Journal of Korean Society for Quality Management (품질경영학회지)

Korean Society for Quality Management (한국품질경영학회)
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Analysis of the Causes of Cracks in Rocket Propellant in Thermal Cycling Test

로켓탄 추진기관 온도반복시험 균열 원인분석

  • Received : 2023.09.26
  • Accepted : 2023.11.20
  • Published : 2023.12.31
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Abstract

Purpose: The purpose of this study is to derive solutions and prevent similar cases from occurring by analyzing the causes of cracks found in temperature cycling tests of rocket motor. Methods: By combining the results of the current state confirmation test, non-destructive test, domestic and foreign rocket motor comparison test, cutting test, and adhesion test according to the number of times to apply mold release agent, a Cause and Effect Diagram analysis was performed to derive the cause of cracks. Results: Through this study, 26 factors that could cause cracking in rocket motors during temperature cycling tests were identified. Through various additional test results, a total of five causes were identified, including chemical and structural design of the joint between the propellant and stress relief insert, omission of procedure in the manufacturing procedures, natural aging due to temperature, and load accumulation due to temperature changes. The fundamental cause was confirmed to be insufficient consideration of the release properties of the propellant and stress relief insert. Conclusion: During the design process, it was confirmed that this could be solved by structurally or chemically designing the insert so that it does not combine with the propellant, or by applying a mold release agent during the manufacturing process.

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References

  1. Cerri, Sara, et al. 2009. Ageing behaviour of HTPB based rocket propellant formulations. Central European Journal of Energetic Materials 6(2):149-165.
  2. Gu, S. H., Jo, K. J., Kim, Y.C., Lee, J. H., and Lee, H. C. 2022. A study on the Implementation Method of the ASRP Live Firing of a Guided Missiles. Journal of the Korea Academia-Industrial Cooperation Society 23(12):118-124.
  3. Ho, Sook-Ying, and Care, Gerard. 1998. Modified fracture mechanics approach in structural analysis of solid-rocket motors. Journal of Propulsion and Power 14(4):409-415.
  4. Iqbal, Muhammad Mazhar, and Liang, Wang. 2006. Modeling the moisture effects of solid ingredients on composite propellant properties. Aerospace Science and Technology 10(8):695-699.
  5. Kim, Youngseub et al. 2010. Introduction to defense quality management. Hyungseul publishing network.
  6. Le, Anhduong Q., Sun, L. Z., and Miller, Timothy C. 2013. Detectability of delaminations in solid rocket motors with embedded stress sensors. Journal of Propulsion and Power 29(2):299-304.
  7. Lim, D., and Park, G. H. 2022. A Case Study on Configuration Change for Preventing Propulsion Wire Fracture and Structural Deformation of Launch System of UAV. Journal of Korean Society for Quality Management 50(3):533-543.
  8. Moon, K. H., Kim, J. K., and Choi, J. H. 2015. Semiquantitative Failure Mode, Effect and Criticality Analysis for Reliability Analysis of Solid Rocket Propulsion System. Trans. Korean Soc. Mech. Eng. A. 39(6):631-638.
  9. Reeling Brouwer, G., Pfiffer, A., and Bancallari, L. 2011, Development and deployment of diagnostic prognostic tactical solid rocket motor demonstrator. In: 47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. p. 5957.
  10. Tussiwand, Giuseppe. 2007. Application of Embedded Sensors Technology to a Full-Scale Nozzleless Rocket Motor. In: 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit. p. 5790.
  11. Wong, F. C. 2003, Pseudodomain fracture analysis of instrumented analog rocket motors. Journal of Spacecraft and Rockets 40(1):92-100.
  12. Yoon, K. S., and Park, S.W. 2014. A Studay on the Estimation of Shelf-life for 155mm propelling charge KM4A2 using ASRP's data. J Korean Soc Qual Manag. 42(3):291-300.