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Xiaoquan Wang

Bio: Xiaoquan Wang is an academic researcher from Arizona State University. The author has contributed to research in topics: Finite element method & Nonlinear system. The author has an hindex of 18, co-authored 57 publications receiving 860 citations. Previous affiliations of Xiaoquan Wang include Hong Kong Polytechnic University.


Papers
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Journal ArticleDOI
TL;DR: In this article, a non-linear structural dynamic reduced-order model for aircraft panels is proposed, with particular emphasis on aircraft panels, and the model is validated for isotropic/symmetric composite structures and then extended to asymmetric and functionally graded ones.
Abstract: The focus of this investigation is on the development and validation of non-linear structural dynamic reduced order models of structures undergoing large deformations, with particular emphasis on aircraft panels. Significant efforts are devoted to the formulation and assessment of “dual modes” which when combined with the linear transverse modes form an excellent basis for the representation of the displacement and stress fields in the reduced order model. This task is first successfully achieved for isotropic/symmetric composite structures and then extended to asymmetric and functionally graded ones. Examples of application are presented that demonstrate the high accuracy of the proposed reduced order models as compared to full finite element preditions, even with a small number of modes.

74 citations

Journal ArticleDOI
TL;DR: In this article, a non-linear fluid force model for a freely vibrating cylinder in a cross flow was developed based on an iterative process and the modal analysis approach, which can be evaluated from measured vibration data with the help of the auto-regressive moving averaging (ARMA) technique.

66 citations

Journal ArticleDOI
TL;DR: In this article, the authors developed and validated a reduced-order model for the geometrically nonlinear response and temperature of heated structures based on a modal-type expansion of both displacements and temperatures in the undeformed, unheated configuration.
Abstract: The focus of this investigation is on the development and validation of thermoelastic reduced-order models for the geometrically nonlinear response and temperature of heated structures. The reduced-order modeling approach is based on a modal-type expansion of both displacements and temperatures in the undeformed, unheated configuration. A set of coupled nonlinear differential equations governing the time-varying generalized coordinates of the response and temperature expansion are derived from finite thermoelasticity using a Galerkin approach. Furthermore, the selection of the basis functions to be used in these reduced-order models is discussed, and the numerical evaluation of the model coefficients is addressed. This approach is first validated on an isotropic beam subjected to both thermal effects and external loads. The thermal effects are large enough to induce a significant buckling of the panel, while the time-varying loads lead to snap-throughs ranging in frequency from infrequent to continuous. Validation to a functionally graded material panel in similar conditions is then performed. In both cases, the reduced-order modeling predicted temperatures and responses are found to very closely match their full finite element counterparts.

57 citations

Proceedings ArticleDOI
04 May 2009
TL;DR: In this article, structural dynamic reduced order models for the geometrically nonlinear response of flat cantilevered structures, e.g. beams and plates, were developed and validated.
Abstract: The focus of this investigation is on the development and validation of structural dynamic reduced order models for the geometrically nonlinear response of flat cantilevered structures, e.g. beams and plates. The specificities of cantilevered structures, as compared to those supported all around, are first highlighted. On this basis, extensions of existing reduced order modeling strategies are presented which provide a complete representation of the structural response, i.e., including both transverse and inplane displacement fields. Next, this methodology is successfully applied, first to a simple beam model and then to a flat wing both of which subjected to transverse loads. Finally, the response of a beam under combined transverse and inplane loads as well as its postbuckling behavior are also shown to be also accurately predicted by the reduced order model.

54 citations


Cited by
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Journal ArticleDOI
TL;DR: A review of mathematical models used to investigate vortex-induced vibration (VIV) of circular cylinders is given in this article, with a focus on single-degree-of-freedom (SFOF) models.

602 citations

Journal ArticleDOI
TL;DR: In this article, a unified approach for analyzing the static and dynamic behaviors of functionally graded beams (FGB) with the rotary inertia and shear deformation included is presented, where all material properties are arbitrary functions along the beam thickness.

450 citations

Journal ArticleDOI
TL;DR: A review of the progress made during the past decade on vortex-induced vibration (VIV) of long slender cylindrical structures is given in this article, where a brief outline is given of numerical methods used in predicting the response of a long slender cylinder undergoing VIV.

294 citations

Journal ArticleDOI
TL;DR: In this article, a review of reduced order modeling techniques for geometrically nonlinear structures, more specifically those techniques that are applicable to structural models constructed using commercial finite element software, is presented.

286 citations

Journal ArticleDOI
TL;DR: In this article, it is shown that the body, surface panels, and aerodynamic control surfaces are flexible due to minimum-weight restrictions for hypersonic vehicle configurations, and that these flexible body designs will consist of long, slender lifting body designs.
Abstract: H YPERSONIC flight began in February 1949 when a WAC Corporal rocket was ignited from a U.S.-captured V-2 rocket [1]. In the six decades since this milestone, there have been significant investments in the development of hypersonic vehicle technologies. The NASA X-15 rocket plane in the early 1960s represents early research toward this goal [2,3]. After a lull in activity, the modern era of hypersonic research started in the mid-1980s with the National Aerospace Plane (NASP) program [4], aimed at developing a single-stage-to-orbit reusable launch vehicle (RLV) that used conventional runways. However, it was canceled due mainly to design requirements that exceeded the state of the art [1,5]. A more recent RLV project, the VentureStar program, failed during structural tests, again for lack of the required technology [5]. Despite these unsuccessful programs, the continued need for a low-cost RLV, as well as the desire of the U.S. Air Force (USAF) for unmanned hypersonic vehicles, has reinvigorated hypersonic flight research. An emergence of recent and current research programs [6] demonstrate this renewed interest. Consider, for example, the NASA Hyper-X experimental vehicle program [7], the University of Queensland HyShot program [8], the NASA Fundamental Aeronautics Hypersonics Project [9], the joint U.S. Defense Advanced Research Projects Administration (DARPA)/USAF Force Application andLaunch fromContinentalUnited States (FALCON) program [10], the X-51 Single Engine Demonstrator [11,12], the joint USAF Research Laboratory (AFRL)/Australian Defence Science and Technology Organisation Hypersonic International Flight Research Experimentation project [13], and ongoing basic hypersonic research at the AFRL (e.g., [14–20]). The conditions encountered in hypersonic flows, combined with the need to design hypersonic vehicles, have motivated research in the areas of hypersonic aeroelasticity and aerothermoelasticity. It is evident from Fig. 1 that hypersonic vehicle configurations will consist of long, slender lifting body designs. In general, the body, surface panels, and aerodynamic control surfaces are flexible due to minimum-weight restrictions. Furthermore, as shown in Fig. 2, these

257 citations