Nonlinear structural damping effects on F-16 limit cycle oscillations

P. C. Chen, Z. Zhang, Z. Zhou, X. Q. Wang, Marc Mignolet

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Recent studies of the occurrence of post-flutter limit cycle oscillations (LCO) of the F-16 have provided good support to the long-standing hypothesis that this phenomenon involves a nonlinear structural damping. The proposed mechanism for the appearance of nonlinearity in the damping are the nonlinear geometric effects that arise when the deformations become large enough to exceed the linear regime. A pair of earlier investigations have first developed a finite element-based reduced order modeling (ROM) framework with nonlinearity in damping and potentially nonlinearity in stiffness to predict the aircraft response. These studies have also demonstrated, with an appropriate calibration of the single model parameter, a good match between flight test LCO amplitudes and those predicted by the model. The focus of the present investigation is first to extend the validation of the approach to an interesting set of flight test results shedding important light on the importance of the aerodynamic forces generated by the control surfaces of tip missiles of the F-16 LCO characteristics. The second objective is to include the nonlinearity in stiffness associated with the large deformations that had not been considered before and to assess whether it can be a LCO bounding mechanism.

Original languageEnglish (US)
Title of host publicationAIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Edition210059
ISBN (Print)9781624105241
DOIs
StatePublished - Jan 1 2018
EventAIAA Aerospace Sciences Meeting, 2018 - Kissimmee, United States
Duration: Jan 8 2018Jan 12 2018

Other

OtherAIAA Aerospace Sciences Meeting, 2018
CountryUnited States
CityKissimmee
Period1/8/181/12/18

Fingerprint

Damping
Stiffness
Control surfaces
Missiles
Aerodynamics
Aircraft
Calibration

ASJC Scopus subject areas

  • Aerospace Engineering

Cite this

Chen, P. C., Zhang, Z., Zhou, Z., Wang, X. Q., & Mignolet, M. (2018). Nonlinear structural damping effects on F-16 limit cycle oscillations. In AIAA Aerospace Sciences Meeting (210059 ed.). American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-2064

Nonlinear structural damping effects on F-16 limit cycle oscillations. / Chen, P. C.; Zhang, Z.; Zhou, Z.; Wang, X. Q.; Mignolet, Marc.

AIAA Aerospace Sciences Meeting. 210059. ed. American Institute of Aeronautics and Astronautics Inc, AIAA, 2018.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Chen, PC, Zhang, Z, Zhou, Z, Wang, XQ & Mignolet, M 2018, Nonlinear structural damping effects on F-16 limit cycle oscillations. in AIAA Aerospace Sciences Meeting. 210059 edn, American Institute of Aeronautics and Astronautics Inc, AIAA, AIAA Aerospace Sciences Meeting, 2018, Kissimmee, United States, 1/8/18. https://doi.org/10.2514/6.2018-2064
Chen PC, Zhang Z, Zhou Z, Wang XQ, Mignolet M. Nonlinear structural damping effects on F-16 limit cycle oscillations. In AIAA Aerospace Sciences Meeting. 210059 ed. American Institute of Aeronautics and Astronautics Inc, AIAA. 2018 https://doi.org/10.2514/6.2018-2064
Chen, P. C. ; Zhang, Z. ; Zhou, Z. ; Wang, X. Q. ; Mignolet, Marc. / Nonlinear structural damping effects on F-16 limit cycle oscillations. AIAA Aerospace Sciences Meeting. 210059. ed. American Institute of Aeronautics and Astronautics Inc, AIAA, 2018.
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