Repair of multisite damage in civil transport aircraft: an example of the damage-tolerant design of composite repairs

Lorrie Molent, Rhys Jones

Research output: Chapter in Book/Report/Conference proceedingChapter (Book)Researchpeer-review

3 Citations (Scopus)

Abstract

This chapter illustrates how the damage-tolerant design approach discussed in Chapter 8 can be used to design repairs to multisite damage in civil transport fuselage lap joints. To this end the chapter discusses the results of the associated laboratory test programme and the subsequence flight demonstrator programmes. This chapter is complimented by the work presented in Chapter 11 which further illustrates how this damage-tolerant design approach was used to design composite repairs to DC-10 and DC11 aircraft.The work presented in this chapter is complimented by that presented in Chapter 17 which illustrates how supersonic particle deposition (SPD), which is an additive metal technology that is also referred to as cold spray, when used in conjunction with the standard practice of using a sealant to stop the environment entering the joint via the gap between the mating fuselage skins, can seal the fasteners and thereby alleviate corrosion damage and consequently extend the time to crack initiation at the joint so that the limit of validity (LOV) is not degraded by corrosion.

Original languageEnglish
Title of host publicationAircraft Sustainment and Repair
EditorsRhys Jones, Alan Baker, Neil Matthews, Victor Champagne
Place of PublicationOxford UK
PublisherElsevier
Chapter9
Pages463-510
Number of pages48
Edition1st
ISBN (Electronic)9780081005446
ISBN (Print)9780081005408
DOIs
Publication statusPublished - 2018

Keywords

  • Civil transport aircraft
  • Composite repairs
  • Damage-tolerant design
  • Fatigue crack growth
  • Multisite damage

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