Abstract
The operational safety and reliability of an airplane must be an integral part of its design. The use of suitable materials that pass material certification tests is very important for a new aircraft design. The next part is testing specific samples, sub-components, and components such as the aileron. The paper deals with a non-destructive evaluation of composite primary structural part fatigue tests in accordance with damage tolerance philosophy considering impact damage presence. NDT methods such as visual, eddy current, and ultrasonic testing included phased array technique, are used for the inspections. A schedule of inspections was created, and structural durability was verified.
Highlights
Certification of any airframe structure can be performed by numerical or experimental methodology in accordance with airworthiness requirements
The impact damage was inspected by conventional UT technique during the fatigue testing, and no propagation has been detected
The aim of the article is to show the process of the fatigue test and Non-destructive testing (NDT) inspections during the test
Summary
Certification of any airframe structure can be performed by numerical or experimental methodology in accordance with airworthiness requirements. Current airworthiness requirements specify to prove the durability of composite structure based on damage tolerance philosophy [2,3]. These requirements are experimentally discussed in [4] in detail. The paper deals with a non-destructive evaluation of a primary structure part (aileron) which is manufactured from carbon fibre-reinforced composites using winding technology. The composite aileron is made of carbon filaments (roving) with an epoxy resin in combination with a hardener.
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