DOI QR코드

DOI QR Code

Non-linear aero-elastic response of a multi-layer TPS

  • Pasolini, P. (Department of Industrial Engineering (DII), University of Naples "Federico II") ;
  • Dowell, E.H. (Department of Mechanical Engineering and Materials Science, Duke University) ;
  • Rosa, S. De (Department of Industrial Engineering (DII), University of Naples "Federico II") ;
  • Franco, F. (Department of Industrial Engineering (DII), University of Naples "Federico II") ;
  • Savino, R. (Department of Industrial Engineering (DII), University of Naples "Federico II")
  • Received : 2016.12.02
  • Accepted : 2016.12.06
  • Published : 2017.07.25

Abstract

The aim of the present work is to present a computational study of the non-linear aero-elastic behavior of a multi-layered Thermal Protection System (TPS). The severity of atmospheric re-entry conditions is due to the combination of high temperatures, high pressures and high velocities, and thus the aero-elastic behavior of flexible structures can be difficult to assess. In order to validate the specific computational model and the overall strategy for structural and aerodynamics analyses of flexible structures, the simplified TPS sample tested in the 8' High Temperature Tunnel (HTT) at NASA LaRC has been selected as a baseline for the validation of the present work. The von $K{\acute{a}}rm{\acute{a}}n^{\prime}s$ three dimensional large deflection theory for the structure and a hybrid Raleigh-Ritz-Galerkin approach, combined with the first order Piston Theory to describe the aerodynamic flow, have been used to derive the equations of motion. The paper shows that a good description of the physical behavior of the fabric is possible with the proposed approach. The model is further applied to investigate structural and aero-elastic influence of the number of the layers and the stitching pattern.

