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Theoretical and experimental evaluations of strain field modification induced by flaws in loaded composite structures

Periodic Reporting for period 1 - MODIFLAW (Theoretical and experimental evaluations of strain field modification induced by flaws in loaded composite structures)

Reporting period: 2020-07-01 to 2021-04-30

MODIFLAW project is part of Clean Sky 2 initiative.
MODIFLAW project aims at becoming a part of R-IADP. Outputs of MODIFLAW project will cover the definition, design, manufacturing, assembling and on-ground testing phases for full-scale structural Outer Wing Box (WP 3.1) and Fuselage and Passenger Cabin demonstrators (WP 3.2) representative of a Regional Aircraft.

The main objectives of the project are:

• To develop, apply and validate numerical models of the strain field modification induced
by the presence of flaws with different kind of morphology and size.
• To define virtual morphology for diagnostic indications provided by the Structural Health
Monitoring (SHM) data and software on damaged representative subcomponents and
structures.
During the first 10-month period (July 2020 to April 2021) the main efforts started with definition of typical flaws according to the airworthiness requirements mentioned in international standard AMC 20-29 for the evaluation of composite materials and other related documentation. VZLU summarized definition of flaws and impact damage relevant to the project scope. The resulted documentation also comprehended finite element models and numerical concepts of flaws modelling.

Next part was focused on test plan preparation which defined and documented all the selected test methods, test standards requirements and all additional requirements related to the specimens and elements fabrication and testing. This work was based on extensive FE modelling to design proper insert definition that would be put in the composite plates during manufacturing. The modelling included two types of damage (manufacturing damage - inserts and impact damage) which was simulated and compared with a pristine specimen condition. Tension, compression and bending loading was considered in the models.

When the test plan was finished, TM started with the plates and beam manufacturing. These were delivered to VZLU for specimen extraction just in the end of the reporting period.

Dissemination and management activities were performed in parallel. An abstract with selected modelling results “Numerical evaluations of strain field modification induced by production flaws in loaded composite structures” was submitted to ICEAF VI conference to be held in June.
MODIFLAW project aims at becoming a part of R-IADP. Outputs of MODIFLAW project will cover the definition, design, manufacturing, assembling and on-ground testing phases for full-scale structural Outer Wing Box (WP 3.1) and Fuselage and Passenger Cabin demonstrators (WP 3.2) representative of a Regional Aircraft.

In WP 3.1 innovative low cost and low weight processes and SHM technologies shall be integrated into the Outer Wing Box on ground demonstrator with the objective to obtain: structural weight reduction, manufacturing and assembling recurring cost reduction, maintenance improvement and implementation of new eco-compatible materials and processes.

In WP 3.2 advanced composite, innovative low cost and low weight processes and SHM technologies shall be integrated into the Fuselage structural demonstrator with the objective to obtain: structural weight reduction, manufacturing recurring cost reduction, maintenance
improvement and implementation of new eco-compatible materials and processes.

VZLU will utilise its knowledge, experience, infrastructure and human resources in order to realise this high level objective.
MODIFLOW SHM