• Title/Summary/Keyword: 고체 로켓

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고체 렘제트탄의 공기역학적 특성에 관한 실험적 연구

  • 박순종;신필권;김경련;박종호;김윤곤
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2002.04a
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    • pp.60-60
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    • 2002
  • 비행탄의 종말속도증대를 위하여 고체램제트를 이용하는 개념은 현재 세계적으로 여러나라에서 연구 중에 있다. Solid Fuel Ramjet Propulsion(고체연료 렘제트 추진)은 로켓추진에 비하여 월등히 높은 비추력을 가지며 구조적으로 매우 간단하여 탄의 사거리 및 평균속도를 증대시키는 좋은 수단으로 사용되고 있다. 그러나 간단한 구조에도 불구하고 고체렘제트의 작동은 매우 다양한 물리적 현상이 연관되므로 필요한 성능을 얻기 위해서는 이들의 상호 작용을 고려하여 설계의 최적화 및 성능 예측이 필요하다.

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Oxamide를 적용한 무연 라이너 연구

  • 박영규;류문삼
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2000.04a
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    • pp.25-25
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    • 2000
  • 가스발생기와 같이 로켓모터에서 추력이 아닌 기체압 형태의 에너지를 일정한 시간동안 얻고자 하는 경우, 로켓모터의 크기 및 추진제 충전율을 고려하여 그레인 형태를 단면 연소형으로 선택할 수 있다. 단면 연소형 그레인을 가진 로켓모터는 그레인의 연소시, 일찍 연소된 부분의 라이너가 추진제 연소 화염에 노출되면서 표면부터 서서히 분해가 진행되며, 분해물질의 일부는 추진제에 포함된 산화제 성분에 의해 산화되어 기체화 될 수 있다. 산화제 성분이 충분치 않은 경우에는 고체 입자 형태로 추진제 연소 기체와 함께 배출되며, 이는 일차연기(primary smoke)의 일종으로 볼 수 있다. 가스 발생기에서 얻고자 하는 기체는 고체 입자가 포함되지 않은 깨끗한 기체형태인 경우가 대부분이며, 따라서, 무연 라이너 및 내열재의 연구가 필요하다.

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Now and the future of Hybrid rocket propulsion system (하이브리드 로켓 추진기관의 현황과 개발방안)

  • Lee Junho;Choi Sunghan;Whang Jongsun;Choi Younggi
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.79-82
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    • 2005
  • The hybrid rocket has been known for over 50 years. It is safe and cheap but wasn't widely used for the deficit of low regression rate. However, the hybrid rocket propulsion system will replace a lot of fields of missiles, rockets and propulsion systems of launch vehicles with new development of paraffin based solid fuel composition

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Bullet Impact Tests for Solid Rocket Motor (고체 로켓 모타의 탄환 충격 시험)

  • 윤현걸;최창선
    • Journal of the Korean Society of Propulsion Engineers
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    • v.6 no.1
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    • pp.30-38
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    • 2002
  • Bullet impact tests for two solid rocket motors were performed and its results were compared and analyzed. One was loaded with the existing propellant with decreased weight content of burning rate catalyst and added high density additives to improve mechanical properties and the other was loaded with the existing propellant with decreased weight content of burning rate catalyst to improve its insensitivity as well as to maintain the ballistic performance. The composite cases were used for both motors.

Large Eddy Simulation on Inhibitor Effect of a Large Solid Rocket Motor (대형 고체로켓의 그레인간 인히비터에 의한 유동 교란 특성 LES)

  • Hong, Ji-Seok;Heo, Jun-Young;Moon, Hee-Jang;Sung, Hong-Gye;Lee, Do-Hyung;Kim, Yoon-Gon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.11a
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    • pp.31-37
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    • 2011
  • Detail flow structure in a large solid rocket motor with two inhibitors has been investigated using 3D Large Eddy Simulation and Proper Orthogonal Decomposition(POD) analysis. Vortex shedding frequencies periodically occurred by inhibitors are coupled with flow acoustics induced by the impinging of vorticity on nozzle head. As a result of 3D analysis, it was observed that the nozzle exit flow causes roll-torques from the vortex being decomposed in unbalanced shape for the impinging of vorticity on the nozzle head.

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Study of a Pressure Tube for Measuring pressure of a Solid Rocket Motor at High Altitude Environment (고고도환경을 고려한 SRM 압력계측배관에 관한 연구)

  • Lee, Dong-Won;Lee, Won-Bok;Koh, Hyeon-Seok;Kil, Gyoung-Sub
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2008.05a
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    • pp.53-56
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    • 2008
  • When someone measuring for pressure of a Solid Rocket Motor(SRM) at Static Firing Test, generally, used with pressure tube to be filled in Oil. But, if you used pressure tube with oil, you were worried about possibility of spilled oil when you measured pressure in SRM at high altitude environment. Because it usually connected at ignitor. In this paper, We described how to make a pressure tube without oil and matters to be attended to design it.

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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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Visualization of Internal Flows in the Wall-injected Test Model of a SRM (고체로켓모터 표면분사 시험모델의 유동 가시화)

  • Kim, Do-Hun;Lee, In-Chul;Koo, Ja-Ye;Cho, Yong-Ho;Kang, Moon-Jung;Kim, Yoon-Gon
    • Journal of the Korean Society of Propulsion Engineers
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    • v.15 no.3
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    • pp.31-39
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    • 2011
  • The flowfield in a solid rocket motor was simulated at the wall-injection test model, which has a fin-slot grain and submerged nozzle, and visualized by a smoke-wire. The high speed CCD camera captured the visualized images around the nozzle inlet through the grain center port. The vortical tube structure and circumferential flow patterns at the nozzle throat were visualized. The radial momentum transfer caused by the shear-interactions of slot-outlet flow, fin-base flow and grain port flow from upstream worked as the source of these phenomena.

Characteristics of Fuel-rich Solid Propellants with Boron Powder and the Combustion Products (Boron Powder 적용 연료과농 추진제 및 연소 후 생성물의 특성 연구)

  • Kim, Miri;Kim, Jeongeun;Khil, Taeock
    • Journal of the Korean Society of Propulsion Engineers
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    • v.26 no.1
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    • pp.12-19
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    • 2022
  • The propellants used in the gas generator of the ducted rocket are fuel-rich propellants, which contain an excessive amount of metal fuel and a small amount of oxidizing agent compared to general solid rocket propellants. In this paper, boron powder and MgAl(Magnesium-Aluminium alloy) were applied to produce fuel-rich propellants. The optimum formulation was determined by characterizing these metal fuel-rich propellants. Analysis of combustion products in the gas generators confirmed that the fuel-rich propellants containing fine boron powder itself instead of boron-bead could be useful in gas generators.