Article

Cover

Title

Problems of finite element model updating of aircraft based on ground vibration test results

Authors

^1,2P.A. Lakiza, ^1,2D.A. Krasnorutskiy, ^1,2V.A. Berns, ^1,2E.P. Zhukov, ^1,2A.V. Shkoda

Organizations

¹S. A. Chaplygin Siberian Research Institute of Aviation
Novosibirsk, Russian Federation
²PJSC «UAC «Sukhoi Design Bureau»
Moscow, Russian Federation

Abstract

The paper addresses the issues occurring during updating of computational dynamic models of aircraft based on ground vibration test results. These include selection of modal testing methodology based on the analysis of ratio between forced monophase modes and eigenmodes. Structural damping properties can be identified from test results. It is worth noting that the errors in experimental determination of eigenfrequencies are significantly lower than the ones in general masses and damping coefficients. The method for updating elastic properties of finite element models is developed. The mass matrix is assumed to be accurately defined.The objective function is a weighted sum of squares of differences between experimental and calculated eigenfrequencies. The objective function is minimized iteratively. The robustness of the approach with respect to errors in ground vibration test results is investigated. The approach to model structural damping properties based on ground vibration test results is presented. The damping coefficients are computed and chosen as the target ones for each experimentally determined eigenmode. That indicates that in modal coordinates the matrix which consists of these coefficients is diagonal. In order to construct the damping matrix in physical coordinates, the Rayleigh damping model is used. The finite element models of aircraft wing and the aircraft of flying wing type have been updated.

Keywords

computational models of aircraft, ground vibration testing, finite element model updating, structural damping modeling, flying wing

References

[1] Karklje P. G., Smyslov V. I. Ground vibration testing of aircraft and reproduction of forces. Moscow: Technosphere, 2017, 156 p.

[2] Mezhin V. S., Obukhov V. V. The practice of using modal tests to verify finite element models of rocket and space hardware. Space Engineering and Technology, 2014, no. 1, vol. 4, pp. 86–91

[3] Karklje P. G., Maljutin V. A., Mamedov O. S., Popovskij V. N., Smotrov A. V., Smyslov V. I. Modern ground vibration testing methods for aeroelasticity, TsAGI Science Journal, 2012, no. 2708, 34 p.

[4] Dat R., Tretout R., Lafont M. Essais de vibration d?une structure comportaut du frottement sec. La Recherche Aerospatiale, 1975, no. 3, pp. 169–174.

[5] Smyslov V. I. Some issues of the multipoint excitation technique in the experimental study of vibrations of elastic structures. TsAGI Science Journal, 1972, vol. 3, no. 5, pp. 110–118.

[6] Heylen W., Lammens S., Sas P. Modal analysis: theory and testing. Leuven, 1998, 350 p.

[7] Berns V. A. Modal identification of dynamic systems based on monophase oscillations. Scientific Bulletin of NSTU, 2010, vol. 40, no. 3, pp. 99–109.

[8] Peres M. A., Bono R. W., Brown D. L. Practical aspects of shaker measurements for modal testing. Proceedings of International Conference on Noise and Vibration Engineering including USD 2010, Leuven, 2010, pp. 2539–2550.

[9] Brillhart R., Napolitano K., Morgan L., LeBlanc R. Advanced GVT testing of the Gulfstream G650. Sound and Vibration, 2011, no. 8, pp. 6–9.

[10] Mottershead J.E, Link M., Friswell M. I. The sensitivity method in finite element model up–dating: A tutorial. Mechanical Systems and Signal Processing, 2011, vol. 25, pp. 2275–2296.

[11] Min C.H., Hong S., Park S. Y., Park D. C. Sensitivity–based finite element model updating with natural frequencies and zero frequencies for damped beam structures. International Journal of Naval Architecture and Ocean Engineering, 2014, vol. 6 (4), pp. 904–921.

[12] Hernandez E. M., Bernal D. Iterative finite element model updating in the time domain. Mechanical Systems and Signal Processing, 2013, vol. 34, pp. 39–46.

[13] Chen L., Guo Y., Li L. Structural dynamic model updating based on multi–level weight coefficients. Applied Mathematical Modelling, 2019, vol. 71, pp. 700–711.

[14] Berns V. A. Assessment of determination accuracy of eigentones characteristics in the presence of random errors in the experimental data. Vestnik Sibsau, 2010, vol. 31, no. 5, pp. 208–212.

[15] Berns V. A. Errors in determining characteristics of natural modes at close natural frequencies. Testing. Diagnostics, 2011, vol. 153, no. 3, pp. 12–16.

[16] Berns V. A., Dolgopolov A. V., Zhukov E. P., Marinin D. A. Influence of the suspension system on the accuracy of the aircraft modal testing results. Vestnik of Samara University, 2016, vol. 15, no. 1., pp. 18–27.

[17] Krasnorutskiy D. A., Lakiza P. A., Berns V. A., Zhukov E. P. Finite Element Model Updating Method of Dynamic Systems. PNRPU Mechanics Bulletin, 2021, no. 3, pp. 84–95. DOI: 10.15593/perm.mech/2021.3.08

[18] Lakiza P. A. Korrekcija raschetnyh modelej letatel'nyh apparatov po rezul'tatam modal'nyh ispytanij [Finite element model updating of aircraft based on ground vibration test results]. Kand, Diss. Novosibirsk, 2023. 162 p.

For citing this article

Lakiza P.A., Krasnorutskiy D.A., Berns V.A., Zhukov E.P., Shkoda A.V. Problems of finite element model updating of aircraft based on ground vibration test results // Spacecrafts & Technologies, 2025, vol. 9, no. 2, pp. 87-100. doi: 10.26732/j.st.2025.2.04

This Article is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License (CC BY-NC 4.0).