Marcos C. Ruggeri, Roberto G. A. da Silva, Carlos E. de Souza

DOI Number: N/A

Conference number: IFASD-2015-180

The present work deals with time response and stability simulations of flexible wings using a structural commercial solver, Abaqus. The use of commercial codes for structural analyses are necessary due to their ability to deal with more complex geometry than in-house codes usually do. The problem becomes establishing strategies for coupling these codes with the different aerodynamic solvers. In aeroelasticity this coupling involves passing displacements, velocities and forces from one model to another. Here, Abaqus is coupled to the commercial aerodynamic solver ZAERO. Initially, static stresses are computed based on loads obtained from trim analyses with ZAERO aiming establishing procedures for information coupling between codes. As a first approach, a simplified cantilever rectangular plate with a concentrated mass modelling a ballast located at the wing tip is simulated and then the results are correlated to experimental data for validation. Secondly, a more complex model of an aircraft is also analysed using the same methodology as described above. Finally, some conclusions are presented regarding the importance of including nonlinearity effects in the formulation of flexible wings and then compared to the same simulations assuming a linear theory. Final comments are also mentioned with guidelines for the computational procedures and limitations on the assumptions made to get reasonably accurate results.

Read the full paper here

In Categories: 2. IFASD 2015, Computational Aeroelasticity
Email
Print
LinkedIn
The paper above was part of  proceedings of a CEAS event and as such the author has signed a publication agreement to have their paper published in the repository. In the case this paper is found somewhere else CEAS always links to the other source.  CEAS takes great care in making the correct content available to the reader. If any mistakes are found  in the listings please contact us directly at papers@aerospacerepository.org and we will correct the listing promptly.  CEAS cannot be held liable either for mistakes in editorial or technical aspects, nor for omissions, nor for the correctness of the content. In particular, CEAS does not guarantee completeness or correctness of information contained in external websites which can be accessed via links from CEAS’s websites. Despite accurate research on the content of such linked external websites, CEAS cannot be held liable for their content. Only the content providers of such external sites are liable for their content. Should you notice any mistake in technical or editorial aspects of the CEAS site, please do not hesitate to inform us.