Hostname: page-component-7dd5485656-jtdwj Total loading time: 0 Render date: 2025-10-31T12:05:40.663Z Has data issue: false hasContentIssue false
  • English
  • Français

Validation of a blade-element helicopter model for large-amplitude manoeuvres

Published online by Cambridge University Press:  04 July 2016

S. S. Houston
S. S. Houston*
Affiliation:
Department of Aerospace EngineeringUniversity of GlasgowScotland
Get access Rights & Permissions [Opens in a new window]

Abstract

The contemporary approach to helicopter mathematical modelling in simulation for handling qualities applications is to represent each blade individually. This allows incorporation of effects not possible with a multiblade disc representation of the rotor system. This paper addresses the validation of such a model, which is uniquely performed for large amplitude manoeuvres, using a recently-developed approach to inverse simulation. The method is reviewed in the context of model validation, and comparisons between simulation and actual data are presented for a Puma helicopter executing sidestep manoeuvres in low-speed flight. The focus for interpreting the results is in the area of wake modelling. It is concluded that further developments are necessary in this area if helicopter flight mechanics models are to be used in simulation of role-related flight.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 101 , Issue 1001 , January 1997 , pp. 1 - 8
Copyright
Copyright © Royal Aeronautical Society 1997 

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.)

Article purchase

Temporarily unavailable

References

1. Padfield, G.D. Theoretical modelling for helicopter flight dynamics: development and validation, Proceedings of the International Congress of the Aeronautical Sciences, Jerusalem, Israel, 1988.Google Scholar
2. Houston, S.S. Rotorcraft Aeromechanics Simulation for Control Analysis — Mathematical Model Definition, University of Glasgow Dept. of Aerospace Engineering Internal Report No 9123, 1991.Google Scholar
3. Lehmann, G, Oertel, C-H. and Gelhaar, B. A new approach in helicopter real-time simulation, Proceedings of the 15th European Rotorcraft Forum, Amsterdam, The Netherlands, 1989.Google Scholar
4. DuVal, R.W. A real-time blade-element helicopter simulation for handling qualities analysis, Proceedings of the 15th European Rotorcraft Forum, Amsterdam, The Netherlands, 1989.Google Scholar
5. Meerwijk, L. and Brouwer, W. Real-time helicopter simulation using the blade-element method, Proceedings of the 17th European Rotorcraft Forum, Berlin, Germany, 1989, ISBN 3 922010 66 0.Google Scholar
6. Chen, R.T.N. A survey of non-uniform inflow models for rotorcraft flight dynamics and control applications, Proceedings of the 15th European Rotorcraft Forum, Amsterdam, The Netherlands, 1989.Google Scholar
7. Gaonkar, G.H. and Peters, DA. A review of dynamic inflow modeling for rotorcraft flight dynamics, Vertica, 1988, 12, (3), pp 213–242.Google Scholar
8. Peters, D.A. and HaQuang, N. Dynamic inflow for practical applica tions, J Am Helicopter Soc, 1988, 33, (4).Google Scholar
9.Various, Rotorcraft system identification, AGARD Lecture Series 178, 1991.Google Scholar
10. Houston, S.S. Validation of a non-linear individual blade rotorcraft flight dynamics model using a perturbation method, Aeronaut J, 1994, 98, (977), pp 260–266.Google Scholar
11. Bradley, R., Padfield, G.D., Murray-Smith, D.J. and Thomson, D.G. Validation of helicopter mathematical models, Transact Institute Measure Cntl, 1990, 12, (4).Google Scholar
12. Rutherford, S. and Thomson, D.G. Helicopter inverse simulation incorporating an individual blade rotor model, Proceedings of the 20th International Congress of the Aeronautical Sciences, Sorrento, Italy, 1996.Google Scholar
13. Tischler, M.B. Digital control of highly augmented combat rotorcraft, NASA TM-88346, 1987.Google Scholar
14. Tournour, S.R. and Celi, R. Modeling of flexible rotor blades for heli copter flight dynamics applications, J Am Helicopter Soc, 1996, 41, (1), pp 52–66.Google Scholar
15. Thomson, D.G. and Bradley, R. Development and verification of an algorithm for helicopter inverse simulation, Vertica, 1990, 14, (2).Google Scholar
16. Rutherford, S. and Thomson, D.G. Improved methodology for inverse simulation, Aeronaut J, 1996, 100, (993), pp 79–86.Google Scholar
17. Gao, C. and Hess, R.A. Inverse simulation of large-amplitude aircraft manoeuvres, J Guid Cntl Dyn, 1993, 16, (4), pp 733–737.Google Scholar
18. Ellenreider, T.J. Investigation of the Dynamic Wake of a Model Rotor, PhD Dissertation, University of Bristol, 1996.Google Scholar
19. Hess, R.A., Gao, C. and Wang, S.H. Generalized technique for inverse simulation applied to aircraft manoeuvres, J Guid Cntl Dyn, 1991, 14, (5), pp 920–926.Google Scholar
20. Lin, K-C. Comment on generalized technique for inverse simulation applied to aircraft manoeuvres, J Guid Cntl Dyn, 1993, 16, (6), pp 1196–1197.Google Scholar