TY - GEN
T1 - Deployable wing model using ancf and uvlm
T2 - AIAA Scitech Forum, 2020
AU - Otsuka, Keisuke
AU - Wang, Yinan
AU - Fujita, Koji
AU - Nagai, Hiroki
AU - Makihara, Kanjuro
N1 - Funding Information:
This work was supported by the Japan Society for the Promotion of Science (JSPS) KAKENHI (Grant Number 18K18905). The wing deployment experiments were performed under the Collaborative Research Project of the Institute of Fluid Science (IFS), Tohoku University. We acknowledge the use of the IFS wind tunnel facility for the experiments.
Publisher Copyright:
© 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
PY - 2020
Y1 - 2020
N2 - This paper presents a deployable-wing multifidelity modeling method based on an asymmetrically gradient-deficient absolute nodal coordinate formulation coupled with unsteady vortex lattice method. Slender deployable wings are composed of multiple bodies connected by hinge joints and can be deployed or folded spanwise during flight. Low-fidelity and high-fidelity deployment simulation models are required for the conceptual and actual design phases of the wings, respectively. The presented multifidelity modeling method can be used for computationally efficient low-fidelity rigid multibody simulation and more realistic high-fidelity flexible multibody simulation. These multi-fidelity simulations are accomplished using a consistent modeling process and the same simulation program architecture. In addition, a consistent methodology can be used to couple an aerodynamic model with the low-fidelity and high-fidelity structural models. To demonstrate the effectiveness of the presented method, we newly present simulations using benchmark slender wing parameters in this paper. To validate the proposed modeling method, wing deployment experiments were performed in a wind tunnel at the Institute of Fluid Science, Tohoku University. Good agreement was found between the simulation using the presented method and the wind tunnel experiments, even when the wings experienced large geometrically nonlinear deformations.
AB - This paper presents a deployable-wing multifidelity modeling method based on an asymmetrically gradient-deficient absolute nodal coordinate formulation coupled with unsteady vortex lattice method. Slender deployable wings are composed of multiple bodies connected by hinge joints and can be deployed or folded spanwise during flight. Low-fidelity and high-fidelity deployment simulation models are required for the conceptual and actual design phases of the wings, respectively. The presented multifidelity modeling method can be used for computationally efficient low-fidelity rigid multibody simulation and more realistic high-fidelity flexible multibody simulation. These multi-fidelity simulations are accomplished using a consistent modeling process and the same simulation program architecture. In addition, a consistent methodology can be used to couple an aerodynamic model with the low-fidelity and high-fidelity structural models. To demonstrate the effectiveness of the presented method, we newly present simulations using benchmark slender wing parameters in this paper. To validate the proposed modeling method, wing deployment experiments were performed in a wind tunnel at the Institute of Fluid Science, Tohoku University. Good agreement was found between the simulation using the presented method and the wind tunnel experiments, even when the wings experienced large geometrically nonlinear deformations.
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U2 - 10.2514/6.2020-1678
DO - 10.2514/6.2020-1678
M3 - Conference contribution
AN - SCOPUS:85092358721
SN - 9781624105951
T3 - AIAA Scitech 2020 Forum
BT - AIAA Scitech 2020 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
Y2 - 6 January 2020 through 10 January 2020
ER -