A review of indirect/non-intrusive reduced order modeling of nonlinear geometric structures

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

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Aeroelastic and Aerothermoelastic Analysis in Hypersonic Flow: Past, Present, and Future

Christian Soize presents the main concepts, formulations, and recent advances in the use of a mathematical-mechanical modeling process to predict the responses of a real structural system in its environment.

Stochastic Models of Uncertainties in Computational Mechanics

Nonintrusive Structural Dynamic Reduced Order Modeling for Large Deformations: Enhancements for Complex Structures

The impact of flow induced loads on snap-through behavior of acoustically excited, thermally buckled panels

Quantifying effects of system-wide uncertainties (i.e., affecting structural, piezoelectric, and/or electrical components) in the analysis and design of piezoelectric vibration energy harve...

Uncertainty Analysis of Piezoelectric Vibration Energy Harvesters Using a Finite Element Level-Based Maximum Entropy Approach

Nonlinear geometric reduced order model for the response of a beam with a piezoelectric actuator

Toward a systematic construction of the basis for nonlinear geometric reduced order models

This paper focuses on the blade peak stress prediction from limited strain gage/tip-timing measurements when multiple vibratory modes are present and in the absence of a validated finite element model. The current protocol assumes that only one mode is present and only provides upper and lower bound estimates of the blade peak stress when multiple modes are important. Two candidate approaches are proposed here to resolve this situation; they are based on test measurements and data provided by the manufacturer/basic blade geometry information, e.g. aspect ratio, taper, thickness, twist, stagger, referred to as “blade descriptors”. The first approach, referred to as the finite element model reconstruction approach, focuses on reconstructing a most likely finite element model of the blade given all available blade information. In the second approach, referred to as the knowledge-based approach, a database of finite element models corresponding to a broad set of blade descriptors is initially established then queried for the application considered. The formulation of these approaches and their successful preliminary validation is presented in details.

X. Q. Wang

Papers

Uncertainty Analysis of Piezoelectric Vibration Energy Harvesters Using a Finite Element Level-Based Maximum Entropy Approach

Nonlinear geometric reduced order model for the response of a beam with a piezoelectric actuator

Toward a systematic construction of the basis for nonlinear geometric reduced order models

Blade stress estimation during multiple vibratory modes

Structural uncertainty modeling for nonlinear geometric response using nonintrusive reduced order models