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Research Papers

Versatile Absolute Nodal Coordinate Formulation Model for Dynamic Folding Wing Deployment and Flutter Analyses

[+] Author and Article Information
Keisuke Otsuka

Department of Aerospace Engineering,
Tohoku University,
6-6-01 Aramaki-Aza-Aoba, Aoba-Ward,
Sendai 980-8579, Japan
e-mail: otsuka@ssl.mech.tohoku.ac.jp

Yinan Wang

Imperial College London,
London SW7 2AZ, UK
e-mail: yw3@hotmail.co.uk

Kanjuro Makihara

Department of Aerospace Engineering,
Tohoku University,
6-6-01 Aramaki-Aza-Aoba, Aoba-Ward,
Sendai 980-8579, Japan
e-mail: makihara@ssl.mech.tohoku.ac.jp

1Corresponding author.

Contributed by the Technical Committee on Vibration and Sound of ASME for publication in the JOURNAL OF VIBRATION AND ACOUSTICS. Manuscript received February 28, 2018; final manuscript received July 25, 2018; published online September 10, 2018. Assoc. Editor: Stefano Gonella.

J. Vib. Acoust 141(1), 011014 (Sep 10, 2018) (10 pages) Paper No: VIB-18-1087; doi: 10.1115/1.4041022 History: Received February 28, 2018; Revised July 25, 2018

Aircraft performance can be improved using morphing wing technologies, in which the wing can be deployed and folded under flight conditions, providing a wide flight envelope, good fuel efficiency, and reducing the space required to store the aircraft. Because the deployment of the wing is a nonlinear-coupled motion comprising large rigid body motion and large elastic deformation, a nonlinear folding-wing model is required to perform the necessary time-domain deployment simulation, while a linear model is required to perform the frequency-domain flutter analysis. The objective of this paper is to propose a versatile model that can be applied to both the time-domain and frequency-domain analyses of a folding wing, based on flexible multibody dynamics (MBD) using absolute nodal coordinate formulation (ANCF) and unsteady aerodynamics. This new versatile model expands the application range of the flexible MBD using ANCF in time-domain simulation, allowing it to express the coupled motion of extremely large elastic deformations and large rigid body motions that arise in next-generation aircraft. The time-domain deployment simulation conducted using the proposed model is useful for parametric deployment-system design because the model has improved calculation time. In the frequency-domain flutter analysis of a folding wing, the flutter speed obtained from the proposed model agrees with that obtained from an experiment, with an error of 4.0%, showing promise for application in next-generation aircraft design.

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Figures

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Fig. 1

Conceptual view of a folding wing

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Fig. 2

The ANCF beam element

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Fig. 9

Time history of fold angle and wingtip torsion in flexible wing deployment

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Fig. 10

Comparison of calculation time required for time-domain deployment simulation between strongly and weakly nonlinear elastic forces

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Fig. 3

Modeling of rotational inertia variation

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Fig. 4

Large axis motion of the beam specified in Sec. 4.3 from Fan and Zhu [17], caused by a vertical force 3600sinπt on the free end

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Fig. 5

(a) Horizontal and (b) vertical displacements at the tip of the cantilever beam specified in Sec. 4.3 from Fan and Zhu [17], caused by a vertical force 3600sinπt on the free end

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Fig. 6

Large rigid body motion and elastic deformation of the spinning beam specified in Sec. 4.4 from Fan and Zhu [17], caused by a prescribed rotation on the connected end

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Fig. 7

(a) Longitudinal and (b) transverse deflections at the tip of the spinning beam specified in Sec. 4.4 from Fan and Zhu [17], caused by a prescribed rotation on the connected end

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Fig. 8

Beam axis motion of flexible wing deployment caused by a deployment torque

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Fig. 14

Relationship between lowest frequency for a two-body folding wing and Young's modulus

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Fig. 15

Flutter properties with respect to fold angle for a two-body folding wing. The proposed ANCF model and the experiment are compared.

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Fig. 11

Convergence performance of natural frequency of a one-body wing with respect to number of elements. Analytical, initially linear, and linearized ANCF models are compared.

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Fig. 12

Relationship between eigenvalue and air speed in frequency-domain flutter analysis. Initially linear and linearized ANCF models are compared.

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Fig. 13

Natural frequency with respect to fold angle for a two-body folding wing, calculated by the linearized ANCF model

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