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MAAXIMUS (More Affordable Aircraft structure through eXtended, Integrated, and Mature nUmerical Sizing)strzaka

The project is being carried out within the EU’s 7th Framework, Aeronautics and Air Transport, FP7-AAT-2007-RTD-1.

The MAAXIMUS Project began in 2008 and is scheduled to conclude in 2013. The Project Coordinator is AIRBUS FRANCE SAS. It is a joint undertaking of 58 partners (airplane manufacturers, material science experts, and computer mechanics, as well as testing centres from the industrial sector and HEIs) from 18 countries, intended to increase the competitiveness and promote continued development of the European aircraft industry in line with the objectives outlined in paragraph AAT.2007.4.4.1 of the EU’s 7th Framework Work Programme. The budget of the entire project exceeds EUR 67 million. The project involves the design and construction of a portion of airplane airframe. The projects main objectives are to:

  • Enable a high-production rate: 50% reduction of the assembly time of fuselage section
  • Reduce the manufacturing and assembly recurring costs by 10% compared to the ALCAS equivalent reference
  • Reduce weight by 10%, compared to best available solutions on similar fuselage sections (F7X, A320 and TANGO fuselage)
  • Reduce by 20% the current development timeframe of aircraft composite structures from preliminary design up to full-scale test
  • Reduce by 10% the non-recurring cost of aircraft composite structures from preliminary design up to full-scale test (ALCAS reference)
  • Reduce the airframe development costs by 5% compared with the equivalent development steps in an industrial context

The innovative composite structures developed within the MAAXIMUS Project, together with correct evaluation and quicker development work will enable a decrease of aircraft construction time and time to market.

The Technology Partners Foundation team, headed by Dr Krzysztof Wiśniewski, is the only Polish participant in the project. The tasks assigned to the Polish team concern stability analysis of composite stiffened panels under shear compression static loads with internal cabin pressure. They are presented below.

Sensitivity analysis for non-linear coating statics

The objective is to develop a methodology and prepare software tools to enable sensitivity analysis of composite with respect to material and geometric parameters of the layers during the structure operation. The task consists of the following sub-tasks:

  • Development and implementation of constitutive models for use in non-linear coating statics for finite element analysis of orthotropic laminate panels.
  • Development and implementation of model of design sensitivity computation with respect to layer thickness and angle of fibre deposition in composite airplane hull coatings. A direct (analytical) method of determining the function and differentiation will be used to compute the constituent parameters and sensitivity.
  • Determination of static solutions and sensitivity for the tested panel.

Constitutive model and microstructure parameter sensitivity analysis

The objective is to develop a methodology and prepare a tool enabling sensitivity analysis of composite coatings with respect to microstructural parameters of the layers during the system’s operation. The task consists of the following sub-tasks:

  • The identification will be performed on the basis of anisotropic properties of the textile layers, including its microstructure. This will be done using a numerical approach based on the Finite Element Method (FEM) as well as the Representative Volume Element (RVE) concept. A substitute constitutive model for a cross-section of a composite with anisotropic layers will also be developed.
  • Development of a sensitivity analysis module for the substitute constitutive model for a cross-section of a composite with anisotropic layers. The design variables are the material and the microstructure parameters. Direct and analytical differentiation will be used (verification will be performed using the Finite Element Method).
  • Computation of solutions for benchmarks and composite panel with respect to statics and sensitivity analysis.