한국추진공학회지 (Journal of the Korean Society of Propulsion Engineers)

  • 제23권4호
  • /
  • Pages.92-97
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  • 2019
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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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HTPB계 추진제/라이너/내열재의 접착력 향상에 관한 연구

A Study on Improvement of Adhesion HTPB Propellant/Liner/Insulation

  • Park, Sungjun (Propulsion Center, Daejeon Plant, Hanwha Corporation) ;
  • Song, Jongkwon (Propulsion Center, Daejeon Plant, Hanwha Corporation) ;
  • Park, Euiyong (Propulsion Center, Daejeon Plant, Hanwha Corporation) ;
  • Rho, Taeho (Propulsion Center, Daejeon Plant, Hanwha Corporation) ;
  • Choi, Sunghan (Propulsion Center, Daejeon Plant, Hanwha Corporation)
  • 투고 : 2018.12.29
  • 심사 : 2019.03.29
  • 발행 : 2019.08.01
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초록

추진제, 라이너 그리고 내열재간의 접착력을 향상시키기 위한 연구를 수행하였다. 내열재에 아무런 처리하지 않은(Bare) 상태보다는 피막처리제를 적용한 것이 접착력 향상에 유리하였다. 라이너 도포 두께가 증가할수록 내열재와 추진제간의 접착력이 향상되는 것을 확인하였으며, 라이너 경화는 24시간 경화 시간이 필요하며, 그 이상의 과경화는 접착력에 불리한 영향을 끼친다. 또한 결합제를 적용할 때가 적용하지 않을 때보다 접착력에 유리하다는 것을 알 수 있었으며, 결합제 함량이 증가할수 록 접착력도 상승하였다. 결합제 종류에 따른 접착력 변화는 HX-868이 HX-752보다 접착력이 소폭 향상되었다.

A study was conducted to improve the adhesion of propellant, liner,and insulation. Insulation was shown to be more advantageous in improving the adhesion when a barrier coat was applied compared to a bare insulation layer. It was confirmed that the adhesion strength between the insulation and the propellant improves as the thickness of the liner coating increases. The liner was cured for 24 h. If the liner is cured for a long time, it will adversely affect adhesion. Adhesion is also improved when a bonding agent is applied. As the bonding agent content increases, the adhesion improves. There is a change in the adhesive strength depending on the type of bonding agent used. HX-868 shows slightly more improved adhesion than HX-752.

키워드

참고문헌

  1. Hong, M.P., Seo, T.S. and Yim, Y.J., "A study on the adhesion of HTPB liner and PCP propellant", Journal of the Korean Society of Propulsion Engineers, Vol. 5, No. 3, pp. 60-70, 2001.
  2. Twichell, S.E. and Keller, R.B., Solid Rocket Motor Internal Insulation", NASA-SP-8093, 1976.
  3. Ashraf F.A. and Soung V.H., "Thermal insulation by heat resistant polymers for solid rocket motor insulation", Journal of composite material, Vol. 46, No. 13, pp. 1549-1559, 2011. https://doi.org/10.1177/0021998311418850
  4. Davenas, A., Solid rocket Propulsion Technology, 1st edition, Pergamon Press, 1993.
  5. Song, H.J., Hong, S.P. and Park, J.W. "The study on service life evaluation test of composite solid propellant", Journal of the Korean Society of Propulsion Engineers fall conference, Korea, pp. 572-575, 2012. 11.
  6. Oberth, A.E., "Principles of Solid Propellant development", CPIA Publication, 469, 1987.
  7. Jeong, B.H, Seo, T.S. and Hong, M.P., "Improvement of Bonding Process and Bond Strength of HTPB Propellant/Liner using a Polymeric Curative", Journal of the Korean Society of Propulsion Engineers, Vol. 10, No. 2, pp. 110-114, 2006.
  8. Spreafico, M., DeLuca, L.T. Condo, A.C., Consaga, J. and Kosowski, B.M., "Influence of bonding agent on steady burning rate and mechanical properties of solid rocket propellants", AIDAA Congress, 2009.