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Marc P. Mignolet

Bio: Marc P. Mignolet 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 10, co-authored 15 publications receiving 575 citations.

Papers
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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, 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, the use of intentional mistuning of bladed disks to reduce their sensitivity to unintentional random mistuning is investigated, and a two-step procedure is described to optimize the arrangement of these blades around the disk to reduce the effects of unintentional mistuning.
Abstract: The focus of the present investigation is on the use of intentional mistuning of bladed disks to reduce their sensitivity to unintentional random mistuning. The class of intentionally mistuned disks considered here is limited, for cost reasons, to arrangements of two types of blades (A and B, say). A two-step procedure is then described to optimize the arrangement of these blades around the disk to reduce the effects of unintentional mistuning. First, a pure optimization effort is undertaken to obtain the pattern(s) of the A and B blades that yields small/the smallest value of the largest amplitude of response to a given excitation in the absence of unintentional mistuning. Then, in the second step, a pattern screening technique based on a recently introduced measure of localization is used to determine which of the patterns does have a large/small sensitivity to random unintentional mistuning. In this manner, expensive Monte Carlo simulations can be eliminated. Examples of application involving both simple bladed disk models and a 17-blade industrial rotor clearly demonstrate the significant benefits of using this class of intentionally mistuned disks.

51 citations

Journal ArticleDOI
TL;DR: In this article, the authors investigated the local and global effects of mistuning on the forced response of bladed disks and found that the largest amplification due to the mistuning occurs at very strong blade-to-blade coupling levels, at contrary of a general perception, but is associated with large mistuning levels.
Abstract: The focus of the percent investigation is on the assessment and modeling of the local (spanning only a few blades) and global (encompassing the entire disk) effects of mistiming on the forced response of bladed disks. To this end, the concept of localization is first revisited and a new measure of this effect is introduced in terms of the number of blades the mistuning of which actually affects the forced response of a central blade. Using this new metric, it is demonstrated that high responding blades typically exhibit a high level of localization and that the reverse is not necessarily true. Thus, localization is not only disk dependent but also varies from blade-to-blade on the same disk. This observation is then used to validate a partial mistiming approach to the determination of the maximum amplitude of response over the entire population of disks. The results of this study indicate that the largest amplification due to the mistuning occurs at very strong blade-to-blade coupling levels, at the contrary of a general perception, but is associated with large mistuning levels. Finally, the above phenomenological observations are used to devise a modeling technique of both local and global components of mistuning. An example of application is presented that demonstrates the high accuracy of this approach through the entire blade-to-blade coupling domain.

37 citations

Proceedings ArticleDOI
04 May 2009
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. Further, 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 validated first 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 (FGM) 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.

36 citations


Cited by
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Journal ArticleDOI
TL;DR: This work reviews the recent status of methodologies and techniques related to the construction of digital twins mostly from a modeling perspective to provide a detailed coverage of the current challenges and enabling technologies along with recommendations and reflections for various stakeholders.
Abstract: Digital twin can be defined as a virtual representation of a physical asset enabled through data and simulators for real-time prediction, optimization, monitoring, controlling, and improved decision making. Recent advances in computational pipelines, multiphysics solvers, artificial intelligence, big data cybernetics, data processing and management tools bring the promise of digital twins and their impact on society closer to reality. Digital twinning is now an important and emerging trend in many applications. Also referred to as a computational megamodel, device shadow, mirrored system, avatar or a synchronized virtual prototype, there can be no doubt that a digital twin plays a transformative role not only in how we design and operate cyber-physical intelligent systems, but also in how we advance the modularity of multi-disciplinary systems to tackle fundamental barriers not addressed by the current, evolutionary modeling practices. In this work, we review the recent status of methodologies and techniques related to the construction of digital twins mostly from a modeling perspective. Our aim is to provide a detailed coverage of the current challenges and enabling technologies along with recommendations and reflections for various stakeholders.

660 citations

Journal ArticleDOI
TL;DR: The literature on reduced-order modeling, simulation, and analysis of the vibration of bladed disks found in gas-turbine engines is reviewed in this paper, where an emphasis is placed on key developments in the last decade that have enabled better prediction and understanding of the forced response of mistuned bladed disk, especially with respect to assessing and mitigating the harmful impact of mistuning on blade vibration, stress increases, and attendant high cycle fatigue.
Abstract: The literature on reduced-order modeling, simulation, and analysis of the vibration of bladed disks found in gas-turbine engines is reviewed. Applications to system identification and design are also considered. In selectively surveying the literature, an emphasis is placed on key developments in the last decade that have enabled better prediction and understanding of the forced response of mistuned bladed disks, especially with respect to assessing and mitigating the harmful impact of mistuning on blade vibration, stress increases, and attendant high cycle fatigue. Important developments and emerging directions in this research area are highlighted.

340 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: It is proved that with arbitrary small amounts of mistuning, the asymptotic behavior of the least stable closed loop eigenvalue can be improved to O(1/N) in the limit of a large number of vehicles.
Abstract: We consider a decentralized bidirectional control of a platoon of N identical vehicles moving in a straight line. The control objective is for each vehicle to maintain a constant velocity and inter-vehicular separation using only the local information from itself and its two nearest neighbors. Each vehicle is modeled as a double integrator. To aid the analysis, we use continuous approximation to derive a partial differential equation (PDE) approximation of the discrete platoon dynamics. The PDE model is used to explain the progressive loss of closed-loop stability with increasing number of vehicles, and to devise ways to combat this loss of stability. If every vehicle uses the same controller, we show that the least stable closed-loop eigenvalue approaches zero as O(1/N2) in the limit of a large number (N) of vehicles. We then show how to ameliorate this loss of stability by small amounts of "mistuning", i.e., changing the controller gains from their nominal values. We prove that with arbitrary small amounts of mistuning, the asymptotic behavior of the least stable closed loop eigenvalue can be improved to O(1/N). All the conclusions drawn from analysis of the PDE model are corroborated via numerical calculations of the state-space platoon model.

281 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