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Hybrid calibration of aeronautical structures instrumented with strain-gages for load prediction

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Abstract

This paper presents a hybrid methodology for loads measurement on aircraft structures. It is based on both experimental data from the actual structure and numerical prediction from finite element models. The model is firstly adjusted based on a reduced amount of experimental data, so it can predict the structure load response in terms of simulated strain-gage bridge responses. Once adjusted, the model is loaded at several points while gathering the corresponding simulated strains responses. Based on regression analysis, the calibration coefficients are established to be used for in-flight load measurements. Comparing with the conventional calibration method, purely based on experimental tests, the new calibration methodology requires less calibration load cases, which makes the test setup also simpler. The new calibration method is applied to a horizontal empennage from a commercial aircraft, for which the conventional calibration was previously conducted, providing therefore the reference for both flight and ground test comparisons. A good correlation was found between the loads estimated by the conventional calibration and present method. Nowadays, virtual tests are getting importance for validation and demonstration purposes, and this work is adherent with this tendency.

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References

  1. Skopinski TH, Aiken WS, Huston WB (1954) Calibration of strain-gage installations in airplane structures for measurements of flight loads. Report 1178, NACA: USA

  2. Jenkins JM, Deangelis VM (1997) A summary of numerous strain-gage load calibrations on aircraft wings and tails in a technology format. Edwards: NASA

  3. Jebacek I (2010) Measurement of the strain and bending moment on the wing of an aircraft and using of these findings for fatigue test. ICAS, Nice, France 2010.

  4. Jebacek I, HORAK M (2012) Possibilities and methods of in-flight loading measurement. Aviation, 16(2): 47–50

  5. Miller E, Pena F, Jordan A, Hudson L (2019) Evaluation of wing load calibration and sensing methods using conventional strain gages and a fiber optic sensing system installed on a straight tapered wing. https://doi.org/10.2514/6.2019-0227

  6. Swiech L (2020) Calibration of a load measurement system for an unmanned aircraft composite wing based on fibre bragg gratings and electrical strain gauges. Aerospace. 7(3)

  7. Verri AA, Barros J, Bussamra FLS, Silvestre FJ, Moreira FJO, Guimarães neto, AB, Cesnik CE, Martins JS (2018) Strain gages full bridge inside composite layers targeting wing shape feedback for flight control laws. 21st Congress of the international Council of the Aeronautical Sciences. September

  8. Davis MC, Saltzman JA (2000) In-flight wing pressure distributions for the NASA F/A-18A high alpha research vehicle. Edwards: NASA

  9. Pyle JS (1965) Flight Pressure distributions on the vertical stabilizers and speed brakes of the X-15 airplane at Mach numbers from 1 to 6. Edwards: NASA

  10. Juretschke IR, Oliveira BV, Santolaya RB (2014) Loads model flight test validation by means of innovative, photogrammetry based, deformation measurement technique. In: 29th Congress of the International Council of the Aeronautical Sciences. St. Petersburg, Russia, 7–12

  11. Burner AW, Lokos WA, Barrows DA (1997) Aeroelastic deformation: adaptation of wind tunnel measurement concepts to full-scale vehicle flight testing. Edwards: NASA

  12. LI, L G (2014) Full-field wing deformation measurement scheme for in-flight cantilever monoplane based on 3D digital image correlation. Institute of Physics (IPO Publishing), 25 6 (2014)

  13. Veerman HPJ, Kannemans H, Jentink HW (2009) High accuracy in-flight wing deformation measurements based on optical correlation technique. National Aerospace Laboratory NLR, Amsterdam

    Google Scholar 

  14. Viana, MV (2015) sensor calibration for calculation of loads on a flexible aircraft. IFASD, St. Petersburg, Russia

  15. Wada D, Igawa H, Tamayama M, Murayama H (2019) Real-time stress concentration monitoring of aircraft structure during flights using optical fiber distributed sensor with high spatial resolution. ICAF 2019, Krakow, Poland, 2019.

  16. Wada D, Igawa H, Tamayama M, Shiotsubo K (2019) Flight demonstration of aircraft fuselage and bulkhead monitoring using optical fiber distributed sensing system. Smart Mater Struct , 27(2)

  17. Wada D, Igawa H, Tamayama M, Murayama H (2019) Flight demonstration of aircraft wing monitoring using optical fiber distributed sensing system. Smart Mater Struct, 28: 5

  18. Wada D, Tamayama M (2019) Wing load and angle of attack identification by integrating optical fiber sensing and neural network approach in wind tunnel test. Appl Sci 9: 1461

  19. Kim D, Marciniak M (2001) A methodology to predict the empennage in-flight loads of a general aviation aircraft using backpropagation neural networks. Embry-Riddle Aeronautical University, FAA sponsoring

    Google Scholar 

  20. Guimaraes TAM, Castro SGP, Cesnik CES, Rade DA (2019) Supersonic flutter and buckling optimization of tow-steered composite plates. AIAA J 57: 1

  21. Papa U, Russo S, Laboblia A., Core GD, Iannuzzo G (2017) Health structure monitoring for the design of an innovative UAS fixed wing through inverse finite element method (iFEM). Aerospace Sci Technol, 9: 1

  22. ESPOSITO M, GHERLONE M, (2020) Composite wing box deformed-shape reconstruction based on measured strains: Optimization and comparison of existing approaches. Aerospace Sci Technol, 99: 1

  23. Nakamura T, Igawa H, Kanda A, (2012) Inverse identification of continuously distributed loads using strain data. Aerospace Sci Technol, 23: 75

  24. Chisholm ST, Castro JF, Chapman BD, et al (2019) Smarter testing through simulation for efficient design and attainment of regulatory compliance. ICAF 2019, Krakow, Poland

  25. MSC. nastran 2013 - Quick reference guide. MSC, 2013.

  26. Jenkins J, Kuhl AE, Carter AL (1977) The use of a simplified structural model as an aid in the strain gage calibration of a complex wing, NASA TM 56046, Edwards: NASA, 1977.

  27. Megson, THG (2017) Aircraft structures for engineering students, sixth edition, Elsevier, Oxford, United Kingdom, 28 p

  28. Verri AA, Bussamra FLS, Morais KC et al. (2020) Static loads evaluation in a flexible aircraft using high-fidelity fluid-structure iteration tool (E2-FSI): extended version. J Brazilian Soc Mech Sci Eng

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Authors and Affiliations

  1. EMBRAER, Empresa Brasileira de Aeronáutica S.A. – Av, Brigadeiro Faria Lima, 2170, Putim, São José dos Campos, SP, 12227-901, Brazil

    Jason de Barros

  2. ITA, Instituto Tecnológico de Aeronáutica - Pç. Mal. Ed. Gomes, 50, V. Acácias, São José dos Campos, SP, 12228-900, Brazil

    Flávio Luiz de Silva Bussamra

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  1. Jason de Barros
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  2. Flávio Luiz de Silva Bussamra
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Correspondence to Jason de Barros.

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Technical Editor: Flávio Silvestre.

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de Barros, J., de Silva Bussamra, F.L. Hybrid calibration of aeronautical structures instrumented with strain-gages for load prediction. J Braz. Soc. Mech. Sci. Eng. 43, 571 (2021). https://doi.org/10.1007/s40430-021-03176-1

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  • DOI: https://doi.org/10.1007/s40430-021-03176-1

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