Repair of Thin Face Sheet Sandwich Structure with Small Holes and Impact Damage
Source abstract
Abstract
This manuscript presents experimental results of compression tests of repaired sandwich structure typical of a launch vehicle Payload Adapter Fitting (PAF) that is being considered for the National Aeronautics and Space Administration’s (NASA) Space Launch System (SLS) launch vehicle. Specimens with 8-ply quasi-isotropic carbon/epoxy face sheets and aluminum honeycomb core were damaged with representations of misdrilled holes, barely visible impact damage (BVID) or visible impact damage (VID). A patch repair technique not requiring removal of any material is presented and assessed for residual in-plane compressive load-carrying capability on each of the three types of damage. Edgewise compression tests on specimens demonstrated the repairs could recover all measured undamaged compressive load-carrying capability of the misdrilled hole and BVID specimens. For the specimens with VID, an average of about 91% of the average measured undamaged compressive load carrying capability was recovered indicating that larger patches, or perhaps removal and replacement of the damaged material, may be needed for more severe damage if all the measured undamaged compression strength needs to be regained.
Source: openaire · Quality: candidate unverified · Source record ↗
Research context
OpenAlex topics: Cellular and Composite Structures · Structural Analysis of Composite Materials · Mechanical Behavior of Composites
SciVX discovery tags are terminology-based. OpenAlex topics are source-provided classifications.
References (22)
Show source-provided references
1. Zenkert, D., Haymen, B.: Damage tolerance assessment of composite sandwich panels with localized damage. Compos. Sci. Technol. 65, 2597–2611 (2005). https://doi.org/10.1016/j.compscitech.2005.05.02610.1016/j.compscitech.2005.05.026 ↗
2. Baker, A.A. and Scott, M.L.: Repair technology In: Composite materials for aircraft structures, Third Edition, AIAA Education Series by the American Institute of Aeronautics and Astronautics, Inc. pp. 369–401. AIAA, Reston, VA, USA (2016) https://doi.org/10.2514/4.10326110.2514/4.103261 ↗
3. Stone, R.H.: Repair Techniques for Graphite/Epoxy Structures for Commercial Transport Applications, NASA Contractor Report 159056 (1983) https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19830008126.pdf
4. Ahn, S.H., Springer, G.S.: Repair of composite laminates I: test results. J. Compos. Mater. 32, 1036–1074 (1998). https://doi.org/10.1177/00219983980320110210.1177/002199839803201102 ↗
5. Ghazali, E., Dano, M.L., Gakwaya, A., Amyot, C.O.: Mechanical performance of repaired sandwich panels: experimental characterization and finite-element modelling. J. Sandw. Struct. Mater. 21, 1357–1378 (2017). https://doi.org/10.1177/109963621771605910.1177/1099636217716059 ↗
6. Mahdi, S., Kinloch, A.J., Matthews, F.L., Crisfield, M.A.: The static mechanical performance of repaired composite sandwich beams: part I-experimental characterization. J. Sandw. Struct. Mater. 5, 179–202 (2003). https://doi.org/10.1177/109963620300500300410.1177/1099636203005003004 ↗
7. Kirollos, B.W.M., Trede, R., Lampen, P.: The experimental static mechanical performance of ironed repaired GFRP-honeycomb sandwich beams. J. Sandw. Struct. Mater. 14, 694–714 (2012). https://doi.org/10.1177/109963621246053810.1177/1099636212460538 ↗
8. Charalambides, M.N., Hardouin, R., Kinloach, A.J., Matthews, F.L.: Adhesively-bonded repairs to fibre-composite materials I: experimental. Composites Part A. 29, 1371–1381 (1998). https://doi.org/10.1016/S1359-835X(98)00060-810.1016/S1359-835X(98)00060-8 ↗
