Body Freedom Flutter of High Aspect Ratio Flying Wings

Love, Michael; Zink, P. Scott; Wieselmann, Paul; Youngren, Harold

doi:10.2514/6.2005-1947

Cited by 64 publications

(29 citation statements)

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“…(9)- (10), follows the modeling construct rationale of [16], despite the signicant simplications adopted in this model. It is also noted that BFF is well predicted using linear models for the aircraft and is not the result of aerodynamic or structural nonlinearities [3], hence the hypotheses underpinning the dynamics in Eq. (11).…”

Section: Fig 2 Straight Wing Geometry B Flexible Aircraft Modelmentioning

confidence: 99%

“…These references showed that inertia and stiness play a decisive role in modifying free-vibration properties, bringing the lowest elastic natural frequencies closer to the frequencies characteristic of the vehicle motion. They also modify the corresponding mode shapes [3]. Similarly, aircraft geometry (with its associated eect on the stability derivatives) is also decisive.…”

Section: Preliminary Considerations and Test Case Denitionmentioning

confidence: 99%

“…a reduction in wing mass enhances the aircraft proneness to BFF) reconciles with known features of BFF in the literature, as was the case for D and EI. In fact, this aspect was ascribed in [3] to the eect that a lower vehicle pitch inertia I yy had in increasing the short period frequency ω SP (recall its expression in Eq. (7)) and thus pushing it closer to the wing bending lowest frequency.…”

Section: Robust Analysismentioning

confidence: 99%

See 2 more Smart Citations

Study of Flexible Aircraft Body Freedom Flutter with Robustness Tools

Iannelli

Marcos

Lowenberg

2018

Journal of Guidance, Control, and Dynamics

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General rightsThis document is made available in accordance with publisher policies. Please cite only the published version using the reference above. Full terms of use are available: http://www.bristol.ac.uk/pure/about/ebr-terms Features that complicate its study are the presence of multiple modal instabilities, and the dierent inuence that system parameters have on each of them. The robust analysis framework based on Linear Fractional Transformation modeling and structured singular value µ analysis is used in this work to study the BFF problem in a systematic way. The analyses performed showcase the potential of these methods, not only in supplying a characterization of the system in terms of its robustness, but also in gaining further understanding of the BFF problem and reconciling the results with physical features. It is also shown that the robust modeling analysis framework complements the conventional, state of practice, methods while allowing the study of highly coupled systems (of which the exible aircraft is an example) to be addressed in an incremental and methodological manner.

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Section: Fig 2 Straight Wing Geometry B Flexible Aircraft Modelmentioning

confidence: 99%

Section: Preliminary Considerations and Test Case Denitionmentioning

confidence: 99%

Section: Robust Analysismentioning

confidence: 99%

See 1 more Smart Citation

Study of Flexible Aircraft Body Freedom Flutter with Robustness Tools

Iannelli

Marcos

Lowenberg

2018

Journal of Guidance, Control, and Dynamics

View full text Add to dashboard Cite

show abstract

“…As shown in [10], the aeroelastic derivatives calculation process is prompted by the same line of reasoning, with integrals employed to take into account variability of the properties along the span. Moreover, it is known [12] that BFF is well predicted using linear models for the aircraft and is not the result of non-linear aerodynamics or structural nonlinearities.…”

Section: Body Freedom Flutter Modelingmentioning

confidence: 99%

“…3. Aircraft Model Geometry literature [12] that wing/fuselage/tail configurations can also undergo this instability for an adverse combination of design parameters. The wing is described by the parameters defining Goland wing [8], with the only exception of EI, which is assumed as a design variable that reflects the tendency towards a lightweight-oriented structural sizing.…”

Section: A Air Vehicle Configurationmentioning

confidence: 99%