Abstract
In this paper, a reduced-order modeling approach based on computational fluid dynamics is presented for an elastic wing with control surfaces in the transonic regime. To treat the computational fluid dynamics grid around the geometrical discontinuities, due to the deflection of control surfaces, the constant volume tetrahedron method and the transpiration method are combined together without deforming the grid. Based on the input–output data from the computational fluid dynamics solver, one multiple-input/multiple-output discrete-time state-space model for the wing is identified via a robust subspace algorithm. For each control surface, one one-input/multiple-output discrete-time state-space model is identified using the same algorithm. With the precomputed state-space models for a few flight parameters, the generalized aerodynamic forces over a range of flight parameters can be computed by interpolating the output data. The methodology is applied to an elastic wing model with two control surfaces and the generalized aerodynamic forces are compared with the results from the computational fluid dynamics solver to validate the reduced-order modeling approach in transonic regime.
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Acknowledgments
This work was supported by the National Natural Science Foundation of China under Grant 11472128 and by the Research Fund of State Key Laboratory of Mechanics and Control of Mechanical Structures (Nanjing University of Aeronautics and astronautics) under Grant No. 0114G01.
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Published In
Journal of Aerospace Engineering
Volume 30 • Issue 3 • May 2017
Copyright
© 2016 American Society of Civil Engineers.
History
Received: Sep 17, 2015
Accepted: Jun 29, 2016
Published online: Aug 23, 2016
Discussion open until: Jan 23, 2017
Published in print: May 1, 2017
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