Advances in aircraft and spacecraft science

  • 제6권2호
  • /
  • Pages.117-144
  • /
  • 2019
  • /
  • 2287-528X(pISSN)
  • /
  • 2287-5271(eISSN)
테크노프레스 (Techno-Press)
권호 표지
DOI QR코드

DOI QR Code

Static and dynamic characterization of a flexible scaled joined-wing flight test demonstrator

  • 투고 : 2018.07.31
  • 심사 : 2018.12.09
  • 발행 : 2019.03.25
⟨ 이전 논문 다음 논문 ⟩

초록

High Altitude and Long Endurance (HALE) aircraft are capable of providing intelligence, surveillance and reconnaissance (ISR) capabilities over vast geographic areas when equipped with advanced sensor packages. As their use becomes more widespread, the demand for additional range, endurance and payload capability will increase and designers are exploring non-conventional configurations to meet the increasing demands. One such configuration is the joined-wing concept. A joined-wing aircraft is one that typically connects a front and aft wings in a diamond shaped planform. One such example is the Boeing SensorCraft configuration. While the joined-wing configuration offers potential benefits regarding aerodynamic efficiency, structural weight, and sensing capabilities, structural design requires careful consideration of elastic buckling resulting from the aft wing supporting, in compression, part of the forward wing structural loading. It has been shown already that this is a nonlinear phenomenon, involving geometric nonlinearities and follower forces that tend to flatten the entire configuration, leading to structural overload due to the loss of the aft wing's ability to support the forward wing load. Severe gusts are likely to be the critical design condition, with flight control system interaction in the form of Gust Load Alleviation (GLA) playing a key role in minimizing the structural loads. The University of Victoria Center for Aerospace Research (UVic-CfAR) has built a 3-meter span scaled and flexible wing UAV based on the Boeing SensorCraft design. The goal is to validate the nonlinear structural behavior in flight. The main objective of this research work is to perform Ground Vibration Tests (GVT) to characterize the dynamic properties of the scaled flight vehicle. Results from the experimental tests are used to characterize the modal dynamics of the aircraft, and to validate the numerical models. The GVT results are an important step towards a safe flight test program.

