• Title/Summary/Keyword: 고체 로켓 노즐

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Numerical Analysis for Thermal Response of Silica Phenolic in Solid Rocket Motor (고체 로켓 추진기관에서 실리카/페놀릭 열반응 해석 연구)

  • Seo, Sangkyu;Hahm, Heecheol;Kang, Yoongoo
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2017.05a
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    • pp.521-528
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    • 2017
  • In this paper, the numerical analysis for heat conduction of silica/phenolic composite material, which is used for solid rocket nozzle liner or insulator, was conducted. 1-D Finite Difference Method for the analysis of silica/phenolic during the firing of solid rocket motor was used to calculate the heat conduction considering the surface ablation and the thermal decomposition. The boundary condition at the nozzle wall took into account the convective heat transfer, which was obtained by integration equation. The numerical results of the surface ablation and char depth were compared with the results of test motor that is TPEM-10. It was found that the result of calculation is favorably agreed with the thermal response of test motor.

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Numerical Analysis for Thermal Response of Silica Phenolic in Solid Rocket Motor (고체 로켓 추진기관에서 실리카/페놀릭 열반응 해석 연구)

  • Seo, Sangkyu;Hahm, Heecheol;Kang, Yoongoo
    • Journal of the Korean Society of Propulsion Engineers
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    • v.22 no.4
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    • pp.76-84
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    • 2018
  • In this paper, the numerical analysis for heat conduction of silica/phenolic composite material, used for solid rocket nozzle liners or insulators, is conducted. A 1-dimensional finite difference method for the analysis of silica/phenolic during the firing of a solid rocket motor is used to calculate heat conduction, considering surface ablation and thermal decomposition. The boundary condition at the nozzle wall, considering the convective heat transfer, is obtained via integration equations. The numerical results of the surface ablation and char depth are compared with the results of a TPEM-10 test motor, finding that the result of calculation agrees with the thermal response of the test motor.

The Experimental Study of Thermal Stress at Supersonic Nozzle (초음속 노즐의 열구조 안전성에 관한 실험적 연구)

  • Kim, Seong-Jin;Han, Hyeok-Seop;Lim, Jae-Hyock;Park, Eui-Yong;Baek, Ki-Bong
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.497-500
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    • 2011
  • The experimental study of thermal stress in the solid rocket engine nozzle with two different materials, SCM-440 and STS-630, was evaluated. SCM-440 has lager temperature increasing rate and higher temperature at the nozzle expansion region than STS-630. Thermal barrier efficiency and endurance of Zirconia coating were evaluated after making two more nozzles coated by Zirconica. Both coated materials showed about 70 percent higher thermal barrier efficiency than uncoated nozzles. Therefore, Zirconia coating using plasma spray method was useful in thermal safety at supersonic nozzle.

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Characteristics and Development Trends of Heat-Resistant Composites for Flight Propulsion System (비행체 추진기관용 내열 복합재의 특성 및 개발 동향)

  • Hwang, Ki-Young;Park, Jong Kyoo
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.47 no.9
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    • pp.629-641
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    • 2019
  • In order to limit the temperature rise of the structure to a certain level or less while maintaining the aerodynamic shape of solid rocket nozzle by effectively blocking a large amount of heat introduced by the combustion gas of high temperature and high pressure, the heat-resistant materials such as C/C composite having excellent ablation resistance are applied to a position in contact with the combustion gas, and the heat-insulating materials having a low thermal diffusivity are applied to the backside thereof. SiC/SiC composite, which has excellent oxidation resistance, is applied to gas turbine engines and contributes to increase engine performance due to light weight and heat-resistant improvement. Scramjet, flying at hypersonic speed, has been studying the development of C/SiC structures using the endothermic fuel as a coolant because the intake air temperature is very high. In this paper, characteristics, application examples, and development trends of various heat-resistant composites used in solid rocket nozzles, gas turbine engines, and ramjet/scramjet propulsions were discussed.

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.

