Start Date: 01/09/2011;xNLx;End Date: 31/08/2015;xNLx;
Airbus Operations GMBH Hamburg hosted a 3-day event on September 6th – 8th 2011 during which the official launch of the SARISTU project took place.
AS07 The materials’ selection has been completed and quantified
AS07 The test specimen geometry has been defined.
AS07 Panel geometry for the IS13 top panel has been identified, including thickness range (1,6mm – 3,8mm).
AS06 4 main working groups have been defined: Manufacturing; Specifications; Software/Algorithms; Simulation
AS06 M21 resin + T800 fibres have been defined for the Door Surround Structure.
AS06 The test matrix contains 4 main groups: i) mechanical fatigue testing (sensor/bondline), ii) non-disturbance testing, iii) guided wave propagation simulation and visualization and iv) panel impact testing.
AS07 The stringer pitch has been fixed at 208mm, also the Omega stringer geometry has been defined.
AS01 The 2D optimizations in span sections have been completed
AS05 A 3-level strategy has been proposed for SHM: skin level Barely VIsible Damages, stringer-skin debondings and a combination of the first two on sub-components. Guided Waves based Structural Health Monitoring systems validated at the three levels are the main objectives of SARISTU AS05.
The Smart Intelligent Aircraft Structures project focuses on the Physical Integration of very different technological approaches acting in synergy. The three key areas are the further development of conformal morphing; structural health monitoring and specific Carbon Nanotube based material approaches. Following the three day September 2011 Kick-off Meeting at the Airbus Operations GmbH site in Hamburg with 130 participants, the project launch phase currently focuses on the collation and generation of specifications for the three main technological areas. In many cases, the high level of integration requires the preparation of completely new specifications such as a wing skin monitoring system or the integration of Carbon Nanotubes into Carbon Fibre Laminates. Targeting a February 2012 completion of the specification phase, partners are heavily involved with the preparation of the first set of ten critical concept reviews which conclude the project launch phase.
AS10 The test matrix has been completed for scenario level testing, for specimen and element level testing.
Afyon Kocatepe University (AKU), 2011. AKU’s FP7 Project funded by EC. Gazete 3 Newspaper, December 8th, 2011.
AS09 The test matrix has been completed for Scenario level testing.
Afyon Kocatepe University (AKU), 2011. Afyon Kocatepe University (AKU) works on a project to prevent lightning strike damage to airplanes, ZAMAN Newspaper (Turkey), December 15th, 2011
AS08 Two partners are working on two different types of coating: sol-gel and clearcoat with the aim to get: i) the best compatibility with the sensors, ii) the best impact revelation, and iii) the optimised impact energy thresholds.
IS12 The reference wing aerodynamic loftline (CAD 5) data have been provided to all related partners.
AS04 Exchange of information with Integration Scenarios with regards to the developments inside AS04 and the required actions to be taken in IS12 and IS13 for the manufacturing of system integrated demonstrator parts (lower fuselage & wing panel, front & rear wing spar, adaptive trailing edge.
AS09 The strategy and way forward for both liquid composite moulding and prepreg processes have been defined.
AS10 TECPAR has produced CNT doped PA fibres to understand the influence of CNT’s on the PA fibre extrusion process and also the mechanical properties of the PA itself.
IS13 Potential synergies with MAAXIMUS are being identified.
AS07 Two sizes of spherical hail stones have been decided to be used for the testing.
IS13 The main material decisions have been finalised.
AS08 Specifications have been established by EADS France jointly with Airbus Germany for internal impact detection.
AS10 The strategy and way forward for both liquid composite moulding and prepreg processes have been defined.
AS10 EADS-F has developed a draft design of the metallic strip for the composite frame structure of the fuselage.
IS13 A positive discussion regarding the synergies between MAAXIMUS and SARISTU has been initiated with the respective Project Coordinators to enable closer collaboration between the two projects.
