Abstract

As fiber reinforced plastic composites gain an increasingly larger share in aerospace structures, the problem of joining them with metal elements becomes significant. The current paper is the second part of the literature review, which gathers and evaluates knowledge about methods suitable for the mechanical joining of composite and metal elements. This paper reviews the joining methods other than bolted joining, which are discussed in the first part of the review, namely self-piercing riveting, friction riveting, clinching, non-adhesive form-locked joints, pin joints, and loop joints. Some of those methods are full-fledged and employed in commercial applications, whereas others are merely ideas tested at the level of specimens. The current review describes the ideas and the qualities of the joining methods as well as the experimental work carried out so far. The summary section of this paper contains a comparison of those methods with the reference to their qualities, which is important from the point of view of a composite structure designer: possibility of the joint disassembly, damages induced in composite, complication level, weight penalty, range of possible materials to be joined, and the joint strength.

Highlights

  • Fibre reinforced composite materials continue to gain progressively larger share in the structures of modern aircraft

  • The subsequent sections of the current work describe two methods of riveting used in composite materials: self-piercing riveting and friction riveting, method of joining by mechanical clinching, non-adhesive form-locked joints designed in order to introduce a concentrated force into a composite structure, pin joints which join the composite to metal by arrays of pins protruding from metal elements inserted into composite during curing process and loop joints which consist in entangling reinforcing fibres into loops protruding from metal elements

  • The results have shown that the influence of the pin inclination angle on the increase of the maximum load and fracture toughness in double cantilever beam (DCB)

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Summary

Introduction

Fibre reinforced composite materials continue to gain progressively larger share in the structures of modern aircraft. The subsequent sections of the current work describe two methods of riveting used in composite materials: self-piercing riveting and friction riveting, method of joining by mechanical clinching, non-adhesive form-locked joints designed in order to introduce a concentrated force into a composite structure, pin joints which join the composite to metal by arrays of pins protruding from metal elements inserted into composite during curing process and loop joints which consist in entangling reinforcing fibres into loops protruding from metal elements As those methods vary significantly, the summary section of this paper contains a comparison of those methods with reference to their features, which is important from the point of view of a composite structure designer: possibility of the joint disassembly, damages induced in composite, complication level, weight penalty, range of possible materials to be joined, and the joint strength. This section is divided into subsections which facilitate fast familiarization with the most important conclusions

Riveted Joints
Self-Piercing Riveting
Friction Riveting
Mechanical Clinching
Non-Adhesive Form-Locked Joint
Pin Joining
Loop Joining
Additive Manufacturing
Summary
Disassembling
Complication and Damages Induced by Joining
Applicability to Thermoset and Thermoplastic Matrices
Level of Development
Strength
Future Perspectives
Findings
10. Conclusions
Full Text
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