Determination of the optimal way to increase the inner radius of a thick-walled cylindrical coupling made of shape memory alloy


Аuthors

Sharunov A. V.

PJSC UAC Sukhoi Design Bureau, 23A, Polikarpova str., Moscow, 125284, Russia

e-mail: aleksej-sharunov@yandex.ru

Abstract

One of the most promising applications of SMAin the aviation industry is the manufacture of couplings from them designed for thermomechanical connection (TMC) of pipelines. Currently, in the Sukhoi Design Bureau, an analysis of the possibility of using the above alloys in the hydraulic system of the aircraft has been carried out, zones of preferred use of SMA couplings in the airframe design have been identified (“dry zones”, “embedded zones” under composite panels). The use of coupling joints from SMA was also considered for carrying out repair work of fuel and hydraulic systems of aircraft directly in the places of basing and operation of aircraft.

As part of the work, mathematical models of SMA material were developed in the Simulia AbaQus finite element modeling software package, capable of describing the functional properties of SMA implemented during the entire life cycle of a coupling made of this material. In addition, the models have a high level of availability and can be used in solving most technical projects for the introduction of SMA elements into the design of aircraft, including when designing thermomechanical connections using couplings made of this material. Two alternative ways of increasing the internal radius of the SPF coupling are also proposed, a comparison with the currently used dorning method is carried out, and the optimal approach is identified.

The reliability of the results of the work is confirmed by the validation of the developed software modules based on the results of field tests of elementary samples based on the Ni-Ti system and verification by known analytical solutions of model boundary value problems of SMA mechanics.

Keywords:

shape memory alloys, thermomechanical coupling, hydraulic and fuel systems of aircraft, finite element method, Simulia AbaQus, stress–strain state

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