Hostname: page-component-78c5997874-t5tsf Total loading time: 0 Render date: 2024-11-17T17:22:42.847Z Has data issue: false hasContentIssue false
  • English
  • Français

Acoustic validation of a new code using particle wake aerodynamics and geometrically-exact beam structural dynamics

Published online by Cambridge University Press:  03 February 2016

F. Nitzsche  and
D. G. Opoku
F. Nitzsche
Affiliation:
Department of Mechanical and Aerospace Engineering, Carleton University, Ottawa, Canada
D. G. Opoku
Affiliation:
United Technologies Research Center, East Hartford, CT, USA
Get access Rights & Permissions [Opens in a new window]

Abstract

This paper describes the validation of a new code for prediction both aeroacoustic and aeroelastic behaviour of hingeless rotors. The structural component is based on a non-linear beam element model considering small strains and finite rotations, which uses a mixed variational intrinsic formulation. The aerodynamic component is built on a loworder panel method incorporating a vortex particle free-wake model. The aerodynamic and structural components are combined to form a closely coupled aeroelastic code that solves in the time-domain. The loading and thickness noise terms for the aeroacoustic calculations are calculated from the aerodynamic data using a formulation based on the Ffowcs Williams-Hawkings (FW-H) equation. The code is successfully validated for acoustic signature and BVI predictions using test cases from the HELINOISE program.

Type
Research Article
Information
The Aeronautical Journal , Volume 109 , Issue 1096 , June 2005 , pp. 257 - 267
Copyright
Copyright © Royal Aeronautical Society 2005 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Voutsinas, S.G.. A GENeralized Unsteady Vortex Particle method (GENUVP) for solving the unsteady flow around multi-component configurations, 1990, Report, Dept. of Mechanical Engineering, Fluids Section, National Technical University of Athens, Greece.Google Scholar
2. Cheng, T.. Structural Dynamics Modeling of Helicopter Blades for Computational Aeroelasticity, 2002, Master’s of Science Dissertation, Massachusetts Institute of Technology, Cambridge, MA.Google Scholar
3. Hodges, D.H.. A mixed variational formulation based on exact intrinsic equations for dynamics of moving beams, Int J solids and structures, 1990, 26, (11), pp 1253–1273.Google Scholar
4. Opoku, D.G.. Aeroelastic and Aeroacoustic Modelling of Rotorcraft, 2002, Master of Applied Science Dissertation, Dept of Mechanical and Aerospace Engineering, Carleton University, Ottawa, Canada.Google Scholar
5. Ffowcs-Williams, J.E. and Hawkings, D.L.. Sound generation by turbulence and surfaces in arbitrary motion, 1969, Philosophical Transactions of the Royal Society, A264.Google Scholar
6. Strawn, R.C. and Djomehri, R.C.. Computational modelling of hovering rotor and wake aerodynamics, Proc 57th AHS Annual Forum, Washington, DC, 9-11 May 2001, pp 1723–1734.Google Scholar
7. Pahlke, K. and Chelli, E.. Calculation of multibladed rotors in forward flight using a 3D Navier-Stokes method, Proc 26th European Rotorcraft Forum, The Hague, Netherlands, 26–29 September 2000.Google Scholar
8. Voutsinas, S.G. and Triantos, D.G.. High-resolution aerodynamic analysis of full helicopter configurations, 14–16 September 1999, Proc.25th European Rotorcraft Forum, Rome, Italy.Google Scholar
9. Voutsinas, S.G. and Triantos, D.G.. Aeroacoustics of full helicopter configurations using vortex particle flow approximations, Proc. CEAS Forum on Aeroacoustics of Rotors and Propellers, 9–11 June 1999, Rome, Italy.Google Scholar
10. Voutsinas, S.G., Belessis, M.A. and Rados, K.G.. Investigation of the yawed operation of wind turbines by means of a vortex particle method, 1995, Report AGARD CP552, Proc. FDP Symposium on Aerodynamics and Aeroacoustics of Rotorcraft, Berlin, Germany.Google Scholar
11. Shin, S.. Integral Twist Actuation of Helicopter Rotor Blades for Vibration Reduction, 2001, PhD dissertation, Dept of Aeronautics and Astronautics, Massachusetts Institute of Technology, Cambridge, MA.Google Scholar
12. Johnson, W.. Rotorcraft aerodynamics models for a comprehensive analysis, 1998, Proc American Helicopter Society 54th Annual Forum, Washington, DC, 20–22 May.Google Scholar
13. Peters, D.A. and He, C.J. 1995, Finite state induced flow models part II: Three-dimensional rotor disk, J Aircr, 32, (2), pp 323–333.Google Scholar
14. Shang, X.. Aeroelastic Stability of Composite Hingeless Rotors With Finite-State Unsteady Aerodynamics, 1995, PhD dissertation, School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, GA.Google Scholar
15. Opoku, D.G., Nitzsche, F., Chang, T. and Cesnik, C.S.. Aeroelastic modeling of active twist rotorblades using particle-wake aerodynamics and Non-linear beam structural dynamics, Paper IMECE 2002-32961, Proc 2002 ASME International Mechanical Engineering Congress and Exposition, New Orleans, LA, November 17–22.Google Scholar
16. Brentner, K.S.. Modeling aerodynamically generated sound: recent advances in rotor noise prediction, Paper AIAA 2000-0345, 38th Aerospace Sciences Meeting and Exhibit, 10–13 January 2000, Reno, NV.Google Scholar
17. Farassat, F. and Succi, G.P.. The prediction of helicopter rotor discrete frequency noise, 1983, Vertica, 7, (4), pp 309–320.Google Scholar
18. Schultz, K.J. et al, Aeroacoustic calculation of helicopter rotors at DLR, Report AGARD CP552, Proc FDP Symposium on Aerodynamics and Aeroacoustics of Rotorcraft, Berlin, Germany, 10–13 October 1994.Google Scholar
19. Beaumier, et al, Effect of higher harmonic control on helicopter rotor blade-vortex interaction noise: prediction and initial validation, 10–13 October 1994, Report AGARD CP552, Proc FDP Symposium on Aerodynamics and Aeroacoustics of Rotorcraft, Berlin, Germany.Google Scholar
20. Brentner, K.S.. An efficient and robust method for predicting helicopter high-speed impulsive noise, 1997, J Sound and Vibration, 23, (1), pp 87–100.Google Scholar
21. Conner, D.A. and Hoad, D.R.. Reduction of high-speed impulsive noise by blade planform modification of a model helicopter rotor, 1982, NASA TM-84553, Langley Research Center, Hampton, VA.Google Scholar
22. Brentner, K.S.. Prediction of helicopter rotor discrete frequency noise: A computer program incorporating realistic blade motions and advanced acoustic formulation, 1986, NASA TM-87721, Langley Research Center, Hampton, VA.Google Scholar
23. Kloppel, V., Helicopter and Tilt-Rotor Aircraft Exterior Noise Research (HELINOISE), Advances in Acoustics Technology, 1995, John Wiley and Sons, New York, NY.Google Scholar
24. Splettstoesser, W.R. et al, The HELINOISE Aeroacoustic Rotor Test in the DNW – Test Documentation and Representative Results, 1993, DLR-Mitt. 93–09, German Aerospace Center, Braunschweig, Germany.Google Scholar