Keywords

References

  1. Carandente, V. (2014), "Aerthermodynamic and mission analyses of deployable aerobraking earth re-entry systems", Ph.D. Dissertation.
  2. Carandente, V., Elia, G. and Savino, R. (2013), "Conceptual design of de-orbit and re-entry modules for standard cubesats", Proceedings of the 2nd IAA Conference on University Satellite Missions and Cubesat Workshop, Rome, February.
  3. Carandente, V. and Savino, R. (2014), "New concepts of deployable de-orbit and re-entry systems for cubesat miniaturized satellites", Rec. Pat. Eng., 8(1), 2-12. https://doi.org/10.2174/1872212108666140204004335
  4. Carandente, V., Savino, R., D'Oriano, V. and Fortezza, R. (2014), "Deployable aerobraking earth entry systems for recoverable microgravity experiments", Proceedings of the 65th International Astronautical Congress, Toronto, Canada, September.
  5. Carandente, V., Savino, R., Iacovazzo, M. and Boffa, C. (2013), "Aerothermal analysis of a sample-return reentry capsule", Flu. Dyn. Mater. Proc., 9(4), 461-484.
  6. Carandente, V., Zuppardi, G. and Savino, R. (2014), "Aerothermodynamic and stability analyses of a deployable re-entry capsule", Acta Astronaut., 93, 291-303. https://doi.org/10.1016/j.actaastro.2013.07.030
  7. Dillman, R., DiNonno, J., Bodkin, R., Gsell, V., Miller, N., Olds, A. and Bruce, W. (2013), "Flight performance of the inflatable reentry vehicle experiment 3", Proceedings of the 10th International Planetary Probe Workshop, San Jose, U.S.A., June.
  8. Dillman, R., DiNonno, J., Bodkin, R., Gsell, V., Miller, N., Olds, A. and Bruce, W. (2010), "Flight performance of the inflatable reentry vehicle experiment II", Proceedings of the International Planetary Probe Workshop, Barcelona, Spain, June.
  9. Dowell, E. (1970), "Panel flutter: A review of aeroelastic stability of plates and shells", AIAA J., 8(3), 385-399. https://doi.org/10.2514/3.5680
  10. Dowell, E. (1975), Aeroelasticity of Plates and Shells, Springer, New York, U.S.A.
  11. Dugundji, J. (1966), "Theoretical considerations of panel flutter at high supersonic mach numbers", AIAA J., 4(7), 1257-1266. https://doi.org/10.2514/3.3657
  12. Ellen, C. (1965), "Approximate solution of the membrane flutter problem", AIAA J., 3(6), 1186-1187. https://doi.org/10.2514/3.3096
  13. Goldman, B. and Dowell, E. (2014), "Nonlinear oscillations of a fluttering plate resting on a unidirectional elastic foundation", AIAA J., 52(10), 2364-2368. https://doi.org/10.2514/1.J053290
  14. Goldman, B., Dowell, E. and Scott, R. (2013), "Flutter analysis of the thermal protection layer on the NASA HIAD", Proceedings of the 22nd AIAA Aerodynamic Decelerator Systems (ADS) Conference, Florida, U.S.A.
  15. Goldman, B., Dowell, E. and Scott, R. (2014), "In-flight aeroelastic stability of the thermal protection system on the NASA HIAD, part I: Linear theory", Proceedings of the 55th AIAA/ASMe/ASCE/AHS/SC Structures, Structural Dynamics, and Materials Conference, Maryland, U.S.A.
  16. Goldman, B., Dowell, E. and Scott, R. (2015), "In-flight aeroelastic stability of the thermal protection system on the NASA HIAD, part II: Nonlinear theory and extended aerodynamics", Proceedings of the 56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Florida, U.S.A.
  17. Goldman, B., Scott, R. and Dowell, E. (2014), Nonlinear Aeroelastic Analysis of the HIAD TPS Coupon in the NASA 8' High Temperature Tunnel: Theory and Experiment, NASA TM-2014-218267.
  18. Guruswamy , G. (2002), "A review of numerical fluids/structures interface methods for computations using high-fidelitynequations", Comput. Struct., 80(1), 31-41. https://doi.org/10.1016/S0045-7949(01)00164-X
  19. Hughes, S., Dillman, R., Starr, B., Stephan, R., Lindell, M., Player, C. and Cheatwood, F. (2005), "Inflatable re-entry vehicle experiment (IRVE) design overview", Proceedings of the 18th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar, Munich, Germany, May.
  20. Johns, D. (1971), "Supersonic membrane flutter", AIAA J., 9(5), 960-961. https://doi.org/10.2514/3.6309
  21. Kramer, R., Cirak, F. and Pantano, C. (2013), "Fluid-structure interaction simulations of a tension-cone inflatable aerodynamic decelerator", AIAA J., 51(7), 1640-1656. https://doi.org/10.2514/1.J051939
  22. McNamara, J. and Friedmann, P. (2007), Aeroelastic and Aerothermoelastic Analysis of Hypersonic Vehicles: Current Status and Future Trends, Collection of Technical Papers-AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference, 3814.
  23. McNamara, J. and Friendmann, P. (2011), "Aeroelastic and aerothermoelastic analysis in hypersonic flows: Past, present, and future", AIAA J., 49(6), 1089-1122. https://doi.org/10.2514/1.J050882
  24. Mei, C., Abdel-Motagaly, K. and Chen, R. (1999), "Review of nonlinear panel flutter at supersonic and hypersonic speeds", Appl. Mech. Rev., 52(10), 321-332. https://doi.org/10.1115/1.3098919
  25. Rohrschneider, R. (2007), "Variable-fidelity hypersonic aeroelastic analysis of thin-film ballutes for aerocapture", Ph.D. Dissertation, Georgia Institute of Technology, U.S.A.
  26. Savino, R. (2013), "Study and development of a sub-orbital reentry demonstrator", Proceedings of the Italian Association of Aeronautics and Astronautics XXII Conference, Naples, Italy, September.
  27. Savino, R. and Carandente, V. (2012), "Aerothermodynamic and feasibility study of a deployable aerobraking re-entry capsule", Flu. Dyn. Mater. Process., 8(4), 453-477.
  28. Scott, R., Bartels, R. and Kandil, O. (2007), "An aeroelastic analysis of a thin flexible membrane", Proceedings of the 48th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Hawaii, U.S.A.
  29. Spriggs, J., Messiter, A. and Anderson, W. (1969), "Membrane flutter paradox-an explanation by singular perturbation methods", AIAA J., 7(9), 1704-1709. https://doi.org/10.2514/3.5379
  30. Wang, Z., Yang, S., Liu, D., Wang, X., Mignolet, M. and Bartels, R. (2010), Nonlinear Aeroelastic Analysis for a Wrinkling Aeroshell/Ballute System, Collection of Technical Papers-AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference.
  31. Wilde, D. and Walther, S. (2001), "Inflatable re-entry and descent technology (IRDT)-further developments", Proceedings of the 2nd International Symposium of Atmospheric Re-entry Vehicles and Systems, Arcachon, France.

Cited by

  1. Coupled Fluid-Structural Thermal Numerical Methods for Thermal Protection System vol.57, pp.8, 2017, https://doi.org/10.2514/1.j057616