Innovation: Dynamics In Aircraft Engineering Design And Analysis For Light Optimized Structures

Last update: 30.06.2013
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Keywords: 
work study, method, aerospace technology, industrial manufacture, transport
Today's design and certification procedures of aircrafts are mainly based on conservative static loading which leads to additional weight and, potentially, to a structurally unsafe aircraft.

The overall objective of the DAEDALOS project is to develop methods and procedures to determine dynamical loads considering the effects of dynamic buckling, material damping and mechanical delay during aircraft service. Use of advanced analysis and design principles from DAEDALOS will partly remove the uncertainty and the conservatism of today's design and certification procedures.

DAEDALOS work will hence form the basis for improved common design practices by:
1. Determining accurate dynamic load spectra to be used for structural sizing.
2. Reducing the added weight of aircraft structural components due to conservative design in compliance with quasi-static loads by using more realistic equivalent dynamic loads. This goal will be achieved through improved introduction of the structure damping capacity and detailed analysis.
3. Increasing structural safety using more realistic loading scenarios.
4. Establishing new procedures for the definition of loads to be used during aircraft design and certification by authorities.
The project is organised in five Work packages (WPs).

During the first 18 months of activity, WP2 has been completed, WP3 and WP4 have been started, while WP5, since mainly focused on design guidelines, will start at month 24 collecting the results coming from the other WPs. The main achievements obtained during the first reporting period can be summarised as follows:

1. Critically review and understand the definition of sizing loads for a civil aircraft fuselage
A deep review of the current approach for the definition of sizing loads for transport aircraft has been completed. A preliminary evaluation on the impact of the proposed new design criteria taking into account since the beginning fully dynamic loads has been drawn up.

2. Definition of the analysis models to be adopted for the different stages of analysis
The main achievement is represented by the definition of a common reference aircraft, called DAEDALOS aircraft, representing a mid-size business jet, powered by two turbofan engines mounted in the aft fuselage. The airplane airworthiness category is: large airplane, subjected to FAR / CS 25 regulations. Different types of Finite element (FE) models have been developed with increasing fidelity, to be used in the different phases of the project: a three-dimensional (3D) Finite element method (FEM) model and a stick model of the full aircraft, and different hybrid models connecting together simplified and detailed components of the aircraft.

3. Identification of typical time history loads
The identification of the typical dynamic loads to be used to check the reliability of the proposed approach has been completed with the support of the background and previous experience of the consortium Partners, and mainly of the industrial ones. Three main dynamic loads have been selected: impact load due to landing, vertical and horizontal gust loads. Finally, typical structural components have been identified, where the selected dynamic loads constitute the primary sizing loads, such as an upper skin panel of wing at 70 % spanwise, two fuselage panels (on top and side positions) located between the wing and the tailplanes, and a skin panel of vertical tail located close to the connection of the vertical tail to the fuselage.

4. Comparison of results between static and dynamic sizing loads
Different simulations together with parametric analysis have been completed to identify the main characteristics of the considered dynamic loads and to compare the values of when the current or the new fully dynamic sizing approach are applied. The first preliminary results, obtained with values of damping available from literature, are encouraging about the project targets.

5. Study of distribution of energy dissipation
Dedicated methodologies have been developed and implemented for investigating the effect of structural dissipation due to damping by means of FE analyses. Specific damping models have been implemented, such as the ones starting from the general viscoelastic Maxwell or Kelvin-Voight material models, trying to overcome the limitation of the traditional Rayleigh hypothesis usually adopted in dynamic simulations.

6. Damping measurement on specimens
The building-up of a reliable data base of damping values for the typical materials and structural configurations to be used during the dynamic simulations on different FE models constitutes one of the main project targets. During the first reporting period the measurement of loss factor, using for example the hysteresis loop method, has been completed for the specimens specifically manufactured for this aim. The biggest part of the test campaign on structural components, panels and shells, will be performed during the second part of DAEDALOS project.
The expected results and strategic impacts of the DAEDALOS project can be summarised as follows:
- determine more realistic loads that act along an aircraft structure;
- establish a scientific basis for reduction of pseudo-static loads to be used for sizing of aircraft structure, as well as for internal force redistribution in the structure;
- define a new structural concept and design philosophy that will be capable of improving the dynamic response of aircraft fuselage structure;
- expand the frontiers of knowledge beyond the state of art, which should lead to innovative technologies in experimentation and simulation;
- update the current design philosophy leading to about 15 % weight reduction in the structure;
- reduce the environmental impact and the operating costs of future passenger aircraft.

List of websites: http://www.daedalos-fp7.eu

Collaboration sought: N/A

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This innovation is the result of the project

Title: Dynamics In Aircraft Engineering Design And Analysis For Light Optimized Structures

Acronym: 
DAEDALOS

Runtime: 
01.11.2010 to 31.10.2013

Status: 
completed project

Organisations and people involved in this eco-innovation.

Please click on an entry to view all contact details.

POLITECNICO DI MILANO

(Italy)

Role in project: Project Coordination

Contact person: Mr. MONGILARDI Fulvio

Phone: +39-0223998331

Contact

ADVANCED LIGHTWEIGHT ENGINEERING BV

(Netherlands)

Contact person: Mr. KOPPERT Jan-Jaap

Website: http://www.ale.nl

Phone: +31-152513430

Contact

AERNNOVA ENGINEERING SOLUTIONS SA

(Spain)

Contact person: Mr. MOLAS Francisco

Website: http://www.aernnova.com

Phone: +39-945185672

Contact

ALENIA AERMACCHI SPA

(Italy)

Contact person: Dr. VALERIO Carlo Oreste

Phone: +39-0331813726

Contact

DEUTSCHES ZENTRUM FUER LUFT - UND RAUMFAHRT EV

(Germany)

Contact person: Mr. RENKER Michael

Website: http://www.dlr.de

Phone: +49 531 295 2119

Contact

GOTTFRIED WILHELM LEIBNIZ UNIVERSITAET HANNOVER

(Germany)

Contact person: Prof. ROLFES Raimund

Website: http://www.uni-hannover.de

Phone: +49-5117622992

Contact

ISRAEL AEROSPACE INDUSTRIES LTD.

(Israel)

Contact person: Mrs. GHILAI Gila

Website: http://www.iai.co.il

Phone: +972-3-9358685

Contact

LETOV LETECKA VYROBA S.R.O.

(Czech Republic)

Contact person: Mr. KRENA Josef

Phone: +420-234312081

Contact

RHEINISCH-WESTFAELISCHE TECHNISCHE HOCHSCHULE AACHEN

(Germany)

Contact person: Prof. SCHMACHTENBERG Ernst

Website: http://www.rwth-aachen.de

Phone: +49-2418090490

Contact

SMR ENGINEERING & DEVELOPMENT SA

(Switzerland)

Contact person: Dr. MERAZZI Silvio

Website: http://www.smr.ch

Phone: +41-323452121

Contact

TECHNION - ISRAEL INSTITUTE OF TECHNOLOGY

(Israel)

Contact person: Mr. LAVAN Jack

Website: http://www.technion.ac.il

Phone: +972-48293097

Contact

TOTALFORSVARETS FORSKNINGSINSTITUT

(Sweden)

Contact person: Mr. JARLAS Rolf

Phone: +46-855503144

Contact

VYSOKE UCENI TECHNICKE V BRNE

(Czech Republic)

Contact person: HLINKA Jiri

Website: http://www.vutbr.cz

Phone: +420-541142584

Contact