한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제18권4호
  • /
  • Pages.74-80
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  • 2014
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  • 1226-6027(pISSN)
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  • 2288-4548(eISSN)
한국추진공학회 (The Korean Society of Propulsion Engineers)
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명중률 향상을 위한 이중추력형 비행모터 개발에 대한 연구

A Study on Development of the Dual-thrust Flight Motor for Enhancing the Hit Probability

  • Kim, Hanjun (R&D Team, Daejeon Plant, Hanwha Corporation) ;
  • Kim, Eunmi (R&D Team, Yeosu Plant, Hanwha Corporation) ;
  • Kim, Namsik (Tactical Missle Systems Team, Defense R&D Center, Hanwha Corporation) ;
  • Lee, Wonbok (R&D Team, Daejeon Plant, Hanwha Corporation) ;
  • Yang, Youngjun (R&D Team, Yeosu Plant, Hanwha Corporation)
  • 투고 : 2013.12.11
  • 심사 : 2014.07.10
  • 발행 : 2014.08.01
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초록

본 논문은 무유도 로켓탄의 명중률을 향상시키기 위해 개발한 이중추력형 비행모터에 관하여 기술하였다. 고연소속도 특성을 지닌 더블베이스 추진제의 형상 조절을 통해 이중추력형 비행모터를 설계하였으며, 실제 지상연소시험을 통해 이중추력 성능을 확인하였다. 연소시험 결과 서스테이닝 단계와 부스팅 단계의 추력비는 약 1:7.6으로 정상적인 이중추력 특성을 보였으며, 압력강하에 의한 추진제 소화현상은 나타나지 않았다.

This paper describes the development of the dual-thrust flight motor for enhancing the hit probability of unguided rockets. We designed dual-thrust flight motor by shape modification of the double base propellant with high burning rate, and confirmed the dual-thrust performance by static firing tests. The test results showed the thrust ratio of about 1:7.6 between sustaining phase and boosting phase, and had a quietly normal dual-thrust characteristics. And the results showed that there was not the fire extinction phenomenon of propellant due to the pressure drop.

키워드

참고문헌

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  8. Belov, G.V., "Thermodynamic Analysis of Combustion Products at High Pressure and Temperature," Propellants, Explosives, Pyrotechnics, Vol. 23, No. 2, pp. 86-89, 1998. https://doi.org/10.1002/(SICI)1521-4087(199804)23:2<86::AID-PREP86>3.0.CO;2-2
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피인용 문헌

  1. Reliability Assessment Approach Using Failure Mode Analysis in Machining Center vol.321-323, pp.1662-9795, 2006, https://doi.org/10.4028/www.scientific.net/KEM.321-323.1535