On experimental determination of aircraft structures stiffness characteristics

Strength and thermal conditions of flying vehicles


Amiryants G. A.*, Malyutin V. A.**

Central Aerohydrodynamic Institute named after N.E. Zhukovsky, TsAGI, 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: amiryants@mail.ru
**e-mail: viktor.malyutin@tsagi.ru


The competitive air materiel development is impossible without permanent improvement of methods for the aircraft stiffness characteristics studies, as well as their elastically similar and “rigid” aerodynamic models. The goal of the work consists in increasing the efficiency, informativity and precision of the stiffness characteristics study.

The article presents the results of studies aimed at improving the system of the stiffness characteristics experimental determination of full-scaled air materiel objects and their aeroelastic models. It presents a brief description of some basic elements of the system, in particular, the robotic test bench for determining stiffness characteristics, multi-channel data acquisition system, and automated loading system.

The results of experimental studies using the above said technical means are presented. For example, using the automated loading system and data acquisition system, the stiffness of fastening elements of the aerodynamic model in the wind tunnel working section was determined. The measured stiffness parameters were used in the computational scheme of the model in the ARGON software package, on which basis the aerodynamic loads were computed. The robotic test bench application for stiffness characteristics determination while determining the beam stiffness characteristics, and influence coefficients matrix allowed quickly and efficiently performing the stiffness tests of the elastically scaled model frame.

Some examples of ARAMIS stereophotogrammetrical system application for measuring spatial movements are presented. The abilities of this system are illustrated by its application in the international AFLoNext project of the Seventh Framework European programme. Quickly obtained data helped to compose a quantitative representation of the mutual movements of the engine nacelle, pylon and wing compartment. Another example of the ARAMIS application system is the of displacements measurement of the high aspect ratio wing in the wind tunnel flow.

The developed and improved system is one of the main elements of a multidisciplinary approach to the design of advanced air materiel, safe in terms of aeroelasticity and strength, and perfect in weight efficiency, aerodynamic and tactical-technical characteristics.


aeroelasticity, experiment, stiffness tests, elastic deformation measurement


  1. Amir'yants G.A. Tekhnika vozdushnogo flota, 1967, no. 4, pp. 41 – 46.

  2. Amir'yants G.A. Tekhnika vozdushnogo flota, 1970, № 7, pp. 24 - 29.

  3. Pendleton E., Griffin K.E., Kehoe M.W., Perry B. A Flight Research Program for Active Aeroelastic Wing Technology, AIAA-96-1574-CP, USA, April 1996, pp. 2263 - 2273.

  4. Zink P.S., Mavris D.N., Love M.H., Karpel M. Robust Design for Aeroelastically Tailored/Active Aeroelastic Wing, 7-th AIAA/USAF/NASA/ISSMO Symposium on Multidisciplinary Analysis and Optimization, St. Louis, MO, September 2-4, 1998, AIAA-98-4781.

  5. Azarov Yu.A., Chernovolov R.A. Trudy MAI, 2017, no. 97, available at: http://trudymai.ru/eng/published.php?ID=87164

  6. Azarov Yu.A., Chernovolov R.A. Trudy MAI, 2017, no. 92, available at: http://trudymai.ru/eng/published.php?ID=77062

  7. Amir'yants G.A., Bun'kov V.G., Nabiullin E.N. Trudy TsAGI, 1968, pp. 1 – 8.

  8. Amir'yants G.A., Bun'kov V.G. Uchenye Zapiski TsAGI, 1976, vol. VII, no. 4, pp. 88 - 94.

  9. Evseev D.D., Ishmuratov F.Z., Chedrik V.V. et al. Uchenye zapiski TsAGI, 1991, vol. XXII, no. 5. pp. 89 - 101.

  10. Grossman E.P. Trudy TsAGI, 1949, 8 p.

  11. Gil'denblat I.Yu., Egorov V.V., Papkhomovskii Ya.M. Eksperimental'nye metody opredeleniya zhestkostnykh khapaktepistik samoleta i ego chastei. Rukovodstvo dlya konstruktorov (Experimental methods for determining stiffness characteristics of aircraft and its parts. Designers Guide: TsAGI Publishing Department), Moscow, Izdatelskii otdel TsAGI, 1979, vol. III, Kn. 2, no. 9, 24 p.

  12. Amir'yants G.A. Adaptivnoe krylo, Avtorskoe svidetel'stvo na izobretenie №1762488 V 64 S 3/48, 30.04.94.

  13. Amiryants G. Adaptive Selectively Deformable Structures, Proceedings of 21-th ICAS Congress, Melbourne, 1998.

  14. Amiryants G., Ishmuratov F., Malyutin V., Timokhin V. Selectively deformable structures for design of adaptive wing smart elements as part of active aeroelastic wing concept, IFASD, St-Petersburg, 2015.

  15. Trutzer M., Siegling H.-F., Betz D., Sangkohl R., Staudigel L., Krumpholz O. Fiberoptic Smart Sensing of Component Deformations in Adaptive Wings, Proceedings of 22-nd ICAS Congress, Harrogate, 2000.

  16. Amir'yants G.A., Latsoev K.F., Malyutin V.A., Mullov Yu.M., Naiko Yu.A. Stantsiya dlya opredeleniya zhestkostnykh kharakteristik konstruktsii i ikh aerodinamicheskikh/aerouprugikh modelei. Trudy Tsentral'nogo aerogidrodinamicheskogo instituta im. N.E. Zhukovskogo (Station for stiffness characteristics determining of structures and their aerodynamic/aeroelastic models. Trudy TsAGI no. 2669), Moscow, Izdatel'skii otdel TsAGI, 2005, pp. 84 - 88.

  17. Blokin-Mechtalin Yu.K., Sudakov V.A., Zalivako V.Yu., Malyutin V.A. Patent na izobretenie no. 2491507, 28.08.2013.

  18. Agarkov A.V., Grigor'ev A.V., Malyutin V.A., Naiko. Yu.A., Chizhov A.A. Eksperimental'noe issledovanie zhestkostnykh kharakteristik elementov krepleniya tsel'nopovorotnogo opereniya manevrennogo samoleta s primeneniem beskontaktnykh datchikov peremeshcheniya. Trudy TsAGI no. 2738 (Experimental study of stiffness characteristics of the maneuvering aircraft fastening elements of the whole-rotating tail employing non-contact displacement sensors. Trudy TsAGI no. 2738), Moscow, Izdatel'skii otdel TsAGI, 2014, pp. 165 - 170.

  19. Grigor'ev A.V., Malyutin V.A. Metodika raschetno-eksperimental'nogo opredeleniya koeffitsientov uprugogo vliyaniya podvesnykh agregatov letatel'nogo apparata. Trudy TsAGI no. 2738 (Computational and experimental determination method of the elastic influence coefficients of the aircraft suspended units. Trudy TsAGI no. 2738), Moscow, Izdatel'skii otdel TsAGI, 2014. Pp. 159 - 165.

  20. Pendleton, E., Flick, P., Voracek, D., Reichenbach, E., Griffin, K., Paul, D.“The X-53, A Summary of the Active Aeroelastic Wing Flight Research Program”. Paper 07-1855, Proceedings of the 48-th AIAA Structures, Structural Dynamics and Materials Conference, Honolulu, Hawaii, 2007.

  21. Amiryants G.A., Grigoriev A.V., Naiko Y.A., Paryshev S.E.. The “Active aeroelasticity” concept – the main stages and prospects of development, 30-th Congress of ICAS, Daejeon, 2016.


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