Lina Dehmlow, Pedro González, Gerrit Stavorinus, Flávio Silvestre

DOI Number: N/A

Conference number: IFASD-2024-149

One way of reducing an aircraft’s induced drag while meeting airport gate limitations is increasing the wingspan and introducing a folding wingtip. By making the hinge
flexible and rotating it’s axis outboard the folding wingtip could be used to reduce gust loads. As aircraft are becoming more flexible, the flexibility is another important factor that needs to be considered. In the following a set of equations of motion describing a constrained flexible wing with a flared folding wingtip, that considers follower forces of the wing and folding wingtip as well as the geometric exact angle of attack is derived using Lagrange’s method considering the folding wingtip as separate body. The formulation is used to set up an aeroelastic model in MATLAB/Simulink. The model is tested on the TU-Flex wing with a hinge introduced at 80 % span and compared to the original wing. It can be shown that the folding wingtip dynamics have an influence on the stability of the system reducing the damping of the modes and introducing a new lower frequency mode.

Read the full paper here

In Categories: 1. IFASD 2024, 1.Events, Steady/Unsteady Aerodynamics
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.