A revision of the flutter margin method to predict in real-time the limit cycle oscillations onset speed with structural freeplay present in the plunge axis

Casado Corpas, José and Sanz Lobera, Alfredo and González Requena, Ignacio and Sevilla, L. (2016). A revision of the flutter margin method to predict in real-time the limit cycle oscillations onset speed with structural freeplay present in the plunge axis. "Proceedings of the Institution of Mechanical Engineers : Journal of Aerospace Engineering", v. 231 (n. 1); pp. 124-142. ISSN 0954-4100. https://doi.org/10.1177/0954410016638867.

Description

Title: A revision of the flutter margin method to predict in real-time the limit cycle oscillations onset speed with structural freeplay present in the plunge axis
Author/s:
  • Casado Corpas, José
  • Sanz Lobera, Alfredo
  • González Requena, Ignacio
  • Sevilla, L.
Item Type: Article
Título de Revista/Publicación: Proceedings of the Institution of Mechanical Engineers : Journal of Aerospace Engineering
Date: January 2016
ISSN: 0954-4100
Volume: 231
Subjects:
Freetext Keywords: Flutter margin, limit cycle oscillations, aeroelasticity
Faculty: E.T.S. de Ingeniería Aeronáutica y del Espacio (UPM)
Department: Materiales y Producción Aeroespacial
Creative Commons Licenses: Recognition - No derivative works - Non commercial

Full text

[img]
Preview
PDF - Requires a PDF viewer, such as GSview, Xpdf or Adobe Acrobat Reader
Download (1MB) | Preview

Abstract

Computational fluid dynamic and order reducing methods have been extensively applied to predict the flutter onset speed of several types of aircrafts. However, the accuracy required by certification standards still ascribes flight testing as the only method available that safely validates the flight envelope of an aircraft. In particular, free-flutter conditions must be demonstrated in the target flight envelope, and several methods have been developed to determine the flutter onset speed in real-time when expanding the envelope during flight testing. Among the methods, the damping versus velocity technique combined with a flutter margin implementation remains the most common technique used for envelope expansion. Even with the popularity and ‘‘easy to implement’’ characteristics of this method, several shortcomings can adversely affect the identification of non-stable conditions during envelope expansion. Notably, the limit cycle oscillations conditions, distinct from flutter, cannot be accurately identified. This study proposes to apply a similar methodology to the flutter margin to anticipate limit cycle oscillations associated with freeplay in the plunge axis of a bi-dimensional airfoil that is aeroelastically representative of the tested aircraft. Analytical considerations are conducted to support this new approach, and a computer model is used to validate the proposed methodology.

More information

Item ID: 48187
DC Identifier: http://oa.upm.es/48187/
OAI Identifier: oai:oa.upm.es:48187
DOI: 10.1177/0954410016638867
Official URL: https://journals.sagepub.com/doi/10.1177/0954410016638867
Deposited by: Memoria Investigacion
Deposited on: 29 Jan 2018 13:36
Last Modified: 03 Jun 2019 11:18
  • Logo InvestigaM (UPM)
  • Logo GEOUP4
  • Logo Open Access
  • Open Access
  • Logo Sherpa/Romeo
    Check whether the anglo-saxon journal in which you have published an article allows you to also publish it under open access.
  • Logo Dulcinea
    Check whether the spanish journal in which you have published an article allows you to also publish it under open access.
  • Logo de Recolecta
  • Logo del Observatorio I+D+i UPM
  • Logo de OpenCourseWare UPM