Recent Technological Advances
BEASY has an active programme to develop new technology and services, and in this month's newsletter we feature some of these activities. |
Residual Stresses
Residual stresses are important as they can retard crack initiation and growth. If they are not considered in the simulation then overly conservative designs can result.
It was reported in a previous newsletter how BEASY have been working with some of our aerospace customers to develop simulation tools and technologies to simulate the growth of 3D cracks in residual stress fields. (Please see 3D Crack Growth Simulation Using BEASY)
In this month's newsletter we highlight a paper which provides an interesting insight into the importance of residual stresses and their impact on crack growth.
For more information on BEASY Crack Growth simulation services and software, please contact info@beasy.com |
Analytical Tools for Residual Stress Enhancement of Rotorcraft Damage Tolerance
A paper which discusses the importance of residual stresses and contact was published at the American Helicopter Society International Forum by S.C. Gould, M.R. Urban, J.C. Newman, S. Ismonov, M.R. Hill, J.E. VanDalen.
Please click here for details of the authors and abstract.
 In the paper the importance of incorporating contact, friction, fastener pre load, head fixity, bending, and load redistribution in a crack growth simulation model is described in order to obtain accurate predictions. In the study to account for all of these effects BEASY was used to model the specimen.
A full version of the paper can be found at https://vtol.org/store/product/analytical-tools-for-residual-stress-enhancement-of-rotorcraft-damage-tolerance-5293.cfm |
Crack Growth Analysis Of A Riveted Fuselage Skin 
Sharon Mellings recently presented a paper with Robert Adey and Roberto Citarella of the University of Salerno at the 35th International Conference on Boundary Elements and Other Mesh Reduction Methods
on some new developments to improve the modelling of cracks in aircraft structures. Generally aircraft structures are highly complex, involving complex load paths, however cracks are often localised features involving just a few of the structural components. One particular location for damage is near to riveted connections where localised forces can lead to fatigue damage problems. These areas can be where stiffening ribs are attached to the aircraft skin, where two or more skin sections are overlapped or where holes in the skin are covered by additional doubler panels.
The paper presented a model which can be used to predict the crack growth path and residual strength of the structure. The simulation technology was tested by applying it to a large scale structure consisting of a number of panels stiffened by ribs and stringers. Virtual Testing of the structure was performed to predict the structural failure due to crack growth and the estimated fatigue life of the structure.
For more information on the paper, or for more information on BEASY Crack Growth simulation services and software, please contact info@beasy.com |
Training
Courses are held regularly at BEASY's offices near Southampton in the UK, and at Billerica, Massachusetts in the USA.
Courses are also held at customers' sites and can be tailored to meet the specific needs of the client.
To discuss your requirements further, please contact us
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If you would like to learn more about any of the above, or if you have a project which you would like to discuss, please contact us |