키워드

참고문헌

  1. Adams, B.J. (2007), "Structural stability of a Joined-Wing Sensorcraft", M.Sc. Thesis, Air Force Institute of Technology, Wright-Patterson Air Force Base.
  2. Almeida, F. (2017), "Design of a ground static load test for a 3m flexible joined wing Sensorcraft", M.Sc. Thesis, Instituto Superior Tecnico, Lisbon.
  3. Blair, M. and Canfield, R. (2002), "A joined-wing structural weight modeling study", 43rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Denver, U.S.A., April.
  4. Blair, M., Canfield, R. and Roberts, R. (2005), "Joined-Wing aeroelastic design with geometric nonlinearity", J. Aircraft, 42(4), 832-848. https://doi.org/10.2514/1.2199
  5. Blair, M., Garmann, D., Canfield, R., Bond, V., Pereira, P. and Suleman, A. (2007), "Non-linear aeroelastic scaling of a joined-wing concept", 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Honolulu, Hawaii, April.
  6. Bond, V., Canfield, R., Cooper, J. and Blair, M. (2012), "Experimental nonlinear static deflections of a subscale joined wing", J. Aircraft, 49(1), 329-333. https://doi.org/10.2514/1.C031423
  7. Bond, V., Canfield, R., Cooper, J. and Blair, M. (2008), "Scaling for a static nonlinear response of a joinedwing aircraft", 12th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference, Multidisciplinary Analysis Optimization Conferences, Victoria, Canada, September.
  8. Bond, V., Canfield, R., Matos, M., Suleman, A. and Blair, M. (2007), "Wind tunnel testing of a twisted wing for longitudinal control in a joined-wing aircraft", 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Honolulu, Hawaii, April.
  9. Bond, V., Canfield, R., Matos, M., Suleman, A. and Blair, M. (2010), "Joined-wing wind-tunnel test for longitudinal control via aft wing twist", J. Aircraft, 47(5), 1481-1489. https://doi.org/10.2514/1.41140
  10. Boston, J., Swenson, E., Kunz, D., Yu, W. and Blair, M. (2011), "Experiments with geometric nonlinear coupling for analytical validation", J. Aircraft, 48(4), 1136-1146. https://doi.org/10.2514/1.C031033
  11. Brandt, A. (2010), Noise and Vibration Analysis: Signal Analysis and Experimental Procedures, Wiley, West Sussex, United Kingdom.
  12. Cavallaro, R. and Demasi, L. (2016), "Challenges, ideas, and innovations of joined-wing configurations: A concept from the past, an opportunity for the future", Progress Aerosp. Sci., 87, 1-93. https://doi.org/10.1016/j.paerosci.2016.07.002
  13. Cavallaro, R., Demasi, L. and Passariello, A. (2014), "Nonlinear analysis of PrandtlPlane joined wings: Effects of anisotropy", AIAA J., 52(5), 964-980. https://doi.org/10.2514/1.J052242
  14. Cavallaro, R., Demasi, L., Bertuccelli, F. and Benson, D.J. (2015a), "Risks of linear design of Joined Wings: Nonlinear dynamic perspective in the presence of follower forces", CEAS Aeronautical J., 6(2), 161-180. https://doi.org/10.1007/s13272-014-0136-x
  15. Cavallaro, R., Iannelli, A., Demasi, L. and Razon, A. (2015b), "Phenomenology of nonlinear aeroelastic responses of highly deformable joined wings", Adv. Aircraft Spacecraft Sci., 2(2), 125-168. https://doi.org/10.12989/aas.2015.2.2.125
  16. Collins, J.D., Hart, G.C., Hasselman, T.K. and Kennedy, B. (1974), "Statistical identification of structures", AIAA J., 12(2), 185-190. https://doi.org/10.2514/3.49190
  17. Demasi, L., Cavallaro, R. and Bertuccelli, F. (2015), "Post-Critical analysis of Joined Wings: The concept of snap-divergence as a characterization of the instability", J. Fluids Struct., 54(1), 701-718. https://doi.org/10.1016/j.jfluidstructs.2015.01.009
  18. Demasi, L., Dipace, A., Monegato, G. and Cavallaro, R. (2014), "Invariant formulation for the minimum induced drag conditions of nonplanar wing systems", AIAA J., 52(10), 2223-2240. https://doi.org/10.2514/1.J052837
  19. Dhandole, S.D. and Modak, S. (2009), "Simulated studies in FE model updating with application to vibroacoustic analysis of cavities", Proceedings of the Third International Conference on Integrity, Reliability and Failure, Porto, Portugal, July.
  20. Goge, D., Boswald, M., Fullekrug, U. and Lubrina, P. (2007), "Ground Vibration Testing of Large Aircraft - State-of-the-art and future perspectives", IMAC XXV: A Conference and Exposition on Structural Dynamics, Orlando, U.S.A., February.
  21. Heeg, J. and Morelli, E. (2011), "Evaluation of simultaneous-multisine excitation of the joined wing SensorCraft aeroelastic wind tunnel model", 52nd AIAA/ ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Denver, U.S.A., April.
  22. Kerschen, G., Peeters, M., Golinval, J.C. and Vakakis, A.F. (2009), "Nonlinear normal modes, Part I: A useful framework for the structural dynamicist", Mech. Syst. Signal Processing, 23(1), 170-194. https://doi.org/10.1016/j.ymssp.2008.04.002
  23. Kerschen, G., Peeters, M. and Golinval, J.C. (2013). "Nonlinear modal analysis of a full-scale aircraft", J. Aircraft, 50(5), 1409-1419. https://doi.org/10.2514/1.C031918
  24. Kim, Y. I., Park, G.J., Kolonay, R.M., Blair, M. and Canfield, R.A. (2008), "Nonlinear response structural optimization of a joined wing using equivalent loads", AIAA J., 46(11), 2703-2713. https://doi.org/10.2514/1.33428
  25. Kuether, R.J. and Allen, M.S. (2014), "A numerical approach to directly compute nonlinear normal modes of geometrically nonlinear finite element models", Mech. Syst. Signal Processing, 46(1), 1-15. https://doi.org/10.1016/j.ymssp.2013.12.010
  26. Kulhman, J. and Ku, T. (1982), "Numerical optimization techniques for bound circulation distribution for minimum induced drag of non-planar wings: Computer program documentation", NASA Contractor Report 3458, Langley Research Center, U.S.A.
