Updating a finite element based structural model of a small flexible aircraft

Gupta, Abhineet; Moreno, Claudia P.; Pfifer, Harald; Taylor, Brian; Balas, Gary J.

doi:10.2514/6.2015-0903

Cited by 22 publications

(20 citation statements)

References 14 publications

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“…Another application example can be found in various references. [12][13][14][15][16] EV-55M is twin turboprop utility aircraft for 9-13 passengers with a total length of 14.35 m, the wingspan of 16.10 m, and a maximal take-off weight of 4600 kg. The aircraft was developed by Evektor, Kunovice company.…”

Section: Application To Ev-55m Aircraft Structurementioning

confidence: 99%

Updating of finite element model of aircraft structure according results of ground vibration test

Cecrdle

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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This paper deals with updating of the aircraft structure finite element (FE) model according ground vibration test (GVT) results. Paper describes possible approaches of flutter analysis as regards to the incorporation of GVT results including:(1) the direct usage of GVT results and (2) updating of analytical FE model. Then the theoretical background of the model updating methods including Bayesian parameter estimation and more generic optimization using powerful nonlinear gradient-based methods are given. Finally, the methodology of an aircraft structure FE model updating is described. The practical application of the procedure is documented on the EV-55M turboprop utility aircraft example. Selected results are shown, evaluated and the conclusions are formulated.

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Section: Application To Ev-55m Aircraft Structurementioning

confidence: 99%

Updating of finite element model of aircraft structure according results of ground vibration test

Cecrdle

2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The structural model is developed using a finite element method which consists of linear Euler beam elements. 9,10 The beams are interconnected as shown in Fig. 3.…”

Section: B Structural Dynamicsmentioning

confidence: 99%

“…The Unmanned Aerial Vehicles (UAV) research group at the University of Minnesota carries out extensive research in the field of aeroservoelastic systems. Theoretical research in system modeling, 3, 4 model reduction 5,6 and control design 7,8 is supplemented by experimental work in ground vibration tests, 9,10 flight tests 11 and system identification. 12,13 The group maintains a well equipped UAV laboratory for experimental research and flight tests.…”

Section: Introductionmentioning

confidence: 99%

Sensitivity of Robust Flutter Boundary to Model Uncertainties in Aeroservoelastic Systems - Invited

Kotikalpudi

Pfifer

Seiler

2016

AIAA Atmospheric Flight Mechanics Conference

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The dynamics of a flexible air vehicle are typically described using an aeroservoelastic model which accounts for interaction between aerodynamics, structural dynamics, rigid body dynamics and control laws. These subsystems are individually modeled using a combination of theory and experimental data from various ground tests. For instance, the structural dynamics model can be obtained using a finite element method which is then updated using data from ground vibration tests. Similarly, an aerodynamic model can be obtained from linear panel methods or computational fluid dynamics and updated using data from wind tunnel tests. In all cases, the models obtained for the subsystems have a degree of uncertainty owing to inherent assumptions in the theory and errors in experimental data. By suitably modeling these uncertainties, a robust stability analysis may be carried out to obtain a robust flutter boundary. In this paper, we examine the affects of bounds on various uncertainties on the resulting robust flutter boundary. This analysis helps us deduce the subsystems most important for a good flutter prediction.

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“…Theoretical research is conducted on topics varying from modeling, 17, 18 model reduction 19,20 and control design. 21,6 Experimental work 13,14,22 and flight tests are also conducted to support and validate the theoretical research. Researchers at the UAV lab are working as part of a large industry/academic team for a NASA grant entitled 'Performance Adaptive Aeroelastic Wing' (PAAW).…”

Section: Introductionmentioning

confidence: 99%

Ground Vibration Tests on a Flexible Flying Wing Aircraft - Invited

Gupta

Seiler

Danowsky

2016

AIAA Atmospheric Flight Mechanics Conference

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This paper presents ground vibration test results for a small flexible flying wing aircraft. The aircraft is suspended from a spring and an input force is applied via an electrodynamic shaker. Accelerometer measurements are obtained at twenty points along the aircraft wings. This measured force and acceleration data is post-processed to identify modal frequencies and mode shapes using two different methods. The effect of small changes in the experimental procedure on the identified modal parameters is discussed. The tests were performed on a series of flexible aircraft that were built to study flutter and other aeroelastic phenomena.

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Updating a finite element based structural model of a small flexible aircraft

Cited by 22 publications

References 14 publications

Updating of finite element model of aircraft structure according results of ground vibration test

Updating of finite element model of aircraft structure according results of ground vibration test

Sensitivity of Robust Flutter Boundary to Model Uncertainties in Aeroservoelastic Systems - Invited

Ground Vibration Tests on a Flexible Flying Wing Aircraft - Invited

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