Peculiarities of making bolt and rivet connections with interference when assembling the aircraft MS-21

Abstract

In this paper the peculiarities of installation of fasteners with tension during assembly of MS-21 aircraft are considered. In particular, we considered the aspects of the necessity of using bolt and rivet connections with tension during the assembly of the aircraft fuselage. We have developed a finite element model of the installation process with the rivet bolt in the hole of the package using the system of finite element analysis Simufact. We used the Elastoplastic Concept of Material Behaviour with Nonlinear Hardening Section. And obtained the characteristics of the stress-strain state of the bolt-ribbon joint elements at various moments of rod retraction, including at the predicted moment of shank tear off. It has been revealed that it is expedient to bring the retraction force up to the value close to destructive one. Determined the residual deformations after removal of axial load from the rod. It is proved that it is necessary to actualize the existing normative and technical documentation with specification of the value of the tool impact force on the rivet bolt rod.

Characteristic of Bolt and Nut Pressure Switch of Cessna Caravan Type 208B

“…Installation of 10 bolts per wheel on the ATR 42 aircraft to increase passenger comfort has encouraged for each bolt to be tested with the NDT Test, namely eddy current test, ultrasonic test, day penetrant, and magnetic particle test [5]. Bolt and rivet connection is a very important component in fastener installation during MS-21 aircraft assembly [6]. Ti-6Al-4V bolts that experience creep for too long and overload will show a fracture in the aircraft [7].…”