  27. Lacarbonara, W. (2013), Nonlinear Structural Mechanics, Springer, New York, NY, U.S.A.
  28. Letcher, J. (1972), "V-wings and diamond-ring wings of minimum induced drag", J. Aircraft, 6(1), 605-607. https://doi.org/10.2514/3.59045
  29. Lin, R.M. and Ewins, D.J. (1990), "Model updating using FRF data", Proceedings of the 15th International Modal Analysis Seminar, Leuven, Belgium, September.
  30. Lubrina, P., Giclais, S., Stephan, C., Boeswald, M., Govers, Y. and Botargues, N. (2014), "AIRBUS A350 XWB GVT - State of the art techniques to perform a faster and better GVT Campaign", IMAC 2014, Orlando, U.S.A., February.
  31. Lucia, D. (2005), "The Sensorcraft configurations: A non-lineara eroservoelastic challenge for aviation", 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Austin, U.S.A., April.
  32. Peeters, M. (2010), "Theoretical an experimental modal analysis of nonlinear vibrating structures using nonlinear normal modes", Ph.D. Dissertation, University of Liege, Liege.
  33. Peeters, B., Hendricx, W., Debille, J. and Climent, H. (2009b), "Modern solutions for ground vibration testing of large aircraft", Sound Vib., 43(1), 8.
  34. Peeters, M., Kerschen, G. and Golinval, J.C. (2011a), "Dynamic testing of nonlinear vibrating structures using nonlinear normal modes", J. Sound Vib., 330(3), 486-509. https://doi.org/10.1016/j.jsv.2010.08.028
  35. Peeters, M., Kerschen, G. and Golinval, J.C. (2011b), "Modal testing of nonlinear vibrating structures based on nonlinear normal modes: Experimental demonstration", Mech. Syst. Signal Processing, 25(4), 1227-1247. https://doi.org/10.1016/j.ymssp.2010.11.006
  36. Peeters, M., Viguie, R., Serandour, G., Kerschen, G. and Golinval. J.C. (2009a), "Nonlinear normal modes, Part II: Toward a practical computation using numerical continuation techniques", 23(1), 195-216. https://doi.org/10.1016/j.ymssp.2008.04.003
  37. Pereira, P., Almeida, L., Suleman, A., Bond, V., Canfield, R. and Blair, M. (2007), "Aeroelastic scaling and optimization of a joined-wing aircraft concept", 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Honolulu, Hawaii, April.
  38. Reichenbach, E. (2008), "Aeroservoelastic design and test validation of the Joined Wing Sensorcraft", 26th AIAA Applied Aerodynamics Conference, Honolulu, Hawaii, August.
  39. Reichenbach, E., Castelluccio, M. and Sexton, B. (2011), "Joined Wing Sensorcraft Aeroservoelastic Wind Tunnel Test Program", 52nd AIAA/ ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Denver, U.S.A., April.
  40. Richards, J. (2014), "An experimental investigation of a joined wing aircraft configuration using flexible, reduced scale flight test vehicles", Ph.D. Dissertation, University of Victoria, Victoria.
  41. Richards, J., Aarons, T., Suleman, A., Canfield, R., Woolsey, C., Lindsley, N. and Blair, M. (2011), "Design for flight test of a scaled Joined Wing SensorCraft", 52nd AIAA/ ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Denver, U.S.A., April.
  42. Richards, J., Suleman, A., Aarons, T. and Canfield, R. (2010), "Multidisciplinary design for flight test of a scaled Joined Wing SensorCraft", 13th AIAA/ISSMO Multidisciplinary Analysis Optimization Conference, Fort Worth, U.S.A., September.
  43. Richards, J., Suleman, A., Canfield, R. and Blair, M. (2009), "Design of a scaled rpv for investigation of gust response of joined-wing Sensorcraft", 50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Palm Springs, U.S.A., April.
  44. Richardson, M. and Formenti, D. (1985), "Global curve fitting of frequency response measurements using the rational fraction polynomial method", IMAC III, Orlando, U.S.A., January.
  45. Rosenberg, R. (1960), "Normal modes of nonlinear dual-mode systems", J. Appl. Mech., 27(2), 263-268. https://doi.org/10.1115/1.3643948
  46. Samuels, M.F. (1982), "Structural weight comparison of a joined wing and a conventional wing", J. Aircraft, 19(6), 485-491. https://doi.org/10.2514/3.57418
  47. Scott, M., Enke, A. and Flanagan, J. (2011), "Sensorcraft free-flying aeroservoelastic model design and fabrication", 52nd AIAA/ ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, Denver, U.S.A., April.
  48. Sehgal, S. and Kumar, H. (2016), "Structural dynamic model updating techniques: A state of the art review", Archives Comput. Methods Eng., 23(3), 515-533. https://doi.org/10.1007/s11831-015-9150-3
  49. Stanbridge, A.B. and Ewins, D.J. (1999), "Modal testing using a scanning laser doppler vibrometer", Mech. Syst. Signal Processing, 13(2), 255-270. https://doi.org/10.1006/mssp.1998.1209
  50. Teunisse, N., Demasi, L., Tiso, P. and Cavallaro, R. (2017), "Reduced basis methods for structurally nonlinear Joined Wings", Aerosp. Sci. Technol., 68, 486-495. https://doi.org/10.1016/j.ast.2017.05.041
  51. Wolkovitch, J. (1986), "The joined wing - An overview", J. Aircraft, 23(3), 161-178. https://doi.org/10.2514/3.45285
  52. Vakakis, A.F. (1997), "Non-linear normal modes (NNMs) and their applications in vibration theory: An overview", Mech. Syst. Signal Processing, 11(1), 3-22. https://doi.org/10.1006/mssp.1996.9999
  53. Yang, Y., Dorn, C., Mancini, T., Talken, Z., Kenyon, G., Farrar, C. and Mascarenas, D. (2017), "Blind identification of full-field vibration modes from video measurements with phase-based video motion magnification", Mech. Syst. Signal Processing, 85, 567-590. https://doi.org/10.1016/j.ymssp.2016.08.041