Unsteady Modeling of a Solid Rocket Motor with a Composite Propellant (혼합형 고체추진제를 이용한 로켓의 비정상 성능해석)

  • Lee, Sung-Nam;Baek, Seung-Wook;Kim, Kyung-Moo;Kim, Yoon-Gon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.05a
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    • pp.175-178
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    • 2008
  • A Numerical Simulation which uses preconditioning algorithm to examine unsteady combustion processes for the AP/HTPB propellant with a converging-diverging nozzle has been compared with experimental data for solid rocket motor. To analysis reacting flow of solid rocket motor, unsteady pressure, temperature contour was simulated by grid moving of propellant.

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A Study on the Advanced Technology of Solid Rocket Propulsion (고체 추진기관 선진국 기술 동향에 관한 연구)

  • Kim, Hyung-Won;Park, Chong-Seung
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.11a
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    • pp.221-224
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    • 2010
  • Recently, due to the enormous cost for sending a satellite into an orbit, small and more reliable satellites have been more demanded. An introduction of new binders(HTPB, GAP) and new oxidizers made great improvements of the large thrust modulation. In order to make cost reduction, one prefers to the low melting temperature thermoplastic propellant reforming the manufacturing process dramatically. Solid propellant rockets have been had a problem of the injection accuracy into orbit, but PBS(Post Boost Stage) using a liquid mono-propellant improves the injection accuracy. This paper also gives the direction of the advanced nozzle materials and the motor case.

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Large Eddy Simulation for the investigation of Roll Development Process in a Solid Rocket Motor (고체로켓 내부에서의 Roll 발생 현상 3D LES)

  • Kim, Jong-Chan;Hong, Ji-Seok;Yeom, Hyo-Won;Moon, Hee-Jang;Kim, Jin-Kon;Sung, Hong-Gye
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.253-257
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    • 2011
  • Vortex generation mechanism by inhibitor in a solid rocket motor have been investigated by 3D Large Eddy Simulation turbulent model. Most of the result of the present study are in good agreement with experimental data and previous numerical calculation. Vortex generation and breakdown behind inhibitor are periodically observed between inhibitor and nozzle head by flow-acoustic coupling mechanism. Vortex generation frequency is the same as the second-mode frequency in the motor. The roll shape vortex generation behind inhibitor induces non-uniform flow field at the nozzle entrance and its throat.

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Analysis on the two-dimensional ablation phenomenon at nozzle throat with graphite (그라파이트 노즐목의 2차원 삭마현상 해석)

  • 윤덕진;강윤구
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1998.04a
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    • pp.35-35
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    • 1998
  • 고체 로켓 추진기관의 노즐을 개발하기 위해서는 주어진 체계 제한 조건내에서 기본적인 가스의 동력학, 내탄도에 의한 형상 설계, 재료 개발 및 적용 기술, 열전달 계산에 의한 열설계 및 해석 등이 종합적으로 적용되며 수많은 반복과정을 거쳐야 한다. 특히 최근에는 알루미늄 함유량을 증가시켜 연소가스의 온도가 300$0^{\circ}C$ 이상이 되는 고성능 추진제가 일반적으로 적용되고 있으므로 고온에 의한 열적문제가 심각하게 대두되고 있으며 이에 견디는 신뢰도가 높은 노즐 설계개발이 요구되고 있다. 노즐목을 노즐내에서 열부하가 가장 심한 곳으로 노즐목 확대에 의한 추력 손실을 최소화하기 위해 내삭마성이 강한 재료를 선정하여야 하며, 그래파이트는 이러한 조건을 만족시키는 소재의 하나로 많이 적용되고 있다.

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Perspectives on the Hot Components for Rocket Nozzle and Thrusters (고성능 로켓노즐 및 추력기용 내열부품 현황)

  • Lim, Seong-Taek;Kim, Jung-Keun;Kang, Yun-Koo;Kim, Hyeong-Won;Kim, Yeon-Chul
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.11a
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    • pp.67-71
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    • 2008
  • Rocket nozzle components and thrusters for next-generation solid rocket with variable thrust, and small uncooled liquid rocket thrusters are required to withstand ultra-high temperature upto $2500^{\circ}C$. In this survey, the operationg environments are investigated with the suggeations of proper materials and their fabrication methods. Especially, It is suggested that Rhenium and other competative matrials are exploited to $2500^{\circ}C$ hot components, and thus needed to be developed.

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