Validation of designing and manufacturing procedures of aircraft dynamically similar models with polymer composite materials application

Аuthors

Chernovolov R. A.^1*, Garifullin M. F.¹, Kozlov S. I.²

1. National Research Center "Zhukovsky Institut", 1, Zhukovsky str, Zhukovsky, Moscow Region, 140180, Russia
2. Central Aerohydrodynamic Institute named after N.E. Zhukovsky (TsAGI), 1, Zhukovsky str., Zhukovsky, Moscow Region, 140180, Russia

*e-mail: r.chernovolov@gmail.com

Abstract

Drained dynamically scaled models have been designed for studying unsteady aerodynamic characteristics in wind tunnels. At present, such models testing is of the greatest interest both from the viewpoint of their application for studying safety of the prospective aircraft from the flutter and buffeting, and for verification of calculated aerodynamics with account for the structure elasticity.

The article presents an algorithm for design parameters selecting of a dynamically scaled model and its tuning by test results. The proposed procedure for implementing this algorithm is demonstrated on a simple example (a beam of constant cross section, reinforced by layers of a polymer composite material). Issues of technology for design and manufacturing of a typical element of the dynamically scaled aircraft model applying polymer composite materials are considered. Frequency tests conducting technique is presented, as well as the results of computational and experimental studies of the shapes and frequencies of natural oscillations with account for the additional loads placement. Computed shapes and frequencies of natural oscillations obtained by the finite element method using several successively condensed grids are given. The research findings comparison indicates that calculated values of the cross-section bending stiffness obtained using theoretical relationships and characteristics of the material, accounting for epy specifics of dynamically similar model manufacturing technology, are close enough to those obtained by the experiments at static loading and resonant tests conducting. Setting-up such model does not require special efforts. It allows considering, that the accepted calculating and design technique ensures obtaining required characteristics of the dynamically similar model.

Keywords:

dynamically scale model, polymer composite materials, oscillation shapes and frequencies

References

1. Kuz’mina S.I. Trudy TsAGI, issue 2738, Moscow, Izdatel’skii otdel TsAGI, 2013, pp. 189-204.

2. Bisplinghoff R.L., Ashley H., Halfman R.L. Aeroelasticity. Dover Publications, Inc., Mineola, N.Y., 1996, 880 p.

3. Lyshchinskii V.V. Modelirovanie flattera v aerodinamicheskikh trubakh (Flutter simulation in wind tunnels), Moscow, Fizmatlit, 2009, 80 p.

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

5. Chernovolov R.A., Yanin V.V. Aviatsionnaya promyshlennost’, 2016, no. 3, pp. 9-14.

6. Azarov Yu.A., Bruskova E.V., Karkle P.G., Chernovolov R.A. Patent RU2578915 C1, 27.03.2016.

7. Garrick I.E., Reed W.H. Historical development of aircraft flutter. Journal of Aircraft, 1981, vol. 18, no. 11, pp. 897-912. DOI: 10.2514/3.57579

8. Kehoe M.W. A Historical Overview of Flight Flutter Testing. National Aeronautics and Space Administration (NASA) Technical Memorandum 4720. October 1995, 20 p.

9. Stodieck O., Francois G., Heathcote D., Zympeloudis E., Kim B.C., Rhead A.T., Cleaver D., Cooper J.E. Experimental validation of tow-streered composite wings for aeroelastic design. 17th International Forum on Aeroelasticity and Structural Dynamics (IFASD 2017). 25-28 June 2017, Como – Italy, pp. 518-533.

10. Ringertz U., Eller D., Keller D.F., Silva W.A. Design and testing of a full span aeroelastic wind tunnel model. 17th International Forum on Aeroelasticity and Structural Dynamics (IFASD 2017). 25-28 June 2017, Como – Italy, pp. 1880-1899.

11. Pankonien A.M., Reich G.W., Hardin J.O., Bhagat N., Berrigan J.D. From model to manufacture: additive aeroelastic morphing testbeds. 17th International Forum on Aeroelasticity and Structural Dynamics (IFASD 2017). 25-28 June 2017, Como – Italy, pp. 1662-1676.

12. Geeraert A., Lepage A., Stephani P., Feldmann D., Haberli W. Wind tunnel flutter tests of a u-tail configuration – Part 1: Model design and testing. 17th International Forum on Aeroelasticity and Structural Dynamics (IFASD 2017). 25-28 June 2017, Como – Italy, pp. 814-833.

13. Endogur A.I., Kravtsov V.A. Trudy MAI, 2015, no. 81. URL: http://trudymai.ru/eng/published.php?ID=57755

14. Endogur A.I., Kravtsov V.A., Soloshenko V.N. Trudy MAI, 2014, no. 72. URL: http://trudymai.ru/eng/published.php?ID=47572

15. Vasil’ev V.V. Mekhanika konstruktsii iz kompozitsionnykh materialov (Mechanics of structures from composite materials), Moscow, Mashinostroenie, 1988, 272 p.

16. Polilov A.N. Etyudy po mekhanike kompozitov (Essays on composites mechanics), Moscow, Fizmatlit, 2015, 320 p.

17. Vasil’ev V.V., Protasov V.D., Bolotin V.V. i dr. Kompozitsionnye materialy. Spravochnik (Composite materials. Handbook), Moscow, Mashinostroenie, 1990, 512 p.

18. Kyaw A.L., Artemev A.V., Rabinskii L.N., Afanas’ev A.V., Semenov N.A., Solyaev Yu.O. Monolayer properties identification in carbon composite with nano-modified matrix. Aerospace MAI Journal, 2017, vol. 24, no. 2, pp. 197-208.

19. Bychkov A.N., Fetisov G.P., Kydralieva K.A., Soko­lov E.A., Dzhardimalieva G.I. Nanocomposite materials based on metallic nanoparticles and thermoplastic polymer matrices: production and properties. Aerospace MAI Journal, 2017, vol. 24, no. 2, pp. 209-222.

20. Popov B.G. Raschet mnogosloinykh konstruktsii variatsionno-matrichnymi metodami (Multilayer structures calculation by variation matrix methods), Moscow, MGTU, 1993, 294 p.

21. Tuktarov S.A., Chedrik V.V. Uchenye zapiski TsAGI, 2015, vol. 46, no. 3, pp. 70-84.

22. Weisshaar T.A., Foist B.L. Vibration Tailoring of Advanced Composite Lifting Surfaces. Journal of Aircraft, 1985, vol. 22, no. 2, pp. 141 – 147. DOI: 10.2514/3.45098