9. Ushakov, A., Stewart, A., Mishulin, I. and Pankov, A.: Probabilistic design of damage tolerant composite aircraft structures. DOT/FAA/AR-01/55, U.S. Department of Transportation, Federal Aviation Administration, (2002) https://pdfs.semanticscholar.org/e39c/66a26deb050f810ce71e9ef07e7ac82154bf.pdf
10. Bull, P.H., Hallstrom, A.: High-velocity and quasi-static impact of large sandwich panels. J. Sandw. Struct. Mater. 6, 97–113 (2004). https://doi.org/10.1177/109963620403046810.1177/1099636204030468 ↗
11. Park, H.: Investigation on repairable damage tolerance for structural design of aircraft composite structure. J. Compos. Mater. (2016). https://doi.org/10.1177/002199831664357910.1177/0021998316643579 ↗
12. Liu, S., Guan, Z., Guo, X., Sun, K., Kong, J.: Edgewise compressive performance of repaired composite sandwich panels-experiment and finite element analysis. J. Reinf. Plast. Compos. 32, 1331–1347 (2013). https://doi.org/10.1177/073168441348778010.1177/0731684413487780 ↗
13. Raju, M., Reddy, C., Swamy, M., Giridhar, G., Srikanth, L., Prakash, M., Rao, R.: Repair effectiveness studies on impact damaged sandwich composite constructions. J. Reinf. Plast. Compos. 25, 5–10 (2006). https://doi.org/10.1177/073168440605438210.1177/0731684406054382 ↗
14. Cox, S.: Composite structures repair development at Kennedy Space Center. Presentation, LSU College of Engineering Sidney E. Fuchs Seminar Series, November 6, 2015. https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/20150022491.pdf
15. Huo, X., Sun, G., Zhang, H., Lv, X., Li, Q.: Experimental study on low-velocity impact responses and residual properties of composite sandwiches with metallic foam core. Compos. Struct. 223, 110835 (2019). https://doi.org/10.1016/j.compstruct.2019.04.00710.1016/j.compstruct.2019.04.007 ↗
16. Moody, R.C. and Vizzini, A.J.: Test and analysis of composite sandwich panels with impact damage. DOT/FAA/AR-01/124, U.S. Department of Transportation, Federal Aviation Administration, (2002) http://www.tc.faa.gov/its/worldpac/techrpt/ar01-124.pdf
17. Sullins, R.T., Smith, G.W., Spier, E.E.: Manual for structural stability analysis of sandwich plates and shells. NASA CR-1457. National Aeronautics and Space Administration. (1969) https://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19700004831.pdf
18. Sun, G., Huo, X., Chen, D., Li, Q.: Experimental and numerical study on honeycomb sandwich panels under bending and in-panel compression. Mater. Des. 133, 154–168 (2017). https://doi.org/10.1016/j.matdes.2017.07.05710.1016/j.matdes.2017.07.057 ↗
19. Wang, J., Li, J., Hota, G., Liang, R., Chen, J.: Low-velocity impact responses and CAI properties of synthetic foam sandwiches. Compos. Struct. 220, 412–422 (2019). https://doi.org/10.1016/j.compstruct.2019.04.04510.1016/j.compstruct.2019.04.045 ↗
20. Sun, G., Chen, D., Wang, H., Hazell, P.J., Li, Q.: High-velocity impact behavior of aluminum honeycomb sandwich panels with different structural configurations. International Journal of Impact Engineering. 122, 119–136 (2018). https://doi.org/10.1016/j.ijimpeng.2018.08.00710.1016/j.ijimpeng.2018.08.007 ↗
21. Babakhani, A., Golestanipour, M., Zebarjad, S.M.: Modelling of aluminum foam core sandwich panels under impact perforation. Mater. Sci. Technol. 32, 1330–1337 (2016). https://doi.org/10.1080/02670836.2015.112229710.1080/02670836.2015.1122297 ↗
22. Tang, E., Zhang, X., Han, Y.: Experimental research on damage characteristics of CFRP/aluminum foam sandwich structure subjected to high velocity impact. Journal of Materials Research and Technology. 8, 4629–4630 (2019). https://doi.org/10.1016/j.jmrt.2019.08.00610.1016/j.jmrt.2019.08.006 ↗