• Title/Summary/Keyword: 고체추진기관

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Design for a Subminiature Solid Rocket Motor (초소형 고체 로켓 모터의 설계)

  • Lee, Sunyoung;Lee, Hyunseob;Yang, Heeseong;Khil, Taeock;Kim, Dongwook;Bang, Jaehoon;Choi, Sungho;Lee, Yongseon
    • Journal of the Korean Society of Propulsion Engineers
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    • v.24 no.6
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    • pp.45-52
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    • 2020
  • In this paper, a subminiature solid rocket motor(SSRM) was designed to develop a miniature smart-bullet and the designed propellant grain was made of thermoplastic propellant for production convenience of inner shape. The internal ballistics analysis and ground test were performed to investigate the performance of SSRM. And a numerical simulation was carried out to obtain basic data on the design of safety distance between the nozzle outlet and a gunner, the temperature distribution of exhaust gas was analyzed by comparing a numerical simulation and the results of IR camera.

Numerical Stability of Serial Staggered Methods in Fluid-Structure Interaction Analysis of Solid Rocket Motors (고체추진기관의 유동-구조 상호작용 해석에서 Serial Staggered 기법의 수치 안정성)

  • Cho, Hyun-Joo;Lee, Jee-Ho;Lee, Chang-Soo;Kim, Chong-Am;Kim, Shin-Hoe;Lee, Jeong-Sub
    • Journal of the Computational Structural Engineering Institute of Korea
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    • v.29 no.2
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    • pp.179-185
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    • 2016
  • In this paper numerical stability of CSS and ISS schemes in axisymmetric fluid-structure-burning simulation for solid rocket motors are studied. The implemented CSS and ISS algorithms for two-dimensional axisymmetric FSI problems are used to analyze ACM and BCM solid rocket motors. Numerical results from CSS and ISS schemes are compared to investigate the efficacy of ISS scheme over CSS scheme in stabilizing the numerical solution. The ACM and BCM simulation results show that ISS scheme gives stable and converged numerical solutions with appropriately small system time step size, while CSS scheme fails to converge after generating rapidly amplified oscillatory solutions. It is concluded that ISS scheme can be useful in improving the numerical stability of FSI analysis for ACM and BCM solid rocket motor simulations, which is not successfully obtained with CSS scheme.

램제트 추진기관 기술 및 발전 동향

  • 김윤곤;김경무
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1995.05a
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    • pp.43-55
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    • 1995
  • 램제트 추진기관의 개념/특징과 현재까지 발전되어 온 여러가지 램제트 추진기관의 기술현황에 대해 기술하였으며 성능, 제작비 등 여러면에서 타 체계와 비교하였다. 또한 실제적 적용분야가 대부분 무기체계 임에 따라 현재까지의 적용현황과 함께 향후 어떻게 적용되고 발전되고자 하는지를 분석하였다. 이로부터 지난 40~50년간 무기체계 임무 및 특성에 따라 액체 램제트, 고체 램제트 및 닥티드 로켓형의 3가지로 발전되어 왔으며, 차세대 유도무기의 성능향상/생존도 향상 측면에서, 즉 고속/장 사거리 능력확보를 위해 램제트 추진기관이 세계적 관심 집중 대상이 되고 있음을 알 수 있었다.

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An introduction to present Research and Development condition about Solid Rocket Motor for Space Launch Vehicle (우주발사체용 고체 추진기관 개발현황 소개)

  • Kwon, Tae-Hoon;Shim, Myung-Sik;Song, Jong-Kwon;Lee, Won-Bok;Choi, Seong-Han;Suh, Hyuk
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2009.11a
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    • pp.623-626
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    • 2009
  • Hanwha Corporation Daejeon Plant have developed apogee Kick Motor of KSLV-I that is the first among nation space launch vehicle for five years from 2003. Now, we are joining in KSLV-II(Korea Space Launch Vehicle-II) project and developing Pyro starter which is turbo pump for the first start-up of liquid propulsion supply.

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The implementation of the firing control system considering a flight sequence control technique (비행시퀀스제어기법을 적용한 점화통제시스템 구현)

  • Lee, Seung-Jae
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.3
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    • pp.41-48
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    • 2008
  • One of main functions of the firing control system applied to a rocket propulsion test has been to provide electric current for ignition of a solid rocket motor. This paper describes the design and implementation of an enhanced firing control system for ground propulsion test that can also control and verify various types of squib events and flight sequences.

