Skip to main content

The Use Of Composite Material Strips To Extend The Damage-Tolerance Life Of Integrally Stiffened Aluminum Panels

  • Conference paper
ICAF 2009, Bridging the Gap between Theory and Operational Practice

This paper describes testing and analysis performed on integrally stiffened aluminum panels reinforced by carbon-epoxy or boron-epoxy bonded strips. Testing was performed at room-temperature and at −50°C. The test results identify a large potential for increasing significantly the damage-tolerance life of these panels. The analytical results, based on finite-element models, correlate very well with the test results.

This is a preview of subscription content, log in via an institution to check access.

Access this chapter

Chapter
USD 29.95
Price excludes VAT (USA)
  • Available as PDF
  • Read on any device
  • Instant download
  • Own it forever
eBook
USD 429.00
Price excludes VAT (USA)
  • Available as PDF
  • Read on any device
  • Instant download
  • Own it forever
Softcover Book
USD 549.99
Price excludes VAT (USA)
  • Compact, lightweight edition
  • Dispatched in 3 to 5 business days
  • Free shipping worldwide - see info
Hardcover Book
USD 549.99
Price excludes VAT (USA)
  • Durable hardcover edition
  • Dispatched in 3 to 5 business days
  • Free shipping worldwide - see info

Tax calculation will be finalised at checkout

Purchases are for personal use only

Institutional subscriptions

Preview

Unable to display preview. Download preview PDF.

Unable to display preview. Download preview PDF.

References

  1. Zhang, X. et al, “Improving Fail-Safety of Aircraft Integral Structures through the Use of Bonded Crack Retarders”, Proceedings of the 24th ICAF Symposium, Naples, May 2007.

    Google Scholar 

  2. Heinimann, M., “Validation of Advanced Metallic Hybrid Concept with Improved Damage Tolerance Capabilities for Next Generation Lower Wing and Fuselage Applications”, Proceedings of the 24th ICAF Symposium, Naples, May 2007.

    Google Scholar 

  3. Baker, A. “Repair of Cracked or Defective Metallic Aircraft Components with Advanced Fibre Composites — an Overview of Australian Work”, J. of Composite Structures, vol. 2, 1984.

    Google Scholar 

  4. Baker, A., Rose, F. and Jones, R. “Advances in the Bonded Composite Repair of Metallic Aircraft Structure”, Elsevier, 2002.

    Google Scholar 

  5. Baker, A. “Bonded Composite Repair of Fatigue-Cracked Primary Aircraft Structure”, Composite Structures, 47:431–443, 1999.

    Article  Google Scholar 

Download references

Author information

Authors and Affiliations

Authors

Editor information

Editors and Affiliations

Rights and permissions

Reprints and permissions

Copyright information

© 2009 Springer-Verlag Berlin Heidelberg

About this paper

Cite this paper

Brot, A., Peleg-Wolfin, Y., Kressel, I., Yosef, Z. (2009). The Use Of Composite Material Strips To Extend The Damage-Tolerance Life Of Integrally Stiffened Aluminum Panels. In: Bos, M.J. (eds) ICAF 2009, Bridging the Gap between Theory and Operational Practice. Springer, Dordrecht. https://doi.org/10.1007/978-90-481-2746-7_14

Download citation

  • DOI: https://doi.org/10.1007/978-90-481-2746-7_14

  • Publisher Name: Springer, Dordrecht

  • Print ISBN: 978-90-481-2745-0

  • Online ISBN: 978-90-481-2746-7

  • eBook Packages: EngineeringEngineering (R0)

Publish with us

Policies and ethics