AS10 The AS10 test matrix for metallic strips has been completed by EADS-F. (concerning electrical, thermal and mechanical tests)
IS12 Aeroelastic model has been provided to related partners.
Soykasap O., 2012. Smart intelligent aircraft structures. TUBITAK, Training Seminar January 16, 2012, Afyonkarahisar, Turkey.
AS09 TECPAR has produced CNT doped PA fibres to understand the influence of CNT’s on the PA fibre extrusion process and also the mechanical properties of the PA itself.
Perelli A., De Marchi L., Marzani A., Speciale N., 2012. Acoustic emission localization in plates with dispersion and reverberations using sparse PZT sensors in passive mode. IOP Publishing, Smart materials and structures, Smart Material Structures, Volume 21, Issue 2, doi:10.1088/0964-1726/21/2/025010.
AS06 The test parameters are being defined (based on AITM) and a corresponding document is under preparation
IS12 Wing morphed shapes (CAD) and relevant aerodynamic loads conditions have been released to Application Scenarios
AS08 Three partners are working on different possible impact sensors: microencapsulation of coloured compounds (visual range or under ultraviolet light), incorporation of active species into porous silica nanocontainers, and use of piezochromic pigments that change colour under pressure.
AS02 Actuators system and layout definition is progressing
AS08 CNRS has been working on piezochromic pigments. Three different Molybdate piezochromic pigments have been investigated. It was shown that the temperature has a high influence on the pressure transition, so either temperature indication should be known when the impact occurs or the temperature range should be limited in this application.
IS13 The majority of the relevant design rules have been identified and distributed.
AS03 The design conditions for the reference wing have been provided
AS05 The Test matrix is under finalization
AS08 As frames and omega stringers are prone to delamination after impact, two impact thresholds have been established according to Airbus damage tolerance team interests: 10 Joules +/-2 Joules for thin parts (1.2mm) and 20 Joules +/-2 Joules for thicker parts (2.5mm).
AS03 The aerodynamic loads for the winglets have been made available
IS12 The reference wing aeroelastic model based on wing aerodynamic loftline, which represents the stiffness and the inertial characteristics of the SARISTU A/C wing box, has been developed. An aerodynamic mesh, based on Nastran DLM, has been coupled to the structure in order to carry out a preliminary aero-elastic analysis (modal, divergence and flutter) to assess the consistency of the wing torsion stiffness increasing the aerodynamic load.
AS07 The test program regarding the “Comparative Vacuum Monitoring – Through The Thickness (CVM-TTT)” has been defined.
AS05 The test-articles production scheduling and work sharing anticipating the first batch of coupon production at the beginning of second year is under finalization
AS07 Additional panels have been manufactured in different thicknesses for laser drilling tests.
AS06 A detailed list of requirements is defined.The first set of CFRP specimen has been laminated.
The Smart Intelligent Aircraft Structures project has launched its official website www.saristu.eu, where you can be informed about the project and follow its progress. The website gives an overview of the project objectives and, through regular updates of the current status, progress and key milestone results. Seven months after the Kick-off meeting, SARISTU is nearly at the end of its specification phase. With the conduct of 11 bi-annual reviews in January and February 2012, the review process orientated on Technology Performance, Value & Risk, Aircraft Operations, Engineering and Project Performance, indicated an overall satisfactory status when compared to the initial planning.
AS06 The Baseline for CFRP layup, thicknesses, etc. has been defined
IS12 The complete version of the deliverable 121.1 “Reference baseline wing and morphing wing aeromechanical requirements” has been finalized.
We'd love to hear from you. Please send questions or feedback to the below email addresses.
Before contacting us, you may wish to visit our FAQs page which has lots of useful info on Tiki-Toki.
We can be contacted by email at: hello@tiki-toki.com.
You can also follow us on twitter at twitter.com/tiki_toki.
If you are having any problems with Tiki-Toki, please contact us as at: help@tiki-toki.com
Close