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A Study on the Shape Selection of Mechanical Fastening for the Repair of Fighter Wing

전투기 날개 수리를 위한 기계적 체결의 형상 선정에 관한 연구

  • Choi, Dongsu (Department of Aerospace Engineering, Air Force Academy)
  • 최동수 (공군사관학교 항공우주공학과)
  • Received : 2021.04.29
  • Accepted : 2021.08.10
  • Published : 2021.10.05

Abstract

A study on optimal shape selection of a mechanical fastening for the repair of crack defect of ROK Air Force F-5 fighter wing was conducted. The crack defect occurred in the spar of the wing, and the technical manual does not specify the repair method. However, ROK Air Force decided to develop a repair technology for this defect in consideration of various logistic conditions. Three repair shapes for the proper repair were devised and the finite element analysis was performed to examine the structural safety of these three connection members. As a result of the structural safety review, two connection members except one were structurally safe with safety margins over zero because the calculated stress values were at or below the yield strength level. Therefore, two connection members were determined to be able to use for repair under the condition that the aircraft operated within the design limit load. The results of this study would be very useful if the same defect occurs in long-term aircraft operated by the ROK Air Force.

Keywords

References

  1. National Academies Press, National Research Council, Division on Engineering and Physical Sciences, National Materials Advisory Board, Commission on Engineering and Technical Systems, Committee on Aging of U.S. Air Force Aircraft, "Aging of U.S. Air Force Aircraft : Final Report", October 30, 1997.
  2. Alten F. Grandt, JR. "Fundamentals of Structural Integrity : Damage Tolerant Design and Nondestructive Evaluation," Wiley-Interscience, November 3, 2003.
  3. Jong-Heon Kim, Young-Sik Joo, "Case Study of F-15 Airframe Battle Damage Repair Design and Assessment Procedure," Journal of The Korean Society Aeronautical and Space Sciences, Vol. 37, No. 1, pp. 105-112, 2009. https://doi.org/10.5139/JKSAS.2009.37.1.105
  4. TO 1-1A-1, "Engineering Handbook Series for Aircraft Repair," Para. 3.13., Fig. 3-13~19.
  5. TO 1F-5E-3, "Structural Repair USAF Series F-5E/F Aircraft," Para 2.24.6.6, Page 2-185, Fig. 2-27.
  6. TO KS1F-16C-3-1, "Structural Repair, ROKAF Series F-16C/D Aircraft Block 32 and 52," Para. 1.12.4, Table 1-12.
  7. MSC Nastran 2018, "Linear Static Analysis User's Guide," MSC.Software.
  8. DK Oh, "MSC Nastran Nonlinear Analysis Application," MSC Software 2014 Korea Users Conference, pp. 1~21, 2014.
  9. MIL-HDBK-516C, DoD Handbook, "Airworthiness Certification Criteria," Page 87, 12 December, 2014.
  10. e-CFR(ecfr.gov), "Limit and Ultimate Loads," Part 23, Sec.23.2230.
  11. NATO Standard, AEP-83, "Light Unmanned Aircraft Systems Airworthiness Requirements," ER.1.1, UL 2.4.
  12. Tuan Nguyen, "Stress Around Bolt Hole Comparison Between a Closed Form Calculation Method and Finite Element Analysis," MSC Software 2013 Regional User Conference, pp. 1~20, 2013.