Analysis of Ultrasonic Resonance Signal in Multi-Layered Structure (다중접착구조물의 초음파 공진 신호 분석)

  • Kim, Dong-Ryun;Kim, Jae-Hoon
    • Journal of the Korean Society for Nondestructive Testing
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    • v.32 no.4
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    • pp.401-409
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    • 2012
  • Ultrasonic testing are far superior to other nondestructive tests for detecting the disbond interface which occurred in adhesive interface. However, a solid rocket motor consisting of a steel case, rubber insulation, liner, and propellant poses many difficulties for analyzing ultrasonic waves because of the superposition of reflected waves and large differences in acoustic impedance of various materials. Therefore, ultrasonic tests for detecting the disbond interface in solid rocket motor have been applied in very limited areas between the steel case and rubber insulation using an automatic C-scan system. The existing ultrasonic test cannot detect the disbond interface between the liner and propellant of a solid rocket motor because most of the ultrasonic waves are absorbed in the rubber material which has low acoustic impedance. This problem could be overcome by analyzing the resonance frequency from the frequency spectrum using the ultrasonic resonance method. In this paper, a new technique to detect the disbond interface between the liner and propellant using ultrasonic resonance characteristics is discussed in detail.

Design and Analysis of Static Firing Test for KM Subscale Motor (KM 축소형 추진기관에 대한 설계 및 시험결과분석)

  • Kwon Taehoon;Lee Wonbok;Hwang Jongsun;Cho Inhyun
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • v.y2005m4
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    • pp.16-19
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    • 2005
  • The basic research on KM(Kick Motor) for space launch vehicle was carried out. KM whick will be used as 2nd stage solid rocket motor. in Korean Satellite Launch Vehicle(I) has been developing. KM is a solid rocket motor using composite propellant based on HTPB and is composed of composite motor case and submerged nozzle. To develop KM rocket motor satisfing a given set of requirement, firstly the full-scale KM was designed, then sub-scale motor reduced about $50\%$ were manufactured and tested.

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Bursting Performance Analysis of a Pulse Separation Device for a Rocket Motor (추진기관 적용 펄스분리장치의 파열특성 분석)

  • Lee, Dong-Won;Lee, Won-Bok;Kim, In-Sik;Kim, Won-Hoon
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2011.04a
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    • pp.245-248
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    • 2011
  • A multi pulse rocket motor(MPRM) has several advantages compared to the single one. The range and the terminal velocity of the guided missile can be remarkably increased by the application of the pulse separation device(PSD) to the solid rocket motor which resulted in appropriate thrust distribution. In this study, the full scale heavy type dual pulse rocket motor with the bulkhead type PSD was designed, manufactured, and fire-tested. The bursting time and pressure of PSD were analyzed by the pressure, thrust and vibration results of static fire tests. As a result, the design requirement was verified that bursting pressure is lower than 30% of 2nd pulse operating pressure.

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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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A Study on the after-end ignition of composite solid propellant (I) (고체 추진기관의 후방점화에 대한 연구(I))

  • Suh, Hyuk;Choi, Young-Seok;Hong, Yoon-Taek
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 1997.11a
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    • pp.15-15
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    • 1997
  • 본 연구는 전방점화 방식(the head-end ignition)을 채택하고 있는 composite 고체 추진기관(구룡 1모타)을 이용하여 후방점화 방식(the after-end ignition)에 의한 점화 가능성을 검토하였으며, 점화 방식 차이에 따른 추진기관의 초기 연소거동의 차이점을 고찰하고자 한 실험 연구로서, 후방 점화장치를 설계·제작하여 지상연소시험을 수행하였다. 점화장치는 착화장치(initiation system)와 에너지 방출장치(energy release system), 구조물(Hardware)로 구성되는데, 착화장치는 기존의 K2 squib를 사용하였고, 에너지 방출장치는 FRP튜브에 MTV pellet 점화제를 사용하였으며, 점화기를 후방에 부착시키는 방법으로는 flexible finger 형태의 locking sleeve를 설계하여 노즐목에 고정하였다.

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