Design methodology for wing trailing edge device mechanisms
| dc.contributor.advisor | Fielding, John | |
| dc.contributor.author | Martins Pires, Rui Miguel | |
| dc.date.accessioned | 2009-05-15T09:37:01Z | |
| dc.date.available | 2009-05-15T09:37:01Z | |
| dc.date.issued | 2007-04 | |
| dc.description.abstract | Over the last few decades the design of high lift devices has become a very important part of the total aircraft design process. Reviews of the design process are performed on a regular basis, with the intent to improve and optimize the design process. This thesis describes a new and innovative methodology for the design and evaluation of mechanisms for Trailing Edge High-Lift devices. The initial research reviewed existing High-Lift device design methodologies and current flap systems used on existing commercial transport aircraft. This revealed the need for a design methodology that could improve the design process of High-Lift devices, moving away from the conventional "trial and error" design approach, and cover a wider range of design attributes. This new methodology includes the use of the innovative design tool called SYNAMEC. This is a state-of-the-art engineering design tool for the synthesis and optimizations of aeronautical mechanisms. The new multidisciplinary design methodology also looks into issues not usually associated with the initial stages of the design process, such as Maintainability, Reliability, Weight and Cost. The availability of the SYNAMEC design tool and its ability to perform Synthesis and Optimization of mechanisms led to it being used as an important module in the development of the new design methodology. The SYNAMEC tool allows designers to assess more mechanisms in a given time than the traditional design methodologies. A validation of the new methodology was performed and showed that creditable results were achieved. A case study was performed on the ATRA - Advance Transport Regional Aircraft, a Cranfield University design project, to apply the design methodology and select from within a group of viable solutions the most suitable type of mechanism for the Variable Camber Wing concept initially defined for the aircraft. The results show that the most appropriate mechanism type for the ATRA Variable Camber Wing is the Link /Track Mechanism. It also demonstrated how a wide range of design attributes can now be considered at a much earlier stage of the design. | en_UK |
| dc.identifier.uri | http://hdl.handle.net/1826/3393 | |
| dc.language.iso | en | en_UK |
| dc.publisher | Cranfield University | en_UK |
| dc.rights | © Cranfield University 2007. All rights reserved. No part of this publication may be reproduced without the written permission of the copyright owner. | en_UK |
| dc.subject | High-Lift device | en_UK |
| dc.subject | flap | en_UK |
| dc.subject | mechanism | en_UK |
| dc.subject | aircraft | en_UK |
| dc.subject | maintainability | en_UK |
| dc.subject | reliability | en_UK |
| dc.subject | cost estimation | en_UK |
| dc.subject | weight estimation | en_UK |
| dc.subject | fairing drag | en_UK |
| dc.subject | design methodology | en_UK |
| dc.subject | variable camber | en_UK |
| dc.title | Design methodology for wing trailing edge device mechanisms | en_UK |
| dc.type | Thesis or dissertation | en_UK |
| dc.type.qualificationlevel | Doctoral | en_UK |
| dc.type.qualificationname | PhD | en_UK |