용한 복합추진제 모터의 추력 향상)

  • Hong Gi-Cheol;Lee Hoon-Hee;Seo Charm;Goo Yong-Je;Sim Ju-Hyun;Kim Sang-Woo;Lim Sung-Bin;Bang Jae-Won
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.495-499
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    • 2005
  • The INHA Rocket Research Institute changed the Ceramic nozzle material of their developed Solid Composite Propellant Motor with Teflon nozzle material. Static firings of the new Solid Rocket Motors was conducted on Thurst Tester to validate the increase in performance. The new enhanced Solid Roket Motor increased the total impulse by 18.3 percent while improving its reliability. The new process of manufacture reduced the time to produce a nozzle.

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Numerical Study of Chemical Performance of 30 tonf -class LRE Nozzle of KARI

  • Kang, Ki-Ha;Lee, Dae-Sung;Cho, Deok-Rae;Choi, H.S.;Choi, J.Y.
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • pp.448-451
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    • 2008
  • Three methods of nozzle flow analysis, frozen-equilibrium, shifting-equilibrium and non-equilibrium approaches, were used to rocket nozzle flow, those were coupled with the methods of computational fluid dynamics code. For a design of high temperature rocket nozzle, chemical equilibrium analysis which shares the same numerical characteristics with frozen flow analysis can be an efficient design tool for predicting maximum thermodynamic performance of the nozzle. Frozen fluid analysis presents the minimum performance of the nozzle because of no consideration for the energy recovery. On the other hand, the case of chemical-equilibrium analysis is able to forecast the maximum performance of the nozzle due to consideration for the energy recovery that is produced for the fast reaction velocity compared with velocity of moving fluid. In this study, using the chemical equilibrium flow analysis code that is combined the modified frozen-equilibrium and the chemical-equilibrium. In order to understand the thermochemical characteristic components and the accompanying energy recovery, shifting-equilibrium flow analysis was carried out for the 30 $ton_f$-class KARI liquid rocket engine nozzle together with frozen flow. The performance evaluation based on the 30 $ton_f$-class KARI LRE nozzle flow analyses will provide an understanding of the thermochemical process in the nozzle and performances of nozzle.

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A Study of Aero-thermodynamic Ablation Characteristics for Rocket Nozzle (로켓노즐내부의 공기 열역학적 삭마특성에 관한 연구)

  • Seo, J.I.;Jeong, J.H.;Kim, Y.I.;Kim, J.H.;Song, D.J.;Bai, C.H.
    • Proceedings of the KSME Conference
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    • pp.282-287
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    • 2001
  • The CSCM Upwind method and Material Transport Analysis (MTA) have been used to predict the thermal response and ablation rate for non-charring material to be used as thermal protection material (TPM) in KSR-III test rocket nozzle. The thermal boundary conditions such as cold wall heat-transfer rate and recovery enthalpy for MTA code are obtained from the upwind Navier-Stokes solution procedure. The heat transfer rate and temperature variations at rocket nozzle wall were studied with shape change of the nozzle surface as time goes by. The surface recession was severely occurred at nozzle throat and this affected nozzle performance such as thrust coefficient substantially.

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Thermochemcial Characteristics of Rocket Nozzle Flow and Methods of Analysis (로켓 노즐 유동의 열/화학적 특징 및 해석 기법)

  • Choi Jeong-Yeol
    • 한국전산유체공학회:학술대회논문집
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    • pp.144-148
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    • 2001
  • Characteristics of high temperature rocket nozzle flow is discussed along with the aspects of computational analysis. Three methods of nozzle flow analysis, frozen-equilibrium, shifting-equilibrium and non-equilibrium approaches, were discussed those were coupled with the methods of computational fluid dynamics. A chemical equilibrium code developed for the analysis of general hydrocarbon fuel was coupled with three approaches of nozzle flow analysis, and a test was made for a bell nozzle at typical operation condition. As a results, the characteristics of the approaches were discussed in aspects of rocket performance, thermal analysis and computational efficiency.

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Thermochemical Performance Analysis of KSR-III Rocket Nozzle (KSR-III 로켓 노즐의 열화학적 성능해석)

  • Choi, J.Y.;Choi, H.S.;Kim, Y.M.
    • 한국연소학회:학술대회논문집
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    • pp.90-98
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    • 2001
  • Characteristics of high temperature rocket nozzle flow is discussed along with the aspects of computational analysis. Three methods of nozzle flow analysis, frozen-equilibrium, shifting-equilibrium and non-equilibrium approaches, were discussed, those were coupled with the methods of computational fluid dynamics code. A chemical equilibrium code developed for the analysis of general hydrocarbon fuel was coupled with three approaches of nozzle flow analysis. The approaches were used for the performance prediction of KSR-III Rocket, and compared with the theoretical results from NASA CEA (Chemical Equilibrium with Applications) code.

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A Numerical Study of Unsteady Plows in A Rocket Main Nozzle (로켓 주노즐내 비정상 유동의 수치해석적 연구)

  • Kim S. D.;Kim Y. I.;Song D. J.
    • 한국전산유체공학회:학술대회논문집
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    • pp.54-59
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    • 2000
  • A numerical study of axisymmetric rocket main nozzle flow has been accomplished. The CSCM upwind flux difference splitting method with an iterative time marching scheme having second order accuracy in time and space has been used to simulate unsteady flow characteristics in an axisymmetric rocket main nozzle. Though the pressure vary at nozzle inlet with the lapse of time, Mach No. and the density were not changed significontly compared with the temperature. Specific heat ratio $\gamma$=1.134 predicted higher temperature at nozzle throat and exit and nondimensional thrust coefficients at exit than specific heat ratio $\gamma$=1.4 did.

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NUMERICAL INVESTIGATION OF EFFECTS OF FLUTED EDGE SHAPE ON THRUST IN A ROCKET NOZZLE (로켓 노즐의 끝면 형상이 추력에 미치는 영향성 연구)

  • Kang, Y.J.;Yang, Y.R.;Kim, S.H.;Hwang, U.C.;Youm, Y.I.;Myong, R.S.;Cho, T.H.
    • 한국전산유체공학회:학술대회논문집
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    • pp.8-12
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    • 2009
  • In this study the performance of the nozzle of a rocket system is evaluated using a CFD code. The main emphasis of the investigation is placed on the effects of the number (9 and 12) and the depth of fluted edge in the rocket nozzle. It is observed that as the depth increases the rolling moment of the nozzle increases while the thrust of the nozzle decreases.

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