Journal of the Korean Society of Propulsion Engineers (한국추진공학회지)

The Korean Society of Propulsion Engineers (한국추진공학회)
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Study on the Formulation of an Energetic Thermoplastic Propellant and its Properties(II)

고에너지 열가소성 추진제 제조 및 특성연구(II)

  • Kim, Han-cheol (Propulsion Center, Daejeon Plant, Hanwha Corporation) ;
  • Park, Eui-Yong (Propulsion Center, Daejeon Plant, Hanwha Corporation) ;
  • Jeong, Jea-Yun (Propulsion Center, Daejeon Plant, Hanwha Corporation) ;
  • Kim, Yoon-Gon (Propulsion Center, Daejeon Plant, Hanwha Corporation) ;
  • Choi, Sung-han (Propulsion Center, Daejeon Plant, Hanwha Corporation) ;
  • Kang, Tae-won (Energetic Materials & Pyrotechnics, hanwha Corporation R&D Center) ;
  • Oh, Kyeong-won (Maneuver&Firepower Technical Team, Defense Industry Technology Center)
  • Received : 2019.12.03
  • Accepted : 2020.04.16
  • Published : 2020.06.30
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Abstract

In this study, measurement and analysis results from Differential scanning calorimetry(DSC) and Thermogravimetric analysis(TGA) on the newly developed high-energy thermoplastic elastomer(ETPE) propellant are described, followed by the previous study done under the same title as this paper [1]. The characteristics of high-energy thermoplastic propellant were also verified by conducting thermal analysis, and the LSGT, Shotgun & RQ Bomb test, was carried out as well. High energetic thermoplastic binders containing 45% of GAP(Glycidyl Azide Polymer), energetic plasticizer(DEGDN) and Oxidizer Aonium Perchlorate), RDX(reseach development explosive, cyclotrimethylenetrinitramine) were used to formulate the propellant.

본 연구에서는 당 논문과 동일한 제목 하에 이루어진 연구결과에 이어서 최신 개발 고에너지 열가소성(ETPE)추진제의 시차 주사 열량(DSC) 및 열중량 분석(TGA)법으로 열분석을 진행하여 고에너지 열가소성 추진제의 특징을 확인하였으며, 추진제 둔감성을 확인하기 위해 추진제 둔감 정도 확인 시험인 LSGT, 파쇄성 시험을 진행하였다. 추진제 원료로는 GAP(Glycidyl Azide Polymer)이 45% 함유된 고에너지 열가소성(ETPE) 바인더와 고에너지 가소제(DEGDN), 산화제로는 AP(Ammonium Perchlorate)와 RDX(research development explosive, cyclotrimethylenetrinitramine)를 사용하였다. 위와 같은 분석을 통해, 개발된 ETPE 추진제가 일반적인 RDX/AP 추진제와 유사한 열적 거동을 갖는 것을 확인 하였다.

Keywords

Acknowledgement

본 연구를 위해 지원해주신 방위산업기술지원센터 기동화력기술팀과 국방과학연구소 4본부 1부 및 3부 분들께 감사의 말씀을 드립니다(계약번호: UC160010D).

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