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Validation of a rotorcraft mathematicalmodel in autorotation by use of gyroplane flighttests

Published online by Cambridge University Press:  03 February 2016

V. M. Spathopoulos
V. M. Spathopoulos*
Affiliation:
Athens, Greece
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Abstract

Aircraft handling qualities in autorotation arecritical in determining the level of safety ofrotorcraft. For helicopters suffering from an enginefailure, transcending from powered to autorotativeflight occurs rapidly and requires immediate andaccurate pilot reaction. Although it is importantfor the handling qualities in this flight state tobe predicted correctly, obvious difficulties willexist in using flight tests as a means of validationwhen autorotation constitutes an abnormal mode ofoperation. In the research work presented in thispaper an alternative approach is applied, ofconfiguring a generic rotorcraft model as agyroplane, a type of vehicle for which its mainrotor is constantly in autorotation. Flight testsare used for the validation purposes both for steadystate and dynamic response cases. Results areproduced to complement those already existing for adissimilar gyroplane type thus increasing the levelof confidence obtained. It is concluded thatimportant handling qualities indicators such as thesteady state trends are correctly predicted althoughlimitations are imposed due to rotor speeddiscrepancy.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 108 , Issue 1079 , January 2004 , pp. 51 - 58
Copyright
Copyright © Royal Aeronautical Society 2004 

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References

1. Padfield, G.D. Helicopter Flight Dynamics, 1996, Blackwell Science.Google Scholar
2. Pegg, R.J. A flight investigation of a lightweight helicopter to study the feasibility of fixed-collective-pitch autorotations, NASA TN D-5270, June 1969, pp 4.Google Scholar
3. Segner, D.R. AH-56A Compound helicopter autorotation characteristics, Society of Experimental Test Pilots, Technical Review, 1973, 11, (2), pp 29–47.Google Scholar
4. Houston, S.S. Thomson, D.G. and Coton, F. The aerodynamics of gyroplanes, 1994-1997, CAA Contract No 7D/S/1125, Progress Report Phases 1–3.Google Scholar
5. Houston, S.S. Validation of a rotorcraft mathematical model for autogyro simulation, J Aircr, 2000, 37, (3), pp 403–409.Google Scholar
6. Houston, S.S. Validation of a non-linear individual blade rotorcraft flight dynamics model using a perturbation method, Aeronaut J, Aug/Sept 1994, 98, (977), pp 260–266.Google Scholar
7. Chen, R.T.N. A survey of non-uniform inflow models for rotorcraft flight dynamics and control applications, Vertica, 1990, 14,(2), pp 147–184.Google Scholar
8. Pitt, D.M. and Peters, D.A. Theoretical prediction of dynamic inflow derivatives, Vertica, 1981, 5, pp 21–34.Google Scholar
9. Gaonkar, G.H. and Peters, D.A. A review of dynamic inflow modelling for rotorcraft flight dynamics, Vertica, 1988, 12, (3), pp 213–242.Google Scholar
10. Peters, D.A. and Haquang, N. Dynamic inflow for practical applications, J American Helicopter Soc, October 1988, Technical Note, pp 64–68.Google Scholar
11. Doyle, S.A. Thomson, D.G. Modification of a helicopter inverse simulation to include an enhanced rotor model, J Aircr, 2000, 37, (3), pp 536–538.Google Scholar
12. Johnson, W. Helicopter Theory, 1980, Princeton University Press.Google Scholar
13. Glauert, H. A General theory of the autogyro, Nov 1926, Aeronautical Research Committee Reports and Memoranda No 1111.Google Scholar
14. Houston, S.S. Identification of autogyro lateral/directional stability and control characteristics from flight test, 1998, Proc Inst Mech Eng, 212, Part G, J Aerospace Eng, pp 271–285.